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UTOMATIC YNAMIC NCREMENTAL ONLINEAR NALYSIS
ADINA User Interface Command Reference Manual Volume I: ADINA Solids & Structures Model Definition Report ARD 09-2
May 2009 ADINA R & D, Inc.
ADINA User Interface Command Reference Manual Volume I: ADINA Solids & Structures Model Definition
Report ARD 09-2 May 2009 for the ADINA System version 8.6 ADINA R & D, Inc. 71 Elton Avenue Watertown, MA 02472 USA tel. (617) 926-5199 telefax (617) 926-0238 www.adina.com
Model definition ................................................................................................... 7-1 Material models .................................................................................................... 7-3 Cross-Sections/Layers ...................................................................................... 7-168 Element properties ............................................................................................. 7-188 Substructures and cyclic symmetry .................................................................. 7-225 Contact conditions ............................................................................................ 7-238 Fracture mechanics ............................................................................................ 7-310 Boundary conditions ......................................................................................... 7-334 Loading .............................................................................................................. 7-368 Initial conditions ................................................................................................ 7-402 Systems ............................................................................................................. 7-414
Chapter 8 8.1 8.2 8.3
Finite element representation ............................................................................. 8-1 Element groups ..................................................................................................... 8-3 Mesh generation.................................................................................................. 8-58 Elements ............................................................................................................. 8-154
Chapter 9 9.1 9.2 9.3 9.4 9.5 9.6 9.7 9.8
Direct finite element data input ........................................................................... 9-1 Nodal data ............................................................................................................. 9-3 Element data ........................................................................................................ 9-14 Boundary conditions ........................................................................................... 9-54 Loads ................................................................................................................... 9-62 Initial conditions .................................................................................................. 9-75 Contact ................................................................................................................ 9-87 Fracture ................................................................................................................ 9-91 Substructures and cyclic symmetry .................................................................... 9-97
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
Chapter 1 Introduction
Sec. 1.1 Program execution
1. Introduction This reference manual provides concise descriptions of the command input requirements for the ADINA User Interface (AUI). This introduction serves to give some background information and indicate the general command syntax including descriptions of the conventions used.
1.1 Program execution Commands can be entered in the following modes: Interactive (a) AUI is running with the user interface displayed – you can enter commands into the user interface command window. (b) AUI is running in command mode (using the "-cmd" option) – you can enter commands from standard input. Batch (a) AUI is running with the user interface displayed – you can read commands from a file by choosing File→Open. (b) Commands can be read from a given file using the aui startup options -s (UNIX versions) or -b (Windows version). You can also read commands from a file using the READ command (see Section 3).
1.2 Command syntax Here is the layout of a typical command reference page:
COMMAND[1]
PARAM1 PARAM2[2]...
data1i data2i[3]... General description of command function.[4]
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PARAM1 Description of parameter PARAM1[5]. {}[7] PARAM2 Description of parameter PARAM2.
[][6] []
{}
... data1i [][6] [5] Description of data line entry data1i (ith row, column 1). {}[7] data2i [] Description of data line entry data2i (ith row, column 2). {} ... Auxiliary commands[8] LIST COMMAND Brief description of this command. DELETE COMMAND Brief description of this command.
Issuing a command allows you to alter the data associated with the command. This data comprises the values associated with the command parameters and possibly a table, input via "data lines", associated with the command. In the above, the command name "COMMAND"[1], given at the top of the reference page, has the first few characters emphasized to show the minimum number of characters required to be input to uniquely identify the command. A list of parameters[2] and data lines[3] for the command then follows. In this list the first few characters in the parameter and data line names are emphasized to show the minimum number of characters required to uniquely identify the parameter and data line names. Following a general outline of the command function[4], a description of the command parameters and data line entries is given below the relevant keynames[5]. The parameters usually have default values[6] which are assumed if the parameter is not explicitly specified. The default values are indicated in brackets [ ] – a bold value indicates a default value (number or string) and an italicized string indicates the source of the default value, which is either (a) a text description of the default, (b) a parameter name from the same
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Sec. 1.2 Command syntax
command, or (c) a combination of command + parameter names, indicating that the default is taken from the setting of another (different) command parameter. A parameter for which no default is provided means that there is no default – i.e., some choice must be entered for that parameter. One important parameter type is that of an entity identifier – for which the parameter keyname "NAME" is normally reserved. If the object identified by NAME has already been defined, then the other parameter defaults are set to the previous settings for that object. If a new NAME is given then the defaults, as indicated by the command reference pages herein, are taken. In the former case, execution of the command redefines the named object. The choice of parameter values is often discussed within the parameter description, but, where appropriate, a simple list of choices follows the parameter description[7]. For example, parameters with simple logical choices will have the list "{YES/NO}" appended to the description. When a table is associated with the command, the command includes data input lines. For some commands, the table is initially empty, but for other commands the table already includes data lines. The columns of a data line can be divided into two types: key columns and data columns. When a data line has key columns, the key value columns always precede the data value columns. In this case the values of the key columns uniquely identify the data line, and, therefore, two data lines cannot have the same key column values – for such input, the second input data line overwrites the data associated with the key column values. You can delete a data line by preceding the key column values with the DELETE prefix. When a data line does not have key columns, two or more data lines can have the same values – but you cannot use the DELETE prefix to delete data lines without key columns. However, you can always delete all of the data lines of a table using the @CLEAR or CLEAR keywords. This is of course especially useful for those tables in which there are no key columns. For data line input, not all the columns need be specified; the ENTRIES keyword, which can be input as the first data line following the command line, can be used to select a subset of the data column entries (see below). Then the values you enter in the subsequent data lines are associated with the columns indicated by the ENTRIES parameters, the other data columns taking default values whenever possible. Note, however, that key columns are required input, and should thus be included in the ENTRIES column list. Many commands have "auxiliary" commands[8] which are entered with one of the following prefixes:
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LIST DELETE UPDATE RESET COPY SET SHOW
List object definitions. Delete objects from the database. Update command defaults. Reset command defaults. Copy objects. Set "currently active" objects. Show "currently active" objects.
A LIST prefixed command has several forms: LIST COMMAND
List all object identifiers (names).
LIST COMMAND
NAME
List definition of object with identifier NAME.
LIST COMMAND
FIRST LAST
List definitions of a range of objects with integer label numbers. Parameters FIRST, LAST may also take the string values ‘FIRST’, ‘LAST’, ‘ALL’.
A DELETE prefixed command has the following forms: DELETE COMMAND
NAME
Delete the object with identifier NAME.
DELETE COMMAND
FIRST LAST
Delete a set of objects with integer label numbers in the specified range.
Note that an object may not be deleted if another model entity depends on its existence as part of its own definition. For example, a geometry line cannot be deleted if it forms a bounding edge of some geometry surface.
1.3 Input details Command input Please refer to command AUTOMATIC LOAD-DISPLACEMENT in the following discussion (Section 5.5): AUTOMATIC LOAD-DISPLACEMENT
POINT DOF DISPLACEMENT ALPHA DISPMAX CONTINUE RPRINT TYPE NODE
When entering commands, only as many characters as necessary to uniquely specify the command name need be entered. The same rule applies to the parameters and data line entry
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Sec. 1.3 Input details
key names within a command. The minimum number of characters necessary are indicated in bold. Note that command / parameter is case insensitive. All commands, parameters, values are stored in upper case, except for string variables (headings, graph legends, etc.). Parameter values may be input in any order if the keynames are used, e.g., AUTOMATIC LOAD-DISPLACEMENT DOF=3 RPRINT=YES DISPMAX=5.0 DISPLACEMENT=4.0 POINT=17 Some or all of the parameters can be excluded if the positional order of the parameters is observed, e.g., AUTOMATIC LOAD-DISPLACEMENT 17
3
4.0, ,5.0, ,YES
(the parameters ALPHA and CONTINUE have been omitted by the use of the commas). A mix of keyname parameters and positional input is allowed, e.g., AUTOMATIC LOAD-DISPLACEMENT 17 DISPLACEMENT=4.0 DOF=3,,5.0,, YES The above uses of the AUTOMATIC LOAD-DISPLACEMENT command are all equivalent. The omitted parameters in each case take the default values. Data lines Many commands require data line (tabular) input, e.g., MODAL-DAMPING (see Section 5.3): MODAL-DAMPING modei factori Use the ENTRIES keyword to select only the data columns that you want to enter (the other data columns will be given default values): MODAL-DAMPING ENTRIES MODE FACTOR 1 1.0 2 0.5 3 2.5 4 1.5 DATAEND Most commands which take this form of input also allow for incremental row generation via the "STEP inc TO" option where "inc" represents an increment in the generation, i.e., in the above
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example modei+k, modei+2k, ..., modej-k, are all generated, with the corresponding values for "factor" linearly interpolated between factori and factorj. When generating integer values, the difference between the first and last values must be an integer multiple of the STEP increment (i.e., modulo((modej-modei),k) = 0). There is a default step increment, which for integer values is normally 1; in this case "STEP 1 TO" may be input simply as "TO". Here are some examples: MODAL-DAMPING 1 5.5 TO 3 7.5 @ or MODAL-DAMPING 1 5.5 STEP 1 TO 3 7.5 DATAEND Both of these are equivalent to MODAL-DAMPING 1 5.5 2 6.5 3 7.5 @ Note that data line input may be terminated either by entering the symbol "@" or the string "DATAEND" – data line input will be terminated automatically by input of the next command. Data line rows can be deleted by preceding the key value by the prefix DELETE. This method of deletion also supports row "generation" – i.e., "DELETE i STEP k TO j" may be used to delete a range of values. All the data lines associated with a command may be deleted simultaneously using the CLEAR or @CLEAR keywords. This is useful when you want to define a table if you do not know if the table is already defined or not: TIMEFUNCTION 1 CLEAR which removes all the currently defined data lines of timefunction 1. The columns for data line input can be selected by use of the keyword ENTRIES in the first input data line following the command line, e.g., 1-8
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Sec. 1.3 Input details
COORDINATES POINT ENTRIES NAME Y Z which indicates that only global Y and Z coordinates are to be input for geometry points in the subsequent data lines. The X coordinate assumes the default value 0.0, and thus subsequent data lines entered describe points in the global Y-Z plane. Names AUI names are usually of two types – alphanumeric strings of up to 30 characters or integer label numbers. Integer label numbers are normally greater than or equal to 1. Integer values Integers can be input with a maximum of 9 significant digits. For positive values, a preceding + sign may, if desired, be input. Real values Specification of real values can include a decimal point and/or an exponent. The exponent must be preceded by the letters E, e, D, or d, e.g., 2E5 2.0d+05 200000. all refer to the same real number. Alphanumeric values Alphanumeric values must start with a letter (A-Z, a-z) or number (0-9). The only permissible characters allowed are the letters A-Z, a-z, the digits 0 to 9, the hyphen (-), and the underscore (_). Lower-case characters in an alphanumeric value are always converted to upper-case by the AUI. String values A string should be enclosed by apostrophes ('). Any apostrophe within the string must be entered twice. Any character can be included in a string. Lower-case characters in a string value are not converted to upper-case. Filenames A filename should be enclosed by apostrophes ('). Filenames can be up to 256 characters long. Length of input lines Input lines to the AUI can each contain up to 256 characters. Line continuation, line separator, blanks, and commas If the last non-blank character of a command or data line is a comma (,), then the command or ADINA R & D, Inc.
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data is continued on the next input line. The total length of an input line and all of its continuations can be up to 2000 characters. A slash (/) in an input line can be used to end a command or data input line; more commands or data can then be entered on the same input line. A blank, several blanks, characters, a comma, or a comma surrounded by blanks act as delimiters. Commands, parameter keynames and values must be separated by delimiters. Comments Comment lines can appear anywhere in the input and are identified by an asterisk (*) in column 1, e.g., * This is a comment line Parameter substitution You can define parameters as numeric expressions, and use the parameter values in later commands. This feature is useful when creating batch files used in structural optimization. For example: PARAMETER A `5 + 7` PARAMETER B `2*$A` PARAMETER C `3 + $A + 4*$B` BODY BLOCK DX1=$A DX2=$B DX3=$C
1.4 Messages Commands will often echo messages confirming their successful completion, or provide other information. Otherwise you may get error/warning messages with varying levels of severity: *** INPUT ERROR You have entered an unacceptable parameter value or data. The command will not execute with invalid input. *** WARNING The command has completed, but has detected a possible inconsistency which may have to be resolved. *** ALERT The command has completed, but has detected a definite modeling inconsistency which has to be resolved in order to create a valid model. *** ERROR The command has not completed. 1-10
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Sec. 1.5 File input/output
*** INTERNAL ERROR The program has determined some conflict in the database, normally indicating a software bug. You should contact ADINA R & D Inc. if you encounter such a message. In order to track down the source of the problem it would be most useful if the input responsible for this condition is made available to the support engineers. *** MEMORY OVERFLOW The command has not completed, due to the program running out of memory. Increse the memory allocation to the program
1.5 File input/output The AUI uses several files for handling I/O. Here is a brief description of some of them, together with a suggested filename extension convention: .in .idb .plo .pdb .ses .ps .dat .por .out
1.6 The AUI database The AUI uses an internal database to store and retrieve data used during program execution. The internal database is stored in main memory and, if main memory is not sufficient, a temporary database file is created to hold the excess data. The internal database can be saved in a disk file, called a permanent database file, so that it can be retrieved in a future run. Five commands are used to create, open and save databases. DATABASE NEW creates a new empty internal database. DATABASE OPEN initializes the internal database using a specified permanent database file. DATABASE SAVE saves the internal database to disk, allowing you to specify the name of the database file. DATABASE ATTACH causes the AUI to use the specified permanent database file as the internal database. DATABASE DETACH renames the internal database file as a permanent database file. All of these commands are described in Section 3.1. The permanent database file is similar to a text file used in a word processing program. Like the text file, the permanent database file resides on disk and can be retrieved by the program
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in a future run. The permanent database file can be saved on disk periodically during program execution to protect against loss of data due to computer failure. During each save operation, a different permanent database file can be selected so that several versions of the database are available for retrieval. (This is similar to saving several versions of a text file on disk when working with a word processing program.) For the differences between DATABASE OPEN and DATABASE ATTACH, see the command description for DATABASE ATTACH. For the differences between DATABASE SAVE and DATABASE DETACH, see the command description for DATABASE DETACH.
1.7 Listings Many AUI commands generate lists. For example, the ZONELIST command (see The AUI Command Reference Manual, Volume IV) lists the values of variables. You can also specify whether listings are to be sent to your terminal or to a disk file (see the FILELIST command). When the listings are sent to your terminal, you are prompted by --More--( %) after each screen of the listing. The number printed before the percent sign represents the percentage of the file that has been displayed so far. Responses to this prompt are as follows: D or d D or d Z or z S or s F or f B or b Q or q = .
Display another line of the listing. Display another screenful of the listing. Display i more lines. Display the next half-screen (a scroll) of the listing. Set the number of lines in the scroll to i and display the next scroll. Set the number of lines in each screen to i and display the next screen. Skip i lines and print a screenful of lines. Skip i screenfuls and print a screenful of lines. Skip back i screenfuls and print a screenful of lines. Stop the listing. Print the current line number in the listing. Repeat the last prompt response.
In these responses, represents an optional integer argument, defaulting to 1. If you are familiar with the UNIX operating system, you will recognize that the above options correspond closely to the options of the 'more' command.
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Sec. 1.8 Units
1.8 Units In model definition no particular unit system is assumed. Any consistent unit system may be adopted. Certain thermodynamic constants do, however, have a choice of temperature unit system (Celsius/Centigrade/Kelvin, Fahrenheit/Rankine).
1.9 Tips for writing batch files Increasing execution speed: The AUI contains features that are useful when you enter commands using the dialog boxes, but are not useful when you read commands from a batch file. These features are activated by default. You can deactivate the features to increase the speed at which batch files are processed, and to reduce the memory requirements of the AUI. The features are Undo/redo storage: Command CONTROL UNDO=-1 turns off storage for undo/redo information. Automatic model rebuilding: Command CONTROL AUTOMREBUILD=NO turns off automatic model rebuilding. Session file creation: Command FILESESSION NO turns off creation of the session file. Storage of session file information in the database: To turn off this feature, use the command CONTROL SESSIONSTORAGE=NO. Stopping after an error or memory overflow is detected: Command CONTROL ERRORACTION=SKIP activate a feature that AUI skips the remaining commands in a batch file after an error or memory overflow is detected. Summary: Use the following commands to perform all of the above actions: FILESESSION NO CONTROL UNDO=-1 AUTOMREBUILD=NO SESSIONSTORAGE=NO, ERRORACTION=SKIP
1.10 Related documentation At the time of printing of this manual, the following documents are available with the ADINA System:
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Installation Notes Describes the installation of the ADINA System on your computer. ADINA User Interface Command Reference Manual Volume I: ADINA Solids & Structures Model Definition, Report ARD 09-2, April 2009 Volume II: ADINA Heat Transfer Model Definition, Report ARD 09-3, April 2009 Volume III: ADINA CFD Model Definition, Report ARD 09-4, April 2009 Volume IV: Display Processing, Report ARD 09-5, April 2009 These documents describe the AUI command language. You use the AUI command language to write batch files for the AUI. ADINA User Interface Primer, Report ARD 09-6, April 2009 Tutorial for the ADINA User Interface, presenting a sequence of worked examples which progressively instruct you how to effectively use the AUI. Theory and Modeling Guide Volume I: ADINA Solids & Structures, Report ARD 09-7, April 2009 Volume II: ADINA Heat Transfer, Report ARD 09-8, April 2009 Volume III: ADINA CFD & FSI, Report ARD 09-9, April 2009 Provides a concise summary and guide for the theoretical basis of the analysis programs ADINA, ADINA-T, ADINA-F, ADINA-FSI and ADINA-TMC. The manuals also provide references to other publications which contain further information, but the detail contained in the manuals is usually sufficient for effective understanding and use of the programs. ADINA Verification Manual, Report ARD 09-10, April 2009 Presents solutions to problems which verify and demonstrate the usage of the ADINA System. Input files for these problems are distributed along with the ADINA System programs. TRANSOR for I-DEAS Users Guide, Report ARD 09-15, April 2009 Describes the interface between the ADINA System and I-deas®. ADINA System 8.6 Release Notes, April 2009 Provides a description of the new and modified features of the ADINA System 8.5. You will also find the following book useful: K. J. Bathe, Finite Element Procedures, Prentice Hall, Englewood Cliffs, NJ, 1996. Provides theoretical background to many of the solution techniques used in the ADINA System.
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Chapter 2 Quick index
Quick index
Chap. 2 Quick index
2.1 New commands, parameters and options In version 8.6, the following new commands, parameters and options were added to Volume I of the AUI Command Reference Manual. The commands are listed in page number order. Command
Parameter
Option/[Default]
Page
LOAD-CLOUD
3-19
LOAD-STL
3-20
NASTRAN-ADINA
DEFAULT
Description change
3-23
MASTER
TMC-MODEL
HEAT
5-6
TMC-CONTROL
GAMMA, TEMP-CUTOFF, CUTOFF, TEMP-RELAX, HEATRELAX
TMC-CONTROL
METHOD
TMC-ITERATION
TMCTOL, LINE-SEARCH
5-18 COMPOSITE
5-18 5-73
TOLERANCES ITERATION
5-76
PRINTNODES NODESETS
5-90
CONTACT-OUTPUTNODES
5-92
SAVENODES NODESETS
5-95
MONITOR
5-100
MONITOR-CONTROL
5-102
LINE SECTION
P1, P2
6-23
BODY-DSCADAP
6-76
BODY MID-SURFACE
6-119
MATERIAL MOHRCOULOMB
TEMPEFFECTS, ECC, ALPHA
7-38
MATERIAL NONLINEAR-ELASTIC
NU, MATRIX
7-50
MATERIAL PLASTICCYCLIC
7-65
MATERIAL SMA
TOLIL
New default
7-75
MATERIAL USERSUPPLIED
NSUBD
Description change
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Command
Parameter
Option/[Default]
Page
MATERIAL USERSUPPLIED
LENGTH3, LENGTH4, AUTOLEN, NONSYM, DENSITY
7-86
TMC-MATERIAL ISOTROPIC
DENSITY
7-92
TMC-MATERIAL ORTHOTROPIC
DENSITY
7-93
TMC-MATERIAL TEMPDEP-K
DENSITY
7-94
TMC-MATERIAL TEMPDEP-CISOTROPIC
DENSITY
7-95
TMC-MATERIAL TEMPDEP-CORTHOTROPIC
DENSITY
7-96
TMC-MATERIAL TEMPDEP-C-K
DENSITY
7-98
TMC-MATERIAL TIMEDEP-K
DENSITY
7-99
PLCYCL-ISOTROPIC BILINEAR
7-107
PLCYCL-ISOTROPIC MULTILINEAR
7-108
PLCYCL-ISOTROPIC EXPONENTIAL
7-109
PLCYCL-ISOTROPIC MEMORYEXPONENTIAL
7-110
PLCYCL-KINEMATIC ARMSTRONGFREDRICK
7-111
PLCYCL-RUPTURE AEPS
7-112
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Quick index
Chap. 2 Quick index
Command
Parameter
Option/[Default]
NODESET
ANGLE
9-10
BOUNDARIES
pore(i), temperature(i), beam-warp(i)
9-54
RIGIDLINK-NODE
Page
9-59
CRACKPROPAGATION NODES
Description change
9-91
J-VIRTUAL-SHIFT NODE
Description change
9-92
J-VIRTUAL-SHIFT ELEMENT
Description change
9-93
Option/[Default]
Page
Updates from 8.6.1 Command
Parameter
REBAR-LINE
NCOINCIDE
8-159
Updates from 8.6.2 Command
Parameter
Option/[Default]
Page
MASTER
MODEX
RESULTS
5-6
CYCLIC-CONTROL
BOUND-ELEMENT
7-228
CONTACT-CONTROL
Description change
7-239
CGROUP CONTACT2
Description change
7-243
CGROUP CONTACT3
Description change
7-264
EGROUP TRUSS
PRINT, SAVE, TBIRTH,TDEATH
Omission inserted
8-3
EGROUP TWODSOLID
PRINT, SAVE, TBIRTH,TDEATH
Omission inserted
8-6
EGROUP THREEDSOLID
PRINT, SAVE, TBIRTH,TDEATH
Omission inserted
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Quick index
Command
Parameter
Option/[Default]
Page
EGROUP BEAM
PRINT, SAVE, TBIRTH,TDEATH
Omission inserted
8-19
EGROUP ISOBEAM
PRINT, SAVE, TBIRTH,TDEATH
Omission inserted
8-24
EGROUP PLATE
PRINT, SAVE, TBIRTH,TDEATH
Omission inserted
8-29
EGROUP SHELL
PRINT, SAVE, TBIRTH,TDEATH
Omission inserted
8-33
EGROUP PIPE
PRINT, SAVE, TBIRTH,TDEATH
Omission inserted
8-40
EGROUP SPRING
PRINT, SAVE, TBIRTH,TDEATH
Omission inserted
8-45
EGROUP GENERAL
PRINT, SAVE,
Omission inserted
8-47
REBAR-LINE
NCOINCIDE
2-8
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2.2 Quick overview of commands The following is a quick overview of all AUI commands in Volume I of the AUI Reference Manual and their functions. The commands are presented in the order in which they appear. Chapter 3: Input/output Section 3.1: Database operations DATABASE NEW, creates a new database. DATABASE OPEN, creates a new database using the specified permanent database file. DATABASE WRITE, saves the current internal database as a permanent database file. DATABASE SAVE, saves the current internal database as a permanent database file. DATABASE ATTACH, allows access to the specified file as an AUI database file. DATABASE DETACH, creates a permanent database file by detaching a working copy of the database file. Section 3.2: Analysis data files ADINA, initiates model validation and/or creates an ADINA data file. REBUILD-MODEL, forces the AUI to rebuild the model. Section 3.3: External data LOADDXF, loads an AutoCAD® DXF file into the database. LOADIGES, loads an IGES file into the database. LOADSOLID, loads Parasolid® part into the database. LOAD-CLOUD, reads in a point cloud file (depicting the boundary of an object) and writes out an STL file. LOAD-STL, Loads an STL format file into the 2-10
AUI by creating a STL body. NASTRAN-ADINA, maps a NASTRAN® data file into the database. EXPORT NASTRAN, exports an ADINA model to a NASTRAN file. EXPORT UNIVERSAL, exports the mesh in ADINA-AUI to an I-DEAS® universal file format. Section 3.4: Auxiliary files READ, reads AUI input commands from the specified file. FILEREAD, controls the source of input commands to the AUI. FILESESSION, controls the generation and output of a session file. FILELIST, controls the format and output of listings. FILEECHO, controls the echoing of input commands. FILELOG, controls the output of log messages. COMMANDFILE, creates a file of commands to recreate the current model. RTOFILE, defines the contents of a run-timeoption file. Section 3.5: Program termination PAUSE, stops processing commands until a key is hit. END, terminates the program. Section 3.6: Auxiliary commands PARAMETER, defines a parameter that can be substituted in a later command.
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Chap. 2 Quick index
Chapter 4: Interface control and editing Section 4.1: Settings CONTROL, defines certain parameters that control program behavior.
tion analysis. ANALYSIS MODAL-PARTICIPATIONFACTORS, provides control data for a modal participation factor analysis. ANALYSIS MODAL-STRESSES, provides control data for modal stress calculations.
Section 4.2: Editing Section 5.3: Options UNDO, cancels the effects of previous commands. REDO, cancels the effects of previous UNDO commands. Chapter 5: Control data Section 5.1: General FEPROGRAM, specifies the finite element analysis program to be used to solve the problem. HEADING, specifies a title for the problem described by the model database. MASTER, defines the data controlling the execution of the analysis program ADINA. DOF-ACTIVE, used to identify the active degree of freedom (DOF) of reduced model. TMC-CONTROL, controls the performance of heat transfer analysis with ADINA. Section 5.2: Analysis details ANALYSIS DYNAMIC-DIRECTINTEGRATION, specifies time integration parameters for dynamic analysis. FREQUENCIES, specifies control data for a frequency solution. BUCKLING-LOADS, specifies control data for evaluating static buckling loads and corresponding mode shapes. ANALYSIS MODAL-TRANSIENT, provides control data for a mode superposi ADINA R & D, Inc.
KINEMATICS, defines the kinematic formulation. MASS-MATRIX, selects the type of mass matrix to be used in dynamic analysis. RAYLEIGH-DAMPING, specifies Rayleigh Damping coefficients. MODAL-DAMPING, defines modal damping factors to be used in mode superposition analysis. FAILURE MAXSTRESS, defines a failure criterion of type MAXSTRESS. FAILURE MAXSTRAIN, defines a failure criterion of type MAXSTRAIN. FAILURE TSAI-HILL, defines a failure criterion of type TSAI-HILL. FAILURE TSAI-WU, defines a failure criterion of type TSAI-WU. FAILURE HASHIN, defines a failure criterion of type HASHIN. FAILURE USERSUPPLIED, defines a failure criterion of type USERSUPPLIED. TEMPERATURE-REFERENCE, defines reference temperatures and temperature gradients for both initial conditions and thermal loads. Section 5.4: Solver details SOLVER ITERATIVE, defines control data for the iterative solution of the matrix system of equilibrium equations. PPROCESS, specifies the number of the processors used to split element groups into sub-groups. 2-11
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TMC-SOLVER ITERATIVE, defines control data for the iterative solution of the matrix system of equilibrium equations for heat transfer analysis. Section 5.5: Automatic control AUTOMATIC LOAD-DISPLACEMENT, defines parameters for an automatic load-displacement control (LDC) procedure. AUTOMATIC TIME-STEPPING, defines parameters controlling the automatic time-stepping procedure. AUTOMATIC TOTAL-LOAD-APPLICATION, controls the total-load-application (TLA) procedure. Section 5.6: Time dependence TIMESTEP, defines a timestep sequence which controls the time/loadstep incrementation during analysis. TIMEFUNCTION, defines a timefunction, which may be referenced, e.g., by an applied load. Section 5.7: Iteration ITERATION, selects the equilibrium iteration scheme to be employed for a nonlinear analysis. STIFFNESS-STEPS, controls the output timesteps at which the effective stiffness matrix is reformed by the analysis program. EQUILIBRIUM-STEPS, controls the output timesteps at which equilibrium iterations are performed. TMC-ITERATION, selects the equilibrium iteration scheme to be employed for a heat transfer analysis.
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Section 5.8: Tolerances TOLERANCES GEOMETRIC, specifies certain geometric tolerances. TOLERANCES ITERATION, specifies the convergence criteria and corresponding tolerances controlling the equilibrium iteration scheme. Section 5.9: Analysis output PRINTOUT, controls the amount of output printed. PRINT-STEPS, controls the output timesteps at which results are printed. PORTHOLE, controls the saving of input data and solution results on the porthole file. NODESAVE-STEPS, controls the output timesteps at which nodal results are saved in the porthole file. ELEMSAVE-STEPS, controls the output timesteps at which element results are saved on the porthole file. PRINTNODES, selects nodes (defined by “blocks” or geometry entities) for which solution results shall be printed. CONTACT-OUTPUT-NODES, select nodes for output of contact results. REACTION-NODES, selects nodes for printing reaction forces. SAVENODES, selects nodes (defined by “blocks” or geometry entities) for which the solution results shall be saved in the porthole file. DISK-STORAGE, indicates file storage and input/output control. Section 5.10: Solution monitoring MONITOR, defines solution monitors to track the change of variables during simulation.
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MONITOR-CONTROL, control settings for the solution monitoring feature. Chapter 6: Geometry definition Section 6.1: Coordinate systems SYSTEM, defines a local coordinate system.
of another geometry line. SPLIT-LINE, creates two geometry lines of type SECTION by “splitting” a given line into two parts connected at some point on the given line. LNTHICKNESS, defines line thicknesses (e.g., for defining axisymmetric shell thicknesses).
Section 6.2: Points Section 6.4: Surfaces COORDINATES POINT, defines geometry point coordinates. Section 6.3: Lines LINE STRAIGHT, defines a straight geometry line between two geometry points. LINE ARC, defines a geometry line as a circular arc, or as an arc with varying radius. LINE CIRCLE, defines a circle geometry line. LINE CURVILINEAR, defines a geometry line as a linearly interpolated curve in a given local coordinate system. KNOTS, defines a vector of “knot” values for NURBS definition. LINE POLYLINE, defines a geometry line as a polyline, i.e., a curve controlled by a series of geometry points. LINE SECTION, defines a geometry line to be part of another geometry line. LINE COMBINED, defines a geometry line as a combina tion of other geometry lines. LINE REVOLVED, defines a geometry line (a circular arc) by rotating a geometry point about an axis. LINE EXTRUDED, defines a geometry line by displacing a geometry point in a given direction. LINE TRANSFORMED, defines a geometry line to be a geometrical transformation ADINA R & D, Inc.
SURFACE PATCH, defines a geometry surface to be bounded by edges which are specified geometry lines. SURFACE VERTEX, defines a geometry surface to be bounded by edges which are specified by their end geometry points - the vertices of the surface. SURFACE GRID, defines a geometry surface as a grid (array) of geometry points, which control the shape of the surface. SURFACE EXTRUDED, defines a geometry surface by displacing a geometry line in a given direction. SURFACE REVOLVED, defines a geometry surface by rotating a geometry line about some axis. SURFACE TRANSFORMED, defines a geometry surface via a transformation of another surface. SFTHICKNESS, defines surface thicknesses. CHECK-SURFACES, checks geometry surface connections looking for two adjoining surfaces which are oppositely oriented, i.e., with opposite surface normals. Section 6.5: Volumes VOLUME PATCH, defines a geometry volume to be bounded by faces which are specified geometry surfaces. 2-13
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VOLUME VERTEX, defines a geometry volume in terms of the vertices. VOLUME REVOLVED, defines a geometry volume by rotating a geometry surface about some axis. VOLUME EXTRUDED, defines a geometry volume by displacing a geometry surface in a given direction. VOLUME SWEEP, defines one or more geometry volumes by sweeping one or more geometry surfaces along a line. VOLUME TRANSFORMED, defines a geometry volume to be a geometrical transformation of another volume. Section 6.6: Solid models BODY SURFACES, defines a solid body via a collection of oriented surfaces. BODY VOLUMES, defines a solid body via a collection of volumes. FACE-THICKNESS, defines solid geometry face thicknesses. FACELINK, establishes a link, for meshing purpose, between two faces of distinct solid models, or between a face of a solid model and a surface. SPLIT-EDGE, splits an edge of a body into two edges by giving a parameter along the edge. SPLIT-FACE, splits a face of a body into two faces by giving two points on the face. BODY-DISCREP, creates a “discrete boundary represenation” for a given body. BODY-DEFEATURE, removes “small” features from the “discrete boundary represenation” of a given body. BODY-CLEANUP, removes “short”body edges and/or “thin” body faces from the AUI represenation” of a given body. BODY-RESTORE, restores the AUI topological representation of the body
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corresponding to its state before commands such as BODY-CLEANUP, REM-EDGE or REM-FACE are executed. BODY-DSCADAP, adapts (according to the mesh densities set prior) the surface triangles that make up the geometry of an STL body. Section 6.7: Spatial functions LINE-FUNCTION, describes the variation of a quantity along a line. SURFACE-FUNCTION, describes the variation of a quantity over a surface. VOLUME-FUNCTION, describes the variation of a quantity within a volume. Section 6.8: Transformations TRANSFORMATION COMBINED, defines a general transformation as an ordered sequence of existing transfor mations. TRANSFORMATION DIRECT, defines a general 3-D transformation by directly specifying the transformation matrix. TRANSFORMATION POINTS, defines a rigid-body 3-D transformation by the specification of 6 geometry points, 3 “initial” points and 3 “target”points. TRANSFORMATION REFLECTION, defines a 3-D reflection (mirror) transfor mation. TRANSFORMATION ROTATION, defines a 3-D rotation transformation. TRANSFORMATION SCALE, defines a 3D scaling transformation. TRANSFORMATION TRANSLATION, defines a 3-D translation transformation. TRANSFORMATION INVERSE, defines a 3-D geometry transformation as the inverse of another transformation.
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Section 6.9: Miscellaneous DOMAIN, defines a geometry “domain”, which is a collection of geometry entities. MEASURE, determines the distance between two points or the length of an edge or a line. GET-EDGE-FACES, lists the body faces connected to a body edge. GET-EDGE-POINTS, lists the AUI points bounding a body edge. GET-FACE-EDGES, lists the body edges bounding a body face. REM-EDGE, removes a body edge by collapsing one end point onto the other. REM-FACE, removes a body face by collapsing one bounding edge onto the other. Section 6.10: ADINA - M BODY BLEND, modifies specified edges of a body to have “a radius” blend. BODY BLOCK, defines a solid geometry or “brick”shape. BODY CHAMFER, applies chamfers to edges of a solid body. BODY CONE, defines a cone shape solid geometry. BODY CYLINDER, defines a cylinder shape solid geometry. BODY HOLLOW, hollows a solid geometry with thickness THICKNESS. BODY INTERSECT, modifies an existing solid body by taking the intersection of it with other, overlapping body. BODY LOFTED, creates a sheet body by lofting through a set of lines or edges and creates a solid body by lofting through a set of surfaces, faces, and sheet bodies.
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BODY MERGE, modifies an existing solid body by joining it with a set of other solid bodies. BODY MID-SURFACE, creates sheet bodies from a thin-walled solid body. BODY OPTION, provides the options for ADINA-M bodies. BODY PARTITION, partition body with a set of faces of the body. BODY PIPE, defines a pipe shape solid geometry. BODY PRISM, defines a prismatic shape solid geometry. BODY PROJECT, projects lines into a face of the body. BODY REVOLVED, creates a body by revolving face of existing body around an axis. BODY SECTION, partition solid body using sheets. BODY SEW, sews a set of sheet bodies into sewn bodies. BODY SHEET, defines a sheet body by a set of geometry lines. BODY SPHERE, defines a sphere shape solid body. BODY SUBTRACT, modifies an existing solid body by removing from it a set of other solid, overlapping bodies. BODY SWEEP, creates a body by sweeping existing face of a body in a given direction or along a line. BODY TORUS, defines a torus shape solid geometry. BODY TRANSFORMED, defines a solid geometry by copying or moving an existing ParasolidÒ body. SHEET PLANE, defines a planar sheet used for partition of bodies. VOLUME BODY, converts a body into a geometrical volume. SURFACE FACE, converts a face of a body into a geometric surface.
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Chapter 7: Model definition Section 7.1: Material models MATERIAL ANAND, defines an Anand material. MATERIAL ARRUDA-BOYCE, defines an Arruda-Boyce material model. MATERIAL CAM-CLAY, defines a nonlinear Cam-Clay material model. MATERIAL CONCRETE, defines a nonlinear concrete material model. MATERIAL CREEP, defines a nonlinear creep material. MATERIALCREEP-IRRADIATION, defines an irradiation creep material. MATERIAL CREEP-VARIABLE, defines a nonlinear creep material with variable creep coefficients. MATERIAL CURVE-DESCRIPTION, defines a nonlinear geological material, with the option of tension cut-off or cracking. MATERIAL DRUCKER-PRAGER, defines a nonlinear Drucker-Prager material model with a hardening cap and tension cut-off. MATERIAL ELASTIC, defines an isotropic linear elastic material. MATERIAL FLUID, defines a linear fluid material. MATERIAL GASKET, defines a gasket material model. MATERIAL GURSON-PLASTIC, defines a nonlinear Gurson plastic material. MATERIAL HYPERELASTIC, defines a hyperelastic material, which is incompressible nonlinear elastic, for rubberlike materials. MATERIAL HYPER-FOAM, defines a hyper-foam material model.
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MATERIAL ILYUSHIN, defines a nonlinear elastic-plastic material with the Ilyushin yield condition and isotropic hardening. MATERIAL MOHR-COULOMB, defines a nonlinear Mohr-Coulomb material. MATERIAL MOONEY-RIVLIN, defines a Mooney-Rivlin material, which is incompressible nonlinear elastic, for rubber materials. MATERIAL MROZ-BILINEAR, defines an elastic-plastic material with Mroz yield criteria and bilinear hardening. MATERIAL MULTILINEAR-PLASTICCREEP, defines a nonlinear thermo-elasticplastic-multilinear and creep material, with von Mises yield condition and isotropic, kinematic or mixed strain hardening. MATERIAL MULTILINEAR-PLASTICCREEP-VARIABLE, defines a nonlinear thermo-elastic-plastic-multilinear creep material model with variable creep coefficients. MATERIAL NONLINEAR-ELASTIC, defines a nonlinear elastic material. MATERIAL OGDEN, defines an Ogden material, which is incompressible nonlinear elastic, for rubber materials. MATERIAL ORTHOTROPIC, defines an orthotropic linear elastic material. MATERIAL PLASTIC-BILINEAR, defines a bilinear elastic-plastic material model with von Mises yield condition. MATERIAL PLASTIC-CREEP, defines a nonlinear thermo-elastic-plastic and creep material, with von Mises yield condition and isotropic or kinematic strain hardening. MATERIAL PLASTIC-CREEP-VARIABLE, defines a nonlinear thermo-elasticplastic creep material model with variable creep coefficients.
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MATERIAL PLASTIC-CYCLIC, defines a plastic-cyclic material. MATERIAL PLASTIC-MULTILINEAR, defines a multilinear elastic-plastic material model with von Mises yield condition. MATERIAL PLASTIC-ORTHOTROPIC, defines a nonlinear orthotropic plastic material. MATERIAL SMA, defines a shape-memory alloy material. MATERIAL SUSSMAN-BATHE, defines a Sussman-Bathe material model. MATERIAL THERMO-ISOTROPIC, defines a nonlinear isotropic thermo-elastic material. MATERIAL THERMO-ORTHOTROPIC, defines a nonlinear orthotropic thermo-elastic material. MATERIAL THERMO-PLASTIC, defines a nonlinear thermo-plastic material. MATERIAL USER-SUPPLIED, defines a user-supplied material for use with ADINA, with options for piezoelectric or consolidation analyses. MATERIAL VISCOELASTIC, defines a time and teperature dependent viscoelastic material model. TMC-MATERIAL ISOTROPIC, defines a constant isotropic conductivity and a constant specific heat material for TMC analysis. TMC-MATERIAL ORTHOTROPIC, defines an orthotropic conductivity and constant specific heat material for TMC analysis. TMC-MATERIAL TEMPDEP-K, defines a material with temperature dependent conductivity and constant specific heat for TMC analysis. TMC-MATERIALTEMPDEP-C-ISOTROPIC, defines a material with temperature dependent specific heat and constant
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isotropic conductivity for TMC analysis. TMC-MATERIALTEMPDEP-CORTHOTROPIC, defines a material with constant, orthotropic, conductivity and temperature dependent specific heat for TMC analysis. TMC-MATERIAL TEMPDEP-C-K, defines a material with temperature dependent specific heat and conductivity for TMC analysis. TMC-MATERIALTIMEDEP-K, defines a material with time dependent conductivity and constant specific heat for TMC analysis. CURVE-FITTING, defines a fitting curve for hyperelastic material models. VISCOELASTIC CONSTANTS, defines viscoelastic contants for a viscoelastic material model. PHI-MODEL-COMPLETION, contrrols parameters for phi model completion phase of potential-based fluid elements. PLCYCL-ISOTROPIC BILINEAR, sets up a PLCYCL-ISOTROPIC definition of type bilinear. PLCYCL-ISOTROPIC MULTILINEAR, sets up a PLCYCL-ISOTROPIC definition of type multilinear. PLCYCL-ISOTROPIC EXPONENTIAL, sets up a PLCYCL-ISOTROPIC defini tion of type exponential. PLCYCL-ISOTROPIC MEMORY-EXPONENTIAL, sets up a PLCYCL-ISOTROPIC definition of type memory-exponential. PLCYCL-KINEMATICARMSTRONGFREDRICK, sets up a PLCYCL-KINEMATIC definition of type Armstrong-Fredrick. PLCYCL-RUPTURE AEPS, sets up a PLCYCL-RUPTURE definition of type AEPS (accumulated effective plastic strain). RUBBER-TABLE MOONEY-RIVLIN, defines a rubber-table data set of type Mooney-Rivlin.
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RUBBER-TABLE OGDEN, defines a rubber-table data set of type Ogden. RUBBER-TABLE ARRUDA-BOYCE, defines a rubber-table data set of type Arruda-Boyce. RUBBER-TABLE HYPER-FOAM, defines a rubber-table data set of type hyperfoam. RUBBER-TABLE SUSSMAN-BATHE defines a rubber-table data set of type Sussman-Bathe. RUBBER-TABLE TRS, defines a rubber-table data set of type TRS (thermorheologically simple). RUBBER-MULLINS OGDEN-ROXBURGH, defines a data set of type rubberMullins, subtype Ogden-Roxburgh. RUBBER-VISCOELASTIC HOLZAPFEL, defines a data set of type rubberviscoelastic, subtype Holzapfel. RUBBER-ORTHOTROPIC HOLZAPFEL, defines a data set of type rubberorthotropic, subtype Holzapfel. COEFFICIENTS-TABLE, defines an effective stress vs. creep coeffients table. CREEP-COEFFICIENTS LUBBY2, defines the dependency of creep law coefficients on temperature. CREEP-COEFFICIENTS MULTILINEAR, defines the temperature and dependence of stress creep coefficients. CREEP-COEFFICIENTS TEMPERATUREONLY, defines the dependency of creep law coefficients on temperature. CREEP-COEFFICIENTS USER-SUPPLIED, Defines a user supplied creep coefficient dependence function. CURVATURE-MOMENT, defines a curvature vs. moment curve. FTABLE, defines a modulus vs. decay coefficient table for MATERIAL VISCOELASTIC.
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FORCE-STRAIN, defines a force vs. strain curve. IRRADIATION-CREEP-TABLE, defines an irradiation creep table. MOMENT-CURVATURE-FORCE, defines a moment-curvature-force property for BEAM elements. MOMENT-TWIST-FORCE, defines a moment-twist-force property for BEAM elements. NEUTRON-DOSE, defines a neutron fluence. NEUTRON-TABLE, defines a neutron fluence table. PORE-FLUID-PROPERTY, defines properties of a pore fluid. PROPERTY NONLINEAR-C, defines a nonlinear relationship between damping and velocity. PROPERTY NONLINEAR-K, defines a nonlinear relationship between force and relative displacement. PROPERTY NONLINEAR-M, defines a time-dependent mass property. PROPERTYSET, defines stiffness, mass, damping, and stress transformation properties for SPRING elements. RIGIDITY-MOMENT-CURVATURE NONLINEAR-ELASTIC, defines a nonlinear-elastic rigidity property. RIGIDITY-MOMENT-CURVATURE PLASTIC-MULTILINEAR, defines a plasticmultilinear rigidity property. RUPTURE MULTILINEAR, defines a rupture criterion in terms of multilinear temperature-dependent curves. RUPTURE THREE-PARAMETER, defines a three-parameter law rupture criterion. RUPTURE-CURVE, defines a rupture-strain vs. stress curve. SCURVE, defines a stress-strain curve which can be referenced by a material model.
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SSCURVE, defines a stress-strain1-2 curve which can be referenced by a material model. LCURVE, defines a loading-unloading curve which can be referenced by the gasket material model. STRAINRATE-FIT, defines a strainrate-fit for the curve fitting of strainrate material parameters. TWIST-MOMENT, defines a twist vs. moment curve. Section 7.2: Cross-sections/layers CROSS-SECTION BOX, defines a box cross-section. CROSS-SECTION I, defines an I-beam cross-section. CROSS-SECTION L, defines an L-beam cross-section. CROSS-SECTION PIPE, defines a pipe cross-section. CROSS-SECTION RECTANGULAR, defines a rectangular cross-section. CROSS-SECTION U, defines a U-beam cross-section. CROSS-SECTION PROPERTIES, defines a general cross-section in terms of principal moments of inertia and areas. LAYER, defines the control parameters of each surface layer (for multi-layer shell elements). PLY-DATA, defines the layer thickness for a fiber-matrix composite. Section 7.3: Element properties LINE-ELEMDATA TRUSS, assigns data for TRUSS elements to geometry lines. EDGE-ELEMDATA TRUSS, assigns data for TRUSS elements on edges. SURF-ELEMDATA TWODSOLID, assigns data for TWODSOLID elements to geometry surfaces. ADINA R & D, Inc.
FACE-ELEMDATA TWODSOLID, assigns data for TWODSOLID elements on faces. VOL-ELEMDATA THREEDSOLID, assigns data for THREEDSOLIDelements in geometry volumes. BODY-ELEMDATA THREEDSOLID, assigns data for THREEDSOLID elements in bodies. LINE-ELEMDATA BEAM , assigns data for BEAM elements to geometry lines. EDGE-ELEMDATA BEAM, assigns data for BEAM elements on edges. LINE-ELEMDATA ISOBEAM, assigns data for ISOBEAM elements to geometry lines. EDGE-ELEMDATA ISOBEAM, assigns data for ISOBEAM elements on edges. SURF-ELEMDATA PLATE, assigns data for PLATE elements to geometry surfaces. FACE-ELEMDATA PLATE, assigns data for PLATE elements on faces. SURF-ELEMDATA SHELL, assigns data for SHELL elements to geometry surfaces. FACE-ELEMDATA SHELL, assigns data for SHELL elements on faces. ELAYER, assigns material to individual element on diffferent layers for shell element. LINE-ELEMDATA PIPE, assigns data for PIPE elements to geometry lines. EDGE-ELEMDATA PIPE, assigns data for PIPE elements on edges. LINE-ELEMDATA GENERAL, assigns data for GENERAL elements on lines. EDGE-ELEMDATA GENERAL, assigns data for GENERAL elements on edges. SURF-ELEMDATA GENERAL, assigns data for GENERAL elements on surfaces. FACE-ELEMDATA GENERAL, assigns data for GENERAL elements on faces. VOL-ELEMDATA GENERAL, assigns data for GENERAL elements in volumes.
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BODY-ELEMDATA GENERAL, assigns data for GENERAL elements in bodies. SURF-ELEMDATA FLUID2, assigns data for FLUID2 elements on surfaces. FACE-ELEMDATA FLUID2, assigns data for FLUID2 elements on faces. VOL-ELEMDATA FLUID3, assigns data for FLUID3 elements in volumes. BODY-ELEMDATA FLUID3, assigns data for FLUID3 elements in bodies. MATRIX STIFFNESS, defines a stiffness matrix for general elements. MATRIX MASS, defines a mass matrix for general elements. MATRIX DAMPING, defines a damping matrix for general elements. MATRIX STRESS, defines a stress matrix for general elements. MATRIXSET, defines the matrixset for the current GENERAL element group. MATRIX USER-SUPPLIED, defines the element stiffness matrix in a general element group to be provided by subroutine CUSERG. MASSES, assigns concentrated masses to the nodes on a set of geometry entities. DAMPERS, assigns concentrated dampers to the nodes on a set of geometry entities. Section 7.4: Substructure and cyclic symmetry SUBSTRUCTURE, defines substructures. REUSE, connects a substructure to the main structure. CYCLIC-CONTROL, specifies parameters that control cyclic symmetry analysis. CYCLICLOADS, cyclic symmetric part of loading. CYCLICBOUNDARY, defines cyclic symmetric boundarie based on points, lines, surfaces or nodes.
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CYCLICBOUNDARY TWO-D, defines cyclic symmetric boundaries based on lines or edges. CYCLICBOUNDARY THREE-D, defines cyclic symmetric boundaries based on surfaces or faces. AXIS-ROTATION, defines a rotational axis which can be referenced other commands. EG-SUBSTRUCTURE, creates substructures in terms of existing element groups. Section 7.5: Contact conditions ANALYTICAL-RIGID-TARGET, defines parameters for analytical rigid target analysis. CONTACT-CONTROL, specifies parameters controlling the behavior of the algorithms used in modeling contact. CGROUP CONTACT2, defines a contact group consisting of 2-D or axisymmetric contact surfaces. CGROUP CONTACT3, defines a contact group consisting of 3-D contact surfaces. CONTACTBODY, defines a contact body i.e. a geometry surface in 2D or a geometry volume in 3D. CONTACTSURFACE, defines a contact surface, i.e., a set of geometry boundaries which are expected to be in contact either initially or during analysis with another similarly defined contact surface. CONTACTPOINT, defines a contact point, i.e., a set of geometry points (in 2-D or 3D analysis) which are expected to be in contact. DRAWBEAD, defines a drawbead for metal forming analysis. COULOMB-FRICTION, specifies variable Coulomb friction coefficient.
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USER-FRICTION, specifies the parameters used in the calculation of user-supplied friction for the current contact group. CS-OFFSET, specifies offset distances for individual contact-surfaces. CONTACTPAIR, defines a contact pair, i.e., two contact surfaces which are either initially in contact or are anticipated to come into contact during analysis. CONTACT-3-SEARCH, creates 3D contact surfaces and contact pairs between two bodies within the given distance range. Section 7.6: Fracture mechanics FRACTURE, defines controlling data for analysis of fracture mechanics problems. CRACK-GROWTH, specifies the parameters that govern control of the growth of a propagating crack. CRACK-PROPAGATION, defines the initial crack front position or the virtual/actual crack propagation path. J-LINE POINT, defines a line contour via a circle centered at a point. J-LINE RING, defines a line contour via a ring of elements. J-VIRTUAL-SHIFT POINT, defines a virtual material shift via a circle centered at a point. J-VIRTUAL-SHIFT LINE, defines a virtual material shift via the nodes lying on any of a given set of lines. J-VIRTUAL-SHIFT SURFACE, defines a virtual material shift via the nodes lying on any of a given set of surfaces. J-VIRTUAL-SHIFT RING, defines a virtual material shift via a number of rings of elements about the crack front. R-CURVE, defines a resistance curve set which can be used in a crack growth analysis.
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SINGULAR, defines a set of “singular” nodes-vertex nodes whose adjacent non-vertex nodes are moved to the “1/4 point”, giving a singularity at the required nodes. USER-RUPTURE, specifies user-defined rupture data. Section 7.7: Boundary conditions RIGIDLINK, specifies rigid links between geometry entities. CONSTRAINT, specifies a constraint equation which expresses a slave (dependent) degree of freedom as a linear combination of a set of master (independent) degrees of freedom. CONSTRAINT-MS, similar to the CONSTRAINT command, but also allows the specification of multiple slave entities for a single master entity. CONSTRAINT-G, defines generalized constraint equations for ADINA. FIXITY, defines a fixity boundary condition. FIXBOUNDARY, assigns fixity conditions to a set of geometry entities. ZOOM-BOUNDARY, specifies the boundary of a zoom model that is inside (internal to) the coarse model. ENDRELEASE, defines an “endrelease” condition for elements of type BEAM. FSBOUNDARY, defines a fluid-structureinteraction boundary. FSBOUNDARY TWO-D, defines a fluidstructure-interaction boundary for 2D analysis. FSBOUNDARY THREE-D, defines a fluidstructure-interaction boundary for 3D analysis.
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POTENTIAL-INTERFACE, defines a freesurface potential-interface for ADINA. POTENTIAL-INTERFACE INFINITE, defines an infinite potential-interface for ADINA. BOUNDARY-SURFACE SURFACETENSION, defines a surface tension boundary for ADINA. OVALIZATION-CONSTRAINT POINT, enforces the zero-slope-of-skin in the longitudinal direction for pipe element nodes. FREESURFACE, defines a free surface on the boundary lines (2-D) or surface(3-D) for potential-based problems. BCELL, defines a boundary cell using a 4node or 3-node cell. Section 7.8: Loading LOAD CENTRIFUGAL, defines a centrifugal load. LOAD CONTACT-SLIP, defines a contactslip load. LOAD CONVECTION, defines a convec tion load. LOAD DISPLACEMENT, defines a displacement load. LOAD ELECTROMAGNETIC, defines an electromagnetic load. LOAD FORCE, defines a force load. LOAD LINE, defines a line load, i.e., a distributed load in terms of force/unit length. LOAD MASS-PROPORTIONAL, defines a mass proportional load. LOAD MOMENT, defines a moment load. LOAD NODAL-PHIFLUX, defines a nodalphiflux load. LOAD PHIFLUX, defines a phiflux load. LOAD PIPE-INTERNAL-PRESSURE, defines a pipe-internal-pressure load. LOAD POREFLOW, defines a poreflow load. 2-22
LOAD PORE-PRESSURE, defines a porepressure load. LOAD PRESSURE, defines a pressure load. LOAD RADIATION, defines a radiation load. LOAD TEMPERATURE, defines a temperature load. LOAD TGRADIENT, defines a temperature gradient load to specify the temperature gradient in the thickness direction of a surface (when applied to shell elements). CPROP, defines conveciton properties for convection loading. RPROP, defines radiaiton properties for radiation loading. LOAD-CASE, used in a linear static analysis to identify the current load case. LCOMBINATION, defines a new load case as a linear combination of previously defined load cases. APPLY-LOAD, specifies loads applied to model geometry. LOAD-PENETRATION, controls transfer of applied pressure loads to neighboring elements when an element “dies”. Section 7.9: Initial conditions INITIAL-CONDITION, defines an initial condition. SET-INITCONDITION, assigns initial conditions to a set of geometry entities. STRAIN-FIELD, defines an initial strain field. IMPERFECTION POINTS, specifies imperfections at points based on buckling mode shapes which have been previously calculated. IMPERFECTION SHAPE, used for initial shape calculations based on previously calculated nodal displacements. INITIAL-MAPPING, loads an initial condition mapping file and interpolates variable values at nodes.
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THERMAL-MAPPING, interpolates nodal temperatures and gradients from a given temperature field contained in a mapping file. Section 7.10: Systems SKEWSYSTEMS CYLINDRICAL, defines a “skew” Cartesian coordinate system in terms of a cylinder origin and axis direction. SKEWSYSTEMS EULERANGLES, defines a “skew” Cartesian coordinate system in terms of Euler angles. SKEWSYSTEMS NORMAL, defines a “skew” Cartesian coordinate system to be such that one of its directions is normal to a given line or surface. SKEWSYSTEMS POINTS, defines a “skew” Cartesian coordinat system in terms of geometry points. SKEWSYSTEMS SPHERICAL, defines a “skew” Cartesian coordinate system in terms of a sphere origin. SKEWSYSTEMS VECTORS, defines a “skew” Cartesian coordinate system in terms of direction vectors. DOF-SYSTEMS POINTS, assigns skew coordinate systems to geometry points. DOF-SYSTEMS LINES, assigns skew coordinate systems to geometry lines. DOF-SYSTEMS EDGES, assigns skew coordinate systems to solid geometry edges. DOF-SYSTEMS SURFACES, assigns skew coordinate systems to geometry surfaces. DOF-SYSTEMS FACES, assigns skew coordinate systems to solid geometry faces. DOF-SYSTEMS VOLUMES, assigns skew coordinate systems to geometry volumes.
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DOF-SYSTEMS BODIES, assigns skew coordinate systems to solid geometry bodies. DOF-SYSTEMS NODESETS, assigns skew coordinate systems to node sets. SHELLNODESDOF, specifies the number of degrees of freedom for shell midsurface nodes associated with a set of geometry entities. AXES CONSTANT, defines an “axessystem” in terms of constant direction vectors. AXES LINE1, defines an “axes-system” via a geometry line. AXES LINE2, defines an “axes-system” via two geometry lines. AXES NODES, defines an “axes-system” via three nodes. AXES POINT2, defines an “axes-system” via two geometry points. AXES POINT3, defines an “axes-system” via three geometry points. AXES POINT-LINE, defines an “axessystem” via a geometry line and a geometry point. AXES SURFACE, defines an “axes-system” via a geometry surface. AXES EDGE, defines an “axes-system” via a geometry edge. AXES FACE, defines an “axes-system” via a geometry face. AXES CYLINDRICAL, defines a cylindrical axes system in terms of an origin and an axis direction. AXES SPHERICAL, defines a spherical axes system in terms of an origin. SET-AXES-MATERIAL, assigns material axes-system, defined by command AXES, to a set of geometry entities. SET-AXES-STRAIN, assigns initial-strain axes-systems, defined by the command AXES, to a set of geometry entities.
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Chap. 2 Quick index
Chapter 8: Finite element representation
Section 8.2: Mesh generation
Section 8.1: Element groups
TRANSITION-ELEMENT, converts a set of shell elements along an edge of a face/ surface into shell transition elements. BLAYER, generates boundary layers on specified body faces. COPY-TRIANGULATION, copies face triangulation for later use by meshing commands like GFACE or GBODY. DELETE-TRIANGULATION, deletes face triangulations created by the COPYTRIANGULATION command. LIST-TRIANGULATION, lists all faces (body and face labels) which have triangulation created by the COPYTRIANGULATION command. SUBDIVIDE DEFAULT, defines default mesh subdivision data. SUBDIVIDE MODEL, assigns mesh subdivision data to the entire current model geometry. SUBDIVIDE POINT, assigns mesh subdivision data to geometry points. SUBDIVIDE LINE, assigns mesh subdivision data to geometry lines. SUBDIVIDE SURFACE, assigns mesh subdivision data to geometry surfaces. SUBDIVIDE VOLUME, assigns mesh subdivision data to geometry volumes. SUBDIVIDE EDGE, assigns mesh subdivision data to edges of a solid geometry body. SUBDIVIDE FACE, assigns mesh subdivision data to faces of a solid geometry body. SUBDIVIDE BODY, assigns mesh subdivision data to solid geometry bodies. POINT-SIZE, specifies the element size at geometr points. SIZE-FUNCTION BOUNDS, defines a mesh size function using the vertices of the model bounding box.
EGROUP TRUSS, defines an element group consisting of truss elements. EGROUP TWODSOLID, defines an element group consisting of planar or axisymmetric elements. EGROUP THREEDSOLID, defines an element group consisting of three-dimensional solid elements. EGROUP BEAM, defines an element group consisting of Hermitian beam elements. EGROUP ISOBEAM, defines an element group consisting of isoparametric beam elements. EGROUP PLATE, defines an element group consisting of plate elements. EGROUP SHELL, defines an element group consisting of shell elements. EGROUP PIPE, defines an element group consisting of pipe elements. EGROUP SPRING, defines an element group consisting of spring elements. EGROUP GENERAL, defines an element group consisting of linear general elements. EGROUP FLUID2, defines an element group consisting of planar or axisymmetric fluid elements. EGROUP FLUID3, defines an element group consisting of 3-D fluid elements. EGCONTROL, specifies general control data for an element group. BOLT-OPTIONS, defines bolt options for use with the EGROUP BEAM command. BOLT-TABLE, specifies the bolt loading sequence.
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Chap. 2 Quick index
SIZE-FUNCTION HEX, defines a mesh size function using the vertices of an input box. SIZE-FUNCTION POINT, defines a mesh size function via a point source. SIZE-FUNCTION AXIS, defines a mesh size function via a line source. SIZE-FUNCTION PLANE, defines a mesh size function via a planar source. SIZE-FUNCTION COMBINED, defines a mesh size function as a combination of others. SIZE-LOCATIONS, specifies mesh size at certain locations (other than geometry points). NLTABLE, creates a table with specification of number of layers across thin sections. GPOINT, creates a node at a point with the same coordinates. GLINE, creates elements along a set of geometry lines. GSURFACE, creates elements on a set of geometry surfaces. GVOLUME, creates elements on a set of geometry volumes. GEDGE, creates elements on a set of solid geometry edges. GFACE, creates elements on a set of solid geometry faces. GBODY, creates elements for a solid geometry body. GBCELL, creates 3D elements from boundary cells. GHEXA, generates brick element dominant free-form meshes for a given body. GADAPT, deletes and remeshes a finite element mesh. ELDELETE, deletes elements generated on specific geometry for a given element group. COPY-MESH-BODY, copies a mesh from one body to another body via affine transformation.
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CSURFACE, creates a set of contact elements on a contact surface. CSDELETE, deletes contact elements generated on specific geometry for a given contact group. GLUEMESH, glues two dissimilar meshes together. Section 8.3: Elements TRUSS-POINTS, defines axisymmetric truss elements at geometry points. SPRING POINTS, defines spring elements at points. SPRING LINES, defines spring elements between geometry lines. REBAR- LINE, defines a rebar using lines. The rebar defined is then referenced in the EGROUP TRUSS command to model rebar elements. TRUSS-LINE, defines TRUSS elements between lines. ELTHICKNESS, defines shell element thickness. Chapter 9: Direte finite element data input Section 9.1: Nodal data COORDINATES NODE, defines coordinates for (current substructure) nodes. SKEWSYSTEMS NODES, defines a “skew” Cartesian coordinate system in terms of nodes. DOF-SYSTEM NODES, assigns skew coordinate systems to nodes in the current substructure. MASSES NODES, assigns concentrated masses to nodes. DAMPERS NODES, assigns concentrated dampers to nodes. SHELLNODESDOF NODES, specifies the number of degrees of freedom for shell midsurface nodes. 2-25
Chap. 2 Quick index
SHELLDIRECTORVECTOR, defines director vectors that can be applied via command SHELLNODESDOF. NODESET, defines a collection of nodes. RIGIDNODES SHELL, specifies special constraints for shell midsurface nodes. Section 9.2: Element data AXES-NODES, defines an “axes-system” via three model nodes. AXES-INITIALSTRAIN, defines a set of axes to be used with the definition of initial strains in element. AXES-ORTHOTROPIC, defines set of principal material axes to be used with orthotropic material model. ELEDGESET, defines an element edge set containing edges of 2-D elements. ELEMENTSET, defines an element set containing elements. ELFACESET, defines an element face set containing faces of 3-D and shell elements. ENODES, defines element nodal connectivity. MESH-CONVERT, changes number of nodes per element. ENODES-INTERFACE, defines fluidstructure interface elements. EDATA, specifies property data associated with individual elements in a group. COPY-ELEMENT-NODES, copies all elements and nodes (in groups) between database models for two analysis programs. DELETE-FE-MODEL, deletes all finiteelement data from the database. REVOLVE, creates 3D elements by revolving 2D elements about an axis. SWEEP, creates 3D elements by extruding 2D elements along a vector.
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Section 9.3: Boundary conditions BOUNDARIES, assigns boundary conditions to nodes. CONSTRAINT-NODE, specifies a constraint equation between nodal degrees of freedom. RIGIDLINK-NODE, specifies a rigid link between two nodes. OVALIZATION-CONSTRAINT NODE, used to enforce the zero-slope-of-pipeskin condition in the longitudinal direction at pipe-element nodes. FSI-FACE, defines FSI boundary using element face nodes. Section 9.4: Loads APPLY CONCENTRATED-LOADS, Defines concentrated loads applied to nodes. APPLY DISPLACEMENTS, defines prescribed displacements applied to nodes. APPLY ELECTROMAGNETIC-LOADS, defines electromagnetic loads applied to nodes. APPLY PIPE-INTERNAL-PRESSURES, defines internal pressures applied to pipe element nodes. APPLY TEMPERATURES, defines temperatures applied to nodes. APPLY TGRADIENTS, defines temperature gradients applied to shell element surface nodes. APPLY USER-SUPPLIED-LOADS, signals the presence of user-supplied loads. LOADS-ELEMENT, used to apply loads onto element edges or faces.
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
Chap. 2 Quick index
Section 9.5: Initial conditions
Section 9.7: Fracture
INITIAL ACCELERATIONS, assigns initial accelerations to nodes. INITIAL DISPLACEMENTS, assigns initial displacements to nodes. INITIAL FLEXURALSTRAINS, assigns initial flexural strains to plate element nodes. INITIAL OVALIZATIONS, assigns initial ovalizations to pipe element nodes. INITIAL PINTERNALPRESSURES, assigns initial pipe internal pressures to pipe element nodes. INITIAL STRAINS, assigns initial strains to nodes. INITIAL SGRADIENTS, assigns initial strain gradients to shell element midsurface nodes. INITIAL TEMPERATURES, assigns initial temperatures to nodes. INITIAL TGRADIENTS, assigns initial temperature gradients to shell element nodes. INITIAL VELOCITIES, assigns initial velocities to nodes. INITIAL WARPINGS, assigns initial warpings to pipe element nodes. IMPERFECTION NODES, specifies imperfections at nodes based on the buckling mode shapes, which have been previously calculated.
CRACK-PROPAGATION NODES, used to define the initial crack front position and the virtual/actual crack propagation path in terms of nodes. J-VIRTUAL-SHIFT NODE, defines a fixed virtual-crack-extension material shift via a set of nodes. J-VIRTUAL-SHIFT ELEMENT, defines a fixed virtual-crack-extension material shift via a set of elements. J-LINE ELEMENT, defines a line contour connected by a series of element faces. SINGULAR NODES, defines a set of vertex nodes whose adjacent non-vertex nodes are to be moved. Section 9.8: Substructures and cyclic symmetry REUSE-NODES, defines the nodal connec tivity between the substructure and the main structure. CYCLICBOUNDARIES NODES, associates cyclicboundaries in terms of nodes.
Section 9.6: Contact CONTACT-ELEMSET, defines a contact surface using element edge or face set. CONTACT-FACENODES, defines a contact surface within the current group using face nodenumbers. CONTACT-NODES, defines a contactsurface in terms of nodes, within the current contact group.
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Chapter 3 Input/Output
DATABASE NEW
DATABASE NEW
Sec. 3.1 Database operations
SAVE PERMFILE PROMPT
DATABASE NEW creates a new database. The new database is initially empty. Before creating the new database, you have the option of saving any current internal database to disk. This option is controlled by parameters SAVE and PERMFILE. SAVE Used only when a database has been modified.
[UNKNOWN]
YES
The program saves the current internal database to disk using the filename specified by parameter PERMFILE. Then the program creates a new internal database.
NO
The program does not save the current internal database before creating a new internal database.
UNKNOWN
The program asks you if you want to save the database.
PERMFILE
[the last permanent database name previously specified] Used only when the database has been modified. PERMFILE is the filename of the permanent database file when saving the current database file to disk. You will be prompted for this name if you do not enter a value for this parameter and no permanent database name was previously specified. PROMPT Used when saving a permanent database file.
[UNKNOWN]
YES
You will be prompted “Ready to save permanent database file?”.
UNKNOWN
You will be prompted “Permanent database file already exists” if the database file already exists.
NO
You will not receive a prompt.
Auxiliary commands DATABASE CREATE SAVE PERMFILE DATABASE CREATE has the same effect as DATABASE NEW.
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DATABASE OPEN
Chap. 3 Input/Output
DATABASE OPEN
FILE SAVE PERMFILE PROMPT
DATABASE OPEN creates a new database using the permanent database file specified in this command. Before creating the new database, the current internal database is optionally saved to disk. FILE
[the last previously specified permanent database filename] The filename of the permanent database file to be opened. If you do not enter a filename and there is no default value, the program will prompt you for the filename. SAVE Used only when a database has been modified.
[UNKNOWN]
YES
The current internal database is saved to disk using the filename specified by parameter PERMFILE.
NO
The current internal database is not saved before clearing the current database and opening the specified database.
UNKNOWN
The program will ask you if you want to save the database.
PERMFILE
[the last previously specified permanent database filename] Used only if the database has been modified. PERMFILE is the filename of the permanent database file when saving the current database file to disk. The program will prompt you if you do not enter a value for PERMFILE and if no permanent database filename has previously been specified. PROMPT Used when saving a permanent database file. YES
You will be prompted “Ready to save permanent database file?”.
UNKNOWN
You will be prompted “Permanent database file already exists,” if the database file already exists.
NO
You will not receive a promp
Note:
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[UNKNOWN]
It is allowed to open a database created by AUI 7.0, AUI 7.1 or AUI 7.2. However, all graphics and model display definitions are deleted and reinitialized in the AUI working copy of the opened database.
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
DATABASE WRITE
DATABASE WRITE
Sec. 3.1 Database operations
PERMFILE PROMPT
DATABASE WRITE saves the current internal database as a permanent database file. It is the same as the DATABASE SAVE command except that DATABASE WRITE is available only when the database has been modified. PERMFILE
[the last previously entered permanent database filename specified] Specifies the filename of the permanent database file. The program will prompt you if you do not enter a value for PERMFILE and if no permanent database filename has previously been specified. PROMPT Used when saving a permanent database file.
[UNKNOWN]
YES
You will be prompted “Ready to save permanent database file?”.
UNKNOWN
You will be prompted “Permanent database file already exists” if the database file already exists.
NO
You will not receive a prompt.
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DATABASE SAVE
Chap. 3 Input/Output
DATABASE SAVE
PERMFILE PROMPT
DATABASE SAVE saves the current internal database as a permanent database file. PERMFILE
[the last previously entered permanent database filename specified] Specifies the filename of the permanent database file. The program will prompt you if you do not enter a value for PERMFILE and if no permanent database filename has previously been specified. PROMPT Used when saving a permanent database file.
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[UNKNOWN]
YES
You will be prompted “Ready to save permanent database file?”.
UNKNOWN
You will be prompted “Permanent database file already exists” if the database file already exists.
NO
You will not receive a prompt.
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
DATABASE ATTACH
DATABASE ATTACH
Sec. 3.1 Database operations
FILE
DATABASE ATTACH allows access to the specified file as an AUI database file. Unlike DATABASE OPEN (described in this section), DATABASE ATTACH does not make a working copy of the database file prior to opening it. Instead you work directly with the specified file as you use the AUI, possibly modifying the file’s contents. The advantages of DATABASE ATTACH as compared to DATABASE OPEN are: disk requirements are reduced because the AUI does not create a copy of the database file, and the CPU time to attach a database is much less than the CPU time required to open it. The disadvantages of DATABASE ATTACH are: (1) important information can be inadvertently modified or deleted from an attached database file, (2) the attached database cannot shrink, but can only grow as the AUI is used and (3) an attached database file cannot be saved, but can only be detached using DATABASE DETACH (described in this section). Before you can use DATABASE ATTACH, you must first save any current database, and then use DATABASE NEW (described in this section) to create a new database. You can use DATABASE ATTACH only if the current database is new and unmodified. DATABASE ATTACH clears the permanent database filename. You can attach a database that was created by earlier versions of the AUI. In this case, however, the AUI deletes and reinitializes all graphics and model display definitions in the attached database. Exiting the AUI when a database is attached automatically detaches the database. FILE The filename of the permanent database file to be attached. If no filename is entered, the AUI will prompt you for the filename. Note:
It is allowed to open a database created by AUI 7.0, AUI 7.1 or AUI 7.2. However, all graphics and model display definitions are deleted and reinitialized in the AUI working copy of the opened database.
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DATABASE DETACH
Chap. 3 Input/Output
DATABASE DETACH
PERMFILE PROMPT
DATABASE DETACH creates a permanent database file by detaching the working copy of the database file. Unlike DATABASE SAVE, DATABASE DETACH does not create a new permanent database file. The advantages of DATABASE DETACH as compared to DATABASE SAVE are: disk requirements are reduced because the AUI does not create a copy of the database file, and the CPU time to detach a database is much less than the CPU time required to save it. The disadvantage of DATABASE DETACH is: the AUI does not compress the database file by removing unused records. After the database is detached, the AUI creates a new empty internal database. A database can be detached at any time whether or not it was attached using DATABASE ATTACH. PERMFILE The working copy of the database file is renamed to PERMFILE. PROMPT Used when saving a permanent database file.
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[UNKNOWN]
YES
You will be prompted “Ready to save permanent database file?”.
UNKNOWN
You will be prompted “Permanent database file already exists” if the database file already exists.
NO
You will not receive a prompt.
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
ADINA initiates model validation and, if the model is valid, creates an ADINA input data file, if requested. OPTIMIZE [SOLVER] Equation numbering may be optimized so as to minimize the profile and bandwidth of the ADINA solution matrices. The node label numbers are not affected by the equation numbering. {SOLVER/YES/NO} SOLVER
If the sparse solver is used (see parameter SOLVER in command MASTER), then equation numbering is not optimized. Otherwise, equation numbering is optimized.
YES
Equation numbering is optimized.
NO
Equation numbering is not optimized.
STARTNODE [automatically selected] Label number of a main structure node, used to initiate the optimized equation numbering algorithm. If such a node is not given, one will be automatically selected. The starting node should be a peripheral node on the boundary of the main structure. FILE The filename of the ADINA input file to be generated. If no file name is given then only model validation is performed. FIXBOUNDARY [YES] Inactive degrees of freedom, i.e., those which are not connected to any elements and are not used in constraint equations, may be automatically deleted. {YES/NO} MIDNODE [NO] Midside nodes on element edges may be moved to the straight line connecting the relevant vertex nodes. {YES/NO} OVERWRITE [CONTROL PROMPT] Determines, if the filename given by FILE already exists, whether the command will overwrite its contents with the currently generated input data. If set to UNKNOWN, a prompt will be given requesting confirmation for overwriting an existing file. {YES/NO/UNKNOWN}
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Chap. 3 Input/Output
REBUILD-MODEL
REBUILD-MODEL Forces the AUI to rebuild the whole model.
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AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
REBUILD-MODEL
Sec. 3.2 Analysis data files
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LOADDXF
Chap. 3 Input/Output
LOADDXF
FILE GCOINCIDE GCTOLERANCE
LOADDXF loads an AutoCAD® DXF file into the database. The points and lines are converted into AUI geometry entities. This command supports only up to AutoCAD Release 12 DXF files. FILE The DXF file to be loaded in this command. Only a formatted file is accepted. GCOINCIDE [YES] Point coincidence checking. If GCOINCIDE is set to YES then point coordinates are checked, and if within GCTOLERANCE × (max. difference in global coordinates between all previous points) then no new point number is created at that location, i.e., the previous point label number is assumed. {YES/NO} GCTOLERANCE Tolerance used to determine point coincidence.
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[1.0E-5]
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
Loads an IGES file into the database. FILE The IGES file to be loaded in this command. Only a formatted and uncompressed file is accepted. GCOINCIDE [YES] Point coincidence checking option. If set to YES, then point coordinates are checked, and if within GCTOLERANCE × (max. difference in global coordinates between all previous points) then no new point is created at that location, i.e. the previous point label number is assumed. Only valid when ADINA-M = NO.{YES/NO} GCTOLERANCE [1.0E-5] Tolerance used to determine point coincidence. Only valid when ADINA-M = NO. TWOD-XY [NO] Indicates whether or not to rotate the IGES geometry model so that the XY plane is transformed into the YZ plane (as used in two-dimensional ADINA, ADINA-T, and ADINA-F models). {YES/NO} ADINA-M Indicates whether IGES data is to be loaded into ADINA-M. {YES/NO} Parameters GCOINCIDE, GCTOLERANCE and TWOD-XY are ignored by ADINA-M.
[NO]
LABEL
[(highest current sheet body or solid body label number) + 1] Sheet body or solid body label number. SEWING Indicates wether ADINA-M sheet bodies are to be sewn together. {YES/NO}
[NO]
SEWGAP [0.01] ADINA-M sewing body gap ratio. The gap value used to sew the body is SEWGAP * (max. difference in global coordinate between the maximum and minimum of the IGES body).
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AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
LOADIGES
Sec. 3.3 External data
TOLER1 This parameter is obsolete. TOLER2 This parameter is obsolete. OPTION1 This parameter is obsolete. REVERSE This parameter is obsolete. OPTION3 This parameter is obsolete. OPTION4 This parameter is obsolete. SCALEFACTOR [1.0] ADINA-M scale factor - input IGES coordinate values are to be divided by, i.e. (x-coordinate, y-coordinate, z-coordinate)/scalefactor. PRECS This parameter is obsolete. PLABEL Starting point label. LLABEL Starting line label.
[(current highest point label number) + 1] [(current highest line label number) + 1]
XZERO The flag to set the x coordinate to 0. {NO/YES}
[NO]
X-SHIFT [0.0] Y-SHIFT [0.0] Z-SHIFT [0.0] Shift the IGES geometry by X-SHIFT, Y-SHIFT, and Z-SHIFT in the x, y, and z direction, respectively. Note that if XZERO=YES, X-SHIFT is ignored. These three parameters are used only when ADINA-M=NO.
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Chap. 3 Input/Output
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AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
LOADSOLID
LOADSOLID
Sec. 3.3 External data
PARTFILE BODYNAME XORIGIN YORIGIN ZORIGIN AX AY AZ BX BY BZ PCOINCIDE PCTOLERANCE MANIFOLD FORMAT OLD-UNIT NEW-UNIT SYSTEM REPAIR
The LOADSOLID command loads a Parasolid® part (or "transmit") file into the database. The model may be displayed, meshed, and loads, boundary conditions may be assigned to its faces, edges, and vertices. For each body within the Parasolid® file a solid geometry BODY is created which is used to reference that body. This command is only active when ADINA-M has been licensed. PARTFILE The name of a Parasolid® part file (i.e. for part file name "abcdef.x_t" you input PARTFILE=abcdef. BODYNAME [(current highest body label number)+1] This is the label number to be assigned to the first BODY to be created which is used to refer to the first body in the part file -- other bodies in the part file will automatically be assigned BODY label numbers incremented from this parameter (i.e. (BODYNAME+1), (BODYNAME+2), ..., etc.) XORIGIN YORIGIN ZORIGIN The global coordinates of the origin of the model.
[0.0] [0.0] [0.0]
AX AY AZ A vector (in global coordinates) giving the direction of the X-axis of the model.
[1.0] [0.0] [0.0]
BX [0.0] BY [1.0] BZ [0.0] A vector (in global coordinates) which together with vector (AX, AY, AZ) gives the X-Y plane of the model. PCOINCIDE [NO] Indicates whether or not the vertices of the part are to be checked for coincidence with existing geometry point coordinates. {NO/YES}
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Chap. 3 Input/Output
PCTOLERANCE Tolerance used to determine whether two points are coincident.
LOADSOLID
[1.0E-5]
MANIFOLD [NO] Indicates whether non-manifold bodies are converted into manifold bodies. {NO/YES} FORMAT Parasolid part file format. TEXT
text format.
BINARY
binary format.
[TEXT]
OLD-UNIT The unit of the part in the Parasolid file to be imported. {METER/CMETER/MMETER/INCH/FOOT}
[METER]
NEW-UNIT The unit of the part after it is imported into ADINA-M. {METER/CMETER/MMETER/INCH/FOOT}
[METER]
SYSTEM [0] If system label is greater than 0 and it is Cartesian coordinate system, replace XORIGIN, YORIGIN, ZORIGIN, AX, AY, AZ, BX, BY, BZ with the values from the given system. REPAIR Repair the bodies if errors are detected. {NO/YES}
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[NO]
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
LOAD-CLOUD
Sec. 3.3 External data
LOAD-CLOUD FILE STL-FILE BINARY BYTESWAP OUTLENGTH elementi Reads in a point cloud file (depicting the boundary of an object) and writes out an STL file which can then be loaded into the AUI with the LOAD-STL command. A tetrahedral mesh of the point cloud is initially built and elements are automatically "sculpted" away from the boundary going in. This command is used repeatedly until the point cloud mesh corresponds to the object. FILE Name of the point cloud file. Each line of the file contains a point defined by three coordinates (x, y and z). The point cloud file is assumed to be noise-free and represent accurately (must be fine enough) the geometry of the object's boundary. The object the point cloud is representing is assumed to be a single body (not an assembly of bodies). STL-FILE If none given, the command will not generate the STL file. It will however save the point cloud mesh into the AUI (which can then be reloaded if the command is called again). If a STL file name is given, the command will create the STL file and delete the current point cloud mesh that's residing in memory. BINARY [NO] If set to NO, the output STL file format is supposed to be ASCII. If set to YES, the output STL file format is supposed to be binary. The byte ordering is supposed to be "little endian" (the norm for STL binary files). {NO/YES} BYTESWAP [NO] If the byte ordering (see BINARY parameter) is "big endian", BYTESWAP should be set to YES. Because STL files are supposed to be written as "little endian", turning on BYTESWAP should not be needed in general {NO/YES} OUTLENGTH [0.0] Elements of the current point cloud mesh with at least one boundary face bigger (longest side) than OUTLENGTH are assumed to be outside and are thus removed from the mesh. Because this process changes the current boundary, a "sculpting" phase follows which automatically removes elements which are believed to be outside. If set to 0.0 (default), it is not used. elementi Elements given are removed from the current point cloud mesh. Because this process changes the current boundary, a "sculpting" phase follows which automatically removes elements which are believed to be outside.
Loads an STL format file into the AUI by creating a STL body. Once loaded, mesh densities (MODE = LENGTH) can be applied to the created STL body, its faces and edges (just like for an ADINA-M body). The command BODY-DSCADAP applies the mesh densities and generates a discrete representation of the STL body which can then be meshed with the GBODY command. It is assumed the model contained in the STL file is single-bodied and solid (defines a threedimensional volume). If the model is made up of several bodies, the command still loads the STL file as a single body made up of disconnected parts. To create multiple bodies, the model should be saved as multiple STL files, one for each body to be created. Upon completion, if the STL file cannot be loaded, problems are either coming from the tolerance choice or the STL model itself. If the number of under connected edges (connected to a single triangle) is greater than 0, the tolerance (NCTOLERA) may be set too low or the model is not watertight. If the number of over connected edges (connected to more than two triangles) is greater than 0, the tolerance (NCTOLERA) may be set too high or the model has non-manifold features (see NMTOLERA parameter). If the number of non-manifold vertices is greater than 0, make sure the tolerance used for eliminating non-manifold features (NMTOLERA) is greater than 0 (but always significantly lower than NCTOLERA). Eliminating non-manifold features is attempted only when the number of under connected edges is 0. If NCTOLERA is changed, NMTOLERA must be changed accordingly as it should always be larger than NCTOLERA. If changing the tolerance (NCTOLERA) does not resolve all problems, it is likely the STL file is not valid in representing a conforming triangular mesh. If the STL file loads properly, it is assumed that the geometry it represents is not selfintersecting. FILE Name of file containing the STL data. BODY Label of STL body to be created.
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[(highest body label number) + 1]
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
LOAD-STL
Sec. 3.3 External data
RIDGEANG [60 (degrees)] Controls ridge detection and therefore the creation of body edges. If two adjacent triangles in the STL file have an angle greater than RIDGEANG, the common edge is assumed to be on a ridge and will be part of a body edge, potentially separating two body faces. By setting the RIDGEANG to 180, the created body will have no edges and no vertices (points). NCTOLERANCE [1.0e-5] Tolerance used for checking coincidence of facet nodes (vertices of triangle facets). RIDGETOL [0.0] Tolerance used to decide whether to discard potential edges on body edges. Given an edge and its two adjacent triangles in the STL file, if the distance from a vertex to the opposite edge is smaller than RIDGETOL (relative to its length) for each triangle, then the edge cannot be considered a ridge. By default, RIDGETOL is set to 0.0, meaning it is disabled. In most cases, enabling RIDGETOL is not necessary. MAXNVARS [0.0] Maximum normal variation used in edge swapping (to improve quality of STL surface mesh prior to ridge detection). This threshold should remain small enough to maintain the shape of the original model. By default, MAXNVARS is set to 0.0, meaning it is only enabled on planes. COTOLERANCE [1.0e-4] Edges that are smaller than COTOLERANCE (relative to model size) are collapsed. Faces with large angle such that distance from vertex at large angle to opposite side is smaller than COTOLERANCE are swapped. This is done to remove small features from the STL surface mesh prior to ridge detection. Note: COTOLERANCE should be larger than NCTOLERANCE. MAXNVARC [90.0] Maximum normal variation used in edge collapsing (to improve quality of STL surface mesh prior to ridge detection). If COTOLERANCE is small then MAXNVARC may be large. If COTOLERANCE is large then MAXNVARC should be small. NMTOLERANCE [1.0e-3] If the surface triangles in the STL file represent a non-manifold body (for example, the surface mesh contacts itself at vertices or edges), it is possible to "break" the surface mesh by duplicating vertices where the surface mesh contacts itself and pulling them away from each other. NMTOLERANCE represents how far duplicate vertices should be pulled apart from each other, relative to the dimensions of the model. If set to 0.0, it is turned off.
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Chap. 3 Input/Output
LOAD-STL
NMTOLERANCE should always be greater than NCTOLERANCE. RIDGEAN2 [180 (degrees)] Before the creation of body edges, if a ridge edge (see RIDGEANG description) is not connected (at either end), it can be extended so as to make sure any edge connects (at either end) to one or more other ridge edges. New ridge edges will be created only if the adjacent triangles have an angle greater than RIDGEAN2. By default, RIDGEAN2 is set to 180, which signifies this extension feature is not activated. If activated (RIDGEAN2 is not equal to 180), RIDGEAN2 should be smaller than RIDGEANG. BYTESWAP [NO] If the STL file is binary and the byte ordering is "big endian" (as opposed to "little endian" which is the norm for STL binary files), BYTESWAP should be set to YES. {NO/YES}
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NASTRAN-ADINA maps a NASTRAN® data file into the ADINA-IN database. FILE The NASTRAN® data filename. XY-YZ This parameter is now obsolete. The program will automatically rotate 2D models in the XY plane to the YZ plane. BEAM [THREE] Indicates whether hermitian beam elements are to be considered as having two-dimensional or three-dimensional action. {TWO/THREE} SUBCASE [0] The label number of a subcase defined in the NASTRAN® data file. If SUBCASE=0, the first subcase is used. {≥0} BCELL [NO] Indicates whether boundary cells (see command BCELL) are created from shell elements according to the property identification number (PID). All elements with the same PID are put into the same BCELL. {NO/YES/REPLACE} NO
Do not create boundary cells.
YES
Create boundary cells. In addition, if the shell elements are attached to 3-D elements, the program will also create element-face sets (see ELFACESET command) and node sets (see NODESET command). All shell elements used for creating these ELFACESETs and NODESETs are not deleted.
REPLACE
Create boundary cells. In addition, if the shell elements are attached to 3-D elements, the program will also create element-face sets (see ELFACESET command) and node sets (see NODESET command). All shell elements used for creating these ELFACESETs and NODESETs will be deleted.
CONVERT-ELEMENT-TYPE [NONE] Specifies whether or not to convert 4-node shell elements to 8-node. {NONE/SHELL} The parameters RBAR, RBE2, NCTOLERANCE, RBAR-MATERIAL, RBAR-AREA, RBAR-
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NASTRAN-ADINA
DIAMETER, RBAR-THICKNESS, RBE2-MATERIAL, RBE2-AREA, RBE2-DIAMETER, and RBE2-THICKNESS are now obsolete. The conversion of RBAR and RBE2 elements is now specified in the NX Nastran bulk data entry NXSTRAT (see parameters EQRBAR and EQRBE2). DEFAULT [AUI] Specifies which default values and convention should be used when a parameter is not specified. {AUI/NXN} AUI
Use AUI default values and convention.
NXN
Use NX Nastran advanced nonlinear analysis (SOL 601/701) default values and convention. Nodal temperature and displacement loads with different time functions are added instead of averaged if DEFAULT=NXN.
Note: The following default values are different between AUI and SOL 601/701 in NX Nastran. Command
Parameter
AUI
NXN
CGROUP CGROUP CONTACT-CONTROL
EPST CONSISTENT-STIFFNESS POST-IMPACT
0.0 DEFAULT YES
1.0E-3 OFF NO
DUPLICATE [YES] This flag indicates whether or not to issue an error message when the Nastran file has a duplicate node or element. {NO/YES} NO
No error message issued. Later entries will override the earlier entries.
YES
Error message issued.
SPLIT [PROGRAM] Indicates whether elements from different bulk entry (e.g., CHEXA, CPENTA, CTETRA) but having the same PID are split into different element groups. By default (i.e., PROGRAM), splitting is done for ADINA and ADINA-T models but not for ADINA-F models. {PROGRAM/YES/NO} ELFACESET [BCELL] Flag to create elfaceset from attached SHELL element. {BCELL/NO/YES/REPLACE} BCELL
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Take the default flag from BCELL parameter
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NASTRAN-ADINA
Sec. 3.3 External data
NO
No elfaceset will bce created
YES
Create elfaceset and keep the attached SHELL element group
REPLACE
Create elfaceset then delete the attached SHELL element group
Note that as long as one of BCELL, ELFACESET or NODESET = REPLACE the attached SHELL element will be deleted. NODESET [BCELL] Flag to create nodeset from attached SHELL element. {BCELL/NO/YES/REPLACE} BCELL
Take the default flag from BCELL parameter
NO
No nodeset will bce created
YES
Create nodeset and keep the attached SHELL element group
REPLACE
Create nodeset then delete the attached SHELL element group
Note that as long as one of BCELL, ELFACESET or NODESET = REPLACE the attached SHELL element will be deleted.
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EXPORT NASTRAN
Chap. 3 Input/Output
EXPORT NASTRAN
FILE OVERWRITE FORMAT
Exports an ADINA model to a NASTRAN file. By default, the small field format is used. FILE Specifies the NASTRAN file name. OVERWRITE [CONTROL PROMPT] Determines, if the file name given by FILE already exists, whether the command will overwrite its contents with the currently generated input data. If set to UNKNOWN, a prompt will be given requesting comfirmation for overwriting an existing file. {YES/NO/UNKNOWN} FORMAT Indicates the format to export the NASTRAN file. {SMALL/LARGE}
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EXPORT UNIVERSAL
EXPORT UNIVERSAL
Sec. 3.3 External data
FILE
Exports the mesh in ADINA-AUI to an I-DEAS® universal file format. FILE Specifies the name of the universal file to be created.
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READ
Chap. 3 Input/Output
READ
FILE REWIND SCANDATA
READ reads AUI input commands from the file specified by parameter FILE until the end of the file is reached or the READ END command is encountered in the file. After the READ command is executed, subsequent input is read from the previous command input source (that is, the input source from which the READ command was entered). READ commands can be nested (that is, a file processed by the READ command can itself include a READ command). FILE The name of the file from which AUI commands are read (up to 80 characters long). Note that the name END is not allowed. REWIND [NO] If the file pointer is at end-of-file or if the file is not currently open, the read file is rewound before beginning to read commands regardless of the value of this parameter. {YES/NO} SCANDATA [‘ ‘] If SCANDATA is specified, the file is scanned until the SCANDATA string (1 - 80 characters) is found anywhere within an input record. Reading of input data from the file starts at the beginning of the record that contains the string. Auxiliary commands READ END Terminates reading from file.
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FILEREAD
FILEREAD
Sec. 3.4 Auxiliary files
OPTION FILE
FILEREAD controls the source of input commands to the AUI. OPTION
[INTERFACE]
INTERFACE
Commands are read from the terminal or window from which you invoked the AUI.
FILE
Commands are read from the file specified by the FILE parameter.
FILE The filename of the file from which commands are read. Used only if OPTION = FILE. Auxiliary commands LIST FILEREAD
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FILESESSION
Chap. 3 Input/Output
FILESESSION
OPTION FILE
FILESESSION controls the generation and output of a session file. The session file contains the commands needed to repeat an AUI session. A session file differs from an echo file in that: 1) You can generate a session file from a user-interface AUI session (this is the primary use of the session file). 2) A session file contains all command parameters, regardless of whether you entered them or whether they were default parameters. 3) Changes to data input lines are handled in a different manner. OPTION
[NO]
NO
No session file is created.
OVERWRITE
A session file is generated and overwrites any existing contents of the specified file.
APPEND
A session file is generated and is appended to any existing contents of the specified file.
FILE The filename of the session file. Auxiliary commands LIST FILESESSION
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FILELIST
FILELIST
Sec. 3.4 Auxiliary files
OPTION FILE LINPAG EJECT
FILELIST controls the format and output of listings. OPTION
[INTERFACE]
INTERFACE
Listings are output at the terminal or window from which you invoked the AUI. Listings are buffered using an interface similar to UNIX “more” that allows you to scroll through listings.
FILE
Listings are output to the file specified by the FILE parameter.
FILE The filename of the file to which listings are written. Used only if OPTION = FILE. This can be the same file used for command echoing or logging. LINPAG [0] The maximum number of lines output between list headings. You can suppress list headings (except for the first list heading) by specifying LINPAG = 0. EJECT Specifies whether page ejects are placed before headings. {YES/NO}
[NO]
Auxiliary commands LIST FILELIST
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FILEECHO
Chap. 3 Input/Output
FILEECHO
OPTION FILE
FILEECHO controls the echoing of your input commands. OPTION
[INTERFACE]
NO
No echoing of input commands.
INTERFACE
Input commands are echoed back to the terminal or window from which you invoked the AUI.
FILE
Input commands are echoed back to the file specified by the FILE parameter.
FILE The filename of the file to which input commands are echoed back. Used only if OPTION = FILE. This can be the same file for logs or listings. Auxiliary commands LIST FILEECHO
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FILELOG
FILELOG
Sec. 3.4 Auxiliary files
OPTION FILE
FILELOG controls the output of log messages. OPTION
[INTERFACE]
INTERFACE
Log messages are written to the terminal or window from which you invoked the AUI.
FILE
Log messages are written to the file specified by the FILE parameter.
FILE The filename of the file to which log messages are written. Used only if OPTION = FILE. This can be the same file used for echoed commands or listings. Auxiliary commands LIST FILELOG
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COMMANDFILE
Chap. 3 Input/Output
COMMANDFILE
FILENAME PROMPT OPTION GRAPHICS
Creates a file containing the commands needed to recreate the model stored in the current database. FILENAME The name of the file to be created. This parameter must be entered. PROMPT [CONTROL PROMPT] You will be prompted “Ready to write command file?” if PROMPT = YES. You will be prompted “The command file already exists” if the specified file already exists and PROMPT = UNKNOWN. You will not be prompted if PROMPT = NO. Note that the default is taken from the parameter with the same name of the CONTROL command. OPTION [SESSION] If OPTION = SESSION, the command file produced is a record of all commands issued when this database file is in use. The command file contains model modifications and deletions as well as model additions. Commands in the command file may contain references to other files, for example, when a porthole file is loaded, the command file contains a LOADPORTHOLE command. Currently OPTION must be set to SESSION. This parameter is provided for future developments of the AUI. GRAPHICS [NO] This parameter is used when OPTION = SESSION to control whether graphics commands such as FRAME, MESHPLOT, VIEW, etc. are written to the command file. If GRAPHICS = YES, graphics commands are written to the command file, otherwise they are not written.
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RTOFILE
Sec. 3.4 Auxiliary files
RTOFILE PROGRAM texti This command defines the contents of a run-time-option (.rto) file. When an ADINA, ADINAT or ADINA-F data file (.dat file) is created, a corresponding run-time-option file (.rto file) is also created. If the RTOFILE command is not run, or if there are no lines of text in the RTOFILE command, then no .rto file is created. PROGRAM [Current FE program] The finite element program for which the .rto file will be created. {ADINA/ADINA-T/ ADINA-F} texti A line of text in the .rto file. This text must be enclosed by single quotes. There can be an arbitrary number of lines of text in the .rto file. Allowable input in the .rto file depends on the finite element program. Auxiliary commands LIST RTOFILE DELETERTOFILE
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PAUSE
PAUSE When the AUI reads the PAUSE command, it stops processing commands until you hit a key.
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END
Sec. 3.5 Program termination
END
SAVE PERMFILE PROMPT IMMEDIATE
END terminates the program. EXIT, QUIT and STOP are equivalent to END. If the program is reading data from a file specified by the FILEREAD command and the end of the file is reached, the END command is executed automatically. SAVE [UNKNOWN] Used only when a database has been modified. YES The program saves the current internal database to disk using the filename specified by parameter PERMFILE. Then the program creates a new internal database. NO
The program does not save the current internal database before creating a new internal database.
UNKNOWN
The program asks you if you want to save the database.
PERMFILE
[the last previously specified permanent database filename] PERMFILE is the filename of the permanent database file when saving the current database file to disk; used only if the database has been modified. The program will prompt you if you do not enter a value for PERMFILE and if no permanent database filename has previously been specified. PROMPT [UNKNOWN] Used when saving a permanent database file. YES You will be prompted “Ready to save permanent database file?”. UNKNOWN
You will be prompted “Permanent database file already exists” if the database file already exists.
NO
You will not receive a prompt.
IMMEDIATE [NO] If IMMEDIATE=YES, the program immediately stops execution without saving the database or prompting you. This option is most useful when writing batch scripts to force the program to terminate. {YES / NO} Auxiliary commands EXIT SAVE PERMFILE PROMPT QUIT SAVE PERMFILE PROMPT STOP SAVE PERMFILE PROMPT EXIT, QUIT and STOP are equivalent to END. ADINA R & D, Inc.
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PARAMETER
Chap. 3 Input/Output
PARAMETER
NAME EXPRESSION
Defines a parameter that can be substituted in a later command. The AUI evaluates the given expression and stores the resulting number as the value of the parameter. Note:
Parameter definitions and values are not stored in the database.
NAME The name of the parameter (1 to 30 alphanumeric characters). The name is not case sensitive. If the parameter is not already defined, a new parameter is created, otherwise the existing parameter is modified. EXPRESSION A string (up to 256 characters long) that contains a numeric expression. The expression string can contain the following items: The arithmetic operators +, -, *, /, ** (exponentiation) Numbers (either real numbers or integers) The following functions: ABS(x) AINT(x) ANINT(x) ACOS(x) ASIN(x) ATAN(x) ATAN2(x,y) COS(x) COSH(x) DIM(x,y) EXP(x) LOG(x) LOG10(x) MAX(x,y,...) MIN(x,y,...) MOD(x,y) SIGN(x,y) SIN(x) SINH(x) SQRT(x)
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absolute value truncation nearest whole number arccosine arcsine arctangent arctangent(x/y) cosine hyperbolic cosine positive difference exponential natural logarithm common logarithm largest value smallest value remaindering transfer of sign sine hyperbolic sine square root
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
PARAMETER
Sec. 3.6 Auxiliary commands
STEP(x)
the unit step function: 0.0 if x ≤ 0.0 1.0 if x < 0.0 tangent hyperbolic tangent
TAN(x) TANH(x)
All trigonometric functions operate on or return angles in radians. Examples PARAMETER A '3.0' PARAMETER B '5 + 7' PARAMETER C '6 * \ 5 '
// A = 3 // B = 12 // The string can be entered on several // command lines as in this example; C = 30
Parameter substitution When the command-line parser finds a token value that starts with a $, the parser finds the parameter name with that token value and substitutes the parameter value. For example, in the commands PARAMETER X1 '2.0/3.0' PARAMETER X2 'SQRT(5.0)' PARAMETER X3 'SIN(2.0)' BODY BLOCK DX1=$X1 DX2=$X2 DX3=$X3 the parser looks for the values of X1, X2 and X3 and substitutes the values (e.g. the characters '0.666666666666667') for the names (e.g. the characters 'X1'). Hence the above commands are exactly equivalent to the command BODY BLOCK DX1=0.666666666666667 DX2=2.23606797749979, DX3=0.909297426825682 The token values need not be in upper-case: BODY BLOCK DX1=$x1 DX2=$x2 DX3=$x3 Parameter substitution occurs before command execution, so the following is allowed: PARAMETER A '2.0' PARAMETER A '$A + 1'
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// A = 3
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Chap. 3 Input/Output
PARAMETER
Now you may want to put the symbol $ into a string without parameter substitution occuring. The rule is: if the next character after the $ is a letter [a-z], the command-line parser attempts parameter substitution. So PARAMETER A '3.0' USERTEXT ABC 'The cost is $2000.00' 'The size is $A' DATAEND is equivalent to USERTEXT ABC 'The cost is $2000.00' 'The size is 3' DATAEND A convenient way to output the value of a single parameter is with the ECHO command: PARAMETER X1 '2.0/3.0' ECHO $X1 ECHO 'The value of X1 is $X1' Auxiliary commands LIST PARAMETER Lists the values of all parameters. ECHO STRING Outputs the given string. This command can be used to output the value of a parameter, see the examples given in the PARAMETER command description. STRING is a string (up to 256 characters long).
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CONTROL defines certain parameters that control program behavior. The parameters defined by the CONTROL command are stored in the database. PLOTUNIT
[PERCENT]
VERBOSE
[YES]
ERRORLIMIT
[0]
LOGLIMIT
[0]
UNDO [5] The UNDO parameter controls the number of commands that can be undone using the UNDO command. If UNDO = 0, the UNDO command cannot be used, if UNDO = 1, UNDO can be used to undo the effects of the previous command, if UNDO = 2, UNDO can be used to undo the effects of the previous two commands, etc. Setting UNDO = 0 can significantly speed up the processing of batch files. PROMPT [UNKNOWN] Controls the default behavior for prompts which may arise from various commands. NO
No command prompts will be issued - this is useful in batch mode - eliminating any interaction.
YES
Command prompts are always issued.
UNKNOWN
Command prompts are issued only when necessary.
AUTOREPAINT [YES] When AUTOREPAINT = YES, the AUI automatically repaints that area of the graphics window that is exposed to the removal or motion of overlapping windows or dialogs. You may want to set AUTOREPAINT to NO to suppress the repainting; in that case, you can use the REFRESH command whenever you want to repaint the graphics window. DRAWMATTACH [YES] When DRAWMATTACH = YES, mesh plot attachments (band plots, load plots, element vector plots, reaction plots, line contour plots) are drawn. Otherwise, they are not drawn. ADINA R & D, Inc.
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CONTROL
One use of this option would be to turn off drawing of mesh plot attachments before moving the mesh plots with the mouse. DRAWTEXT DRAWLINES DRAWFILLS These options control the drawing of text, lines and fills:
[EXACT] [EXACT] [EXACT]
EXACT
Use the requested colors while drawing.
SATURATED
Convert all colors to saturated colors before drawing.
GRAY
Convert all colors to gray scales before drawing.
INVERSE
Convert all colors to the INVERSE color before drawing (the INVERSE color is the opposite of the background color).
NO
Do not draw.
AUTOMREBUILD [YES] When you enter a command that alters the geometry or finite element model, the AUI rebuilds all corresponding data structures so that the model can be re-plotted. This feature can be deactivated by setting AUTOMREBUILD = NO (in this case, if you want to plot the model, you must use the ADINA, ADINA-T or ADINA-F commands to rebuild the model beforehand). Setting AUTOMREBUILD = NO can significantly speed up the processing of batch files. Notes :
1) One important use of parameters DRAWTEXT, DRAWLINES, DRAWFILLS is when making plots in black and white for reports. In this case you might use DRAWTEXT = INVERSE, DRAWLINES = INVERSE, DRAWFILLS = GRAY. 2) The drawing parameters apply both to graphics as displayed on the screen and to graphics as produced using SNAPSHOT or MOVIESAVE. 3) One use of DRAWFILLS = SATURATED is to speed up shaded color image drawing, especially using X Window graphics; all shades of each color are converted to the same color, resulting in significantly fewer color changes.
ZONECOPY [NO] Controls whether the commands BANDPLOT, MESHPLOT, ELINEPLOT, EVECTORPLOT, LCPLOT, REACTIONPLOT, BANDSTYLE, MESHSTYLE, ELINESTYLE, EVECTORSTYLE, LCSTYLE, REACTIONSTYLE create copies of the input zones. Zone copies are always created by these commands in AUI 7.0 but not in later versions of the AUI. The preferred
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CONTROL
Sec. 4.1 Settings
setting of ZONECOPY is NO, but YES may be necessary to read input/session files produced for/by AUI 7.0. {YES/NO} SWEEPCOINCIDE [YES] Controls whether the SURFACE/VOLUME REVOLVED/EXTRUDED geometry definition commands check for coincident lines and surfaces, as well as for coincident vertices (points). AUI 7.0 did not attempt to connect adjacent surfaces/volumes, resulting in duplicate lines and surfaces fro such “sweep” geometry definition. The default in AUI 7.1 and higher is to connect adjacent surfaces/volumes whenever possible. However, AUI 7.0 input/session files which contain such “sweep” geometry will likely fail, so it may well be necessary to set SWEEPCOINCIDE=NO to correctly process older input files. {YES/NO} SESSIONSTORAGE [YES] If SESSIONSTORAGE = YES, the subsequent commands are stored in the AUI database. You can output these commands using the command COMMANDFILE. In the event of a system crash, you can retrieve these commands by opening the AUI temporary database, and subsequently issuing the COMMANDFILE command. If SESSIONSTORAGE = NO, subsequent commands are not stored in the AUI database and therefore cannot be retrieved. You may wish to set SESSIONSTORAGE = NO before reading commands from a batch file to eliminate the overhead of storing those commands within the AUI database. Note that the storage of commands in the AUI database is independent of the writing of commands to the session file determined by command FILESESSION. DYNAMICTRANSFORM [YES] Controls how the program indicates the transformation when you move, resize or rotate graphics using the mouse. If DYNAMICTRANSFORM=YES, the program redraws all picked graphics completely and redraws all other graphics that overlap the picked graphics. If DYNAMICTRANSFORM=PARTIAL, the program partially redraws all picked graphics and does not redraw overlapping graphics. If DYNAMICTRANSFORM=NO, the program indicates the transformation using a bounding box. UPDATETHICKNESS [YES] When you change the thickness of geometry surfaces or faces, all elements generated onto the surfaces or faces are automatically updated with the updated thickness. {YES/NO} In AUI 7.2 and lower, elements are not automatically updated. Therefore you may need to set UPDATETHICKNESS=NO so that input files constructed for use with AUI 7.2 and lower work correctly.
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Chap. 4 Interface control and editing
CONTROL
AUTOREGENERATE [NO] If AUTOREGENERATE=YES, the program regenerates the graphics after you run a command that changes the model definition. This parameter only applies to commands that are run from the command-line (or read from a file); it does not apply to dialog box input from the user interface. Note that the user interface always regenerates the graphics after you use a dialog box that changes the model definition. {YES/NO} ERRORACTION [CONTINUE] Defines AUI action when error is detected. Parameter affects only commands read from a batch file.
Note:
CONTINUE
AUI continues to process commands.
SKIP
AUI skips the remaining commands up to the next READ END command, if any.
For more details see AUI Command Reference Manual: Vol. IV - Display processing.
FILEVERSION [V85] This parameter tells the AUI which algorithms to use during subsequent commands. Use this flag to request algorithms from previous versions of the AUI. For example, if you constructed a batch file in AUI 8.3, set FILEVERSION=V83 to specify that the AUI 8.2 algorithms should be used in processing the file. {V73 / V74 / V75 / V80 / V81 / V82 / V83 / V84 / V85}. INITFCHECK [NO] This parameter tells the AUI whether or not to consider subsequent commands as part of an initialization file. If INITFCHECK=NO, subsequent commands are not considered part of an initialization file, if INITFCHECK=YES, subsequent commands are considered part of an initialization file. When INITFCHECK=YES, the AUI does not check resultants and aliases for errors. Therefore resultants and aliases can be included in initialization files when INITFCHECK=YES. Also the AUI always allows the use of the FEPROGRAM command when INITFCHECK=YES. SIGDIGITS [6] This parameter controls the number of significant digits used in listings. Between 1 and 16 significant digits can be requested. AUTOZONE [YES] When AUTOZONE=YES, the AUI automatically creates zones for many common parts of the model, such as element groups, contact surfaces and geometry bodies. See the description in
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CONTROL
Sec. 4.1 Settings
the Zones - Introduction section of this manual (Section 6.2.) { YES / NO } For models with many element groups or geometry bodies, you may want to turn off the AUTOZONE feature to save storage and CPU time. PSFILEVERSION [V0] This parameter gives the Parasolid version number used for saving Parasolid files. For example, V150 means to save in Parasolid version 15.0 format. V0 means the Parasolid version used to compile the AUI. { V0 / V80 / V90 / V91 / V100 / V110 / V111 / V120 / V121 / V130 / V140 / V150 / V160} Notes 1)
One important use of parameters DRAWTEXT, DRAWLINES, DRAWFILLS is when making plots in black and white for reports. In this case you might use DRAWTEXT = INVERSE, DRAWLINES = INVERSE, DRAWFILLS = GRAY.
2)
The drawing parameters apply both to graphics as displayed on the screen and to graphics as produced using SNAPSHOT or MOVIESAVE (see Section 3.3).
3)
One use of DRAWFILLS = SATURATED is to speed up shaded color image drawing, especially using X Window System graphics; all shades of each color are converted to the same color, resulting in significantly fewer color changes.
4) Example of a session file that will not work unless ZONECOPY = YES: * LOADPORTHOLE OPERATIO=CREATE FILE=... * MESHPLOT MESHSTYL=DEFAULT ZONENAME=WHOLE_MODEL RESPONSE=DEFAULT, MODELDEP=DEFAULT VIEW=DEFAULT MESHWIND=DEFAULT PLOTAREA=DEFAULT, SUBFRAME=DEFAULT ELDEPICT=DEFAULT NODEDEPI=DEFAULT, BOUNDEPI=DEFAULT GPDEPICT=DEFAULT GLDEPICT=DEFAULT, GSDEPICT=DEFAULT GVDEPICT=DEFAULT MESHREND=DEFAULT, MESHANNO=DEFAULT FRONDEPI=DEFAULT CONDEPIC=DEFAULT, VSDEPICI=DEFAULT CRACKDEP=DEFAULT RESULTCO=DEFAULT * NODEDEPICTIO NAME=MESHPLOT00001 SYMBOLPL=YES SYMBOL=’@C[1,5]’, SYMBOLCO=GREEN SYMBOLSI=0.150000005960000 UNITSYMB=CM NUMBER=NO, NUMBERCO=GREEN NUMBERSI=0.250000000000000 UNITNUMB=CM @STARTMODIFY @ENDMODIFY * MESHPLOT NAME=MESHPLOT00001 MESHSTYL=DEFAULT ZONENAME=MESHPLOT00001, RESPONSE=MESHPLOT00001 MODELDEP=MESHPLOT00001 VIEW=MESHPLOT00001, MESHWIND=MESHPLOT00001 PLOTAREA=MESHPLOT00001,
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Chap. 4 Interface control and editing SUBFRAME=MESHPLOT00001 NODEDEPI=MESHPLOT00001 GPDEPICT=MESHPLOT00001 GSDEPICT=MESHPLOT00001 MESHREND=MESHPLOT00001 FRONDEPI=MESHPLOT00001 VSDEPICI=MESHPLOT00001 RESULTCO=MESHPLOT00001
The second mesh plot requires a zone name MESHPLOT00001; this zone name is produced by the first MESHPLOT command by a copy. Notice that the initial mesh plot works regardless of the value of CONTROL ZONECOPY. 5) Example of commands that work unexpectedly unless ZONECOPY = NO: MESHPLOT ZONE=PART1 ACTIVEZONE CLEAR ‘PART1’ DATAEND LINE STRAIGHT 1 1 2 REGENERATE We expect that the REGENERATE command will draw line 1, as line 1 has been added to active zone PART1 and the mesh plot contains zone PART1. However the REGENERATE command will only draw line 1 if CONTROL ZONECOPY = NO. Auxiliary commands LIST CONTROL Lists the values of the parameters set by the CONTROL command.
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UNDO
UNDO
Sec. 4.2 Editing
NUMBER
UNDO cancels the effects of previous commands. UNDO is possible only if CONTROL UNDO is greater than zero. See Section 4.1 for a description of the CONTROL command. The UNDO command can itself be undone by REDO (described in this section). NUMBER [1] The number of previous commands to be undone. The maximum possible number of previous commands that can be undone is set by CONTROL UNDO. However, the actual number of previous commands that can be undone may be less than this.
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Chap. 4 Interface control and editing
REDO
REDO
NUMBER
REDO cancels the effects of previous UNDO commands (described in this section). It can be used only if the previous command was either UNDO or REDO. The REDO command can be followed by the UNDO command to cancel the REDO. NUMBER The number of previous UNDO commands to be undone.
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Chapter 5 Control data
FEPROGRAM
FEPROGRAM
Sec. 5.1 General
PROGRAM
FEPROGRAM specifies the finite element analysis program to be used to solve the problem described by the model database. PROGRAM The finite element analysis program name. The following choices are available: ADINA
For displacement and stress analysis.
ADINA-T
For heat transfer analysis.
ADINA-F
For fluid flow and heat transfer analysis.
[ADINA]
Auxiliary commands LIST FEPROGRAM Lists the currently selected finite element analysis program.
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HEADING
Chap. 5 Control data
HEADING
STRING
HEADING specifies a title for the problem described by the model database. STRING [‘*** NO HEADING DEFINED ***’] The problem heading, input as a string of up to 80 characters (including blank spaces) enclosed within apostrophes (‘). Auxiliary commands LIST HEADING Lists the current problem heading.
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MASTER defines the data controlling the execution of the analysis program ADINA. ANALYSIS Selects the category of analysis to be performed.
[STATIC]
STATIC
Static analysis.
DYNAMIC-DIRECT-INTEGRATION
Dynamic analysis.
FREQUENCIES
Frequency / mode-shape calculation.
BUCKLING-LOADS
Linearized buckling load calculation.
MODAL-TRANSIENT
Mode superposition for time integration of modal response.
MODAL-PARTICIPATION-FACTORS Calculation of modal participation factors for subsequent response spectrum, harmonic, or random analyses. MODAL-STRESSES
Calculation of modal stresses.
MODEX [EXECUTE] Selects the execution mode of the analysis. {CHECK/EXECUTE/RESTART/RESULTS}
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CHECK
ADINA checks the data without executing.
EXECUTE
ADINA checks the data and executes.
RESTART
ADINA performs a restart, reading data from a previous run, checks the data and executes.
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
MASTER
RESULTS
Sec. 5.1 General
ADINA performs result-recovery.
TSTART [0.0] Solution start time. For a restart run (MODEX = RESTART) TSTART must equal a solution time at which data was saved from a previous run. IDOF [000000] Master degree of freedom code. A six digit integer, where each digit indicates either an allowed (0) or a deleted (1) degree of freedom. A degree of freedom deleted by this parameter is deleted from the entire model. The digits correspond to the following degrees of freedom: Digit 1: X-translation (a-translation for a skew system). Digit 2: Y-translation (b-translation for a skew system). Digit 3: Z-translation (c-translation for a skew system). Digit 4: X-rotation (a-rotation for a skew system). Digit 5: Y-rotation (b-rotation for a skew system). Digit 6: Z-rotation (c-rotation for a skew system). The default is for all degrees of freedom to be active. Note: The directions of rotational degrees of freedom at a shell element mid-surface node with a local reference system depend on the orientation of the director vector or element normal vector, as applicable. Note: Preceding zeroes may be omitted, i.e., IDOF = 111 is equivalent to IDOF = 000111. OVALIZATION [NONE] Pipe element nodes can have additional ovalization and warping degrees of freedom, as selected by the following options: NONE
All ovalization and warping degrees of freedom are deleted.
IN-PLANE
Only the 3 ovalization and 3 warping degrees of freedom corresponding to in-plane loading are admissible.
OUT-OF-PLANE
Only the 3 ovalization and 3 warping degrees of freedom corresponding to out-of-plane loading are admissible.
ALL
All 6 ovalization and 6 warping degrees of freedom are admissible.
FLUIDPOTENTIAL [AUTOMATIC] Selects the fluid potential degree of freedom. If there are elements in groups of type FLUID2 or FLUID3 with a potential-based formulation, this degree of freedom is automatically selected. {AUTOMATIC/YES/NO}
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MASTER
Chap. 5 Control data
CYCLICPARTS [1] The number of cyclic symmetric parts of the main structure. If the value is greater than or equal to 2 then a cyclic symmetric analysis is performed. The maximum number of cyclic symmetric parts allowed is 999. CYCLICPARTS = 1 indicates no cyclic symmetry. IPOSIT [STOP] Specifies the preferred behavior of ADINA when a zero or negative diagonal element is encountered, i.e. when the system matrix is not positive definite. STOP
ADINA may terminate, see note below.
CONTINUE
ADINA continues execution.
Note: The selection IPOSIT = STOP may be overridden by ADINA, as follows: IPOSIT = STOP Linear analysis: ADINA stops if the stiffness matrix is not positive definite, except when potential-based fluid elements are in use. Non-linear analysis: ADINA stops if the stiffness matrix is not positive definite, unless: - the automatic load-displacement (LDC) option is being used, or - the automatic time-stepping (ATS) option is being used, or - the element birth/death option is used, or - potential-based fluid elements are being used, or - a contact analysis is being performed. IPOSIT = CONTINUE ADINA will always continue execution. If an exact zero pivot is encountered, ADINA assigns a very large number to the diagonal term, effectively attaching a very stiff spring to the degree of freedom. If the stiffness matrix is not positive definite in linear analysis, this usually means that the problem is not well defined (e.g. insufficient restraint). Use of IPOSIT = CONTINUE in such cases can give misleading results. REACTIONS [YES] Indicates whether reaction forces and moments corresponding to fixed or prescribed degrees of freedom are evaluated and printed. {NO/YES/SELECTED/SUM-SELECTED} NO
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No reaction forces and moments corresponding to fixed or prescribed degrees of freedom are evaluated and printed.
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MASTER
Sec. 5.1 General
YES
All reaction forces and moments corresponding to fixed or prescribed degrees of freedom are evaluated and printed.
SELECTED
Reaction forces are printed for nodes selected by command REACTION-NODES.
SUM-SELECTED
The sum of reaction forces for nodes selected by command REACTION-NODES are printed.
INITIALSTRESS [NO] Indicates whether the initial strains input at nodes are to be interpreted by ADINA as the corresponding initial stresses. {NO/YES/DEFORMATION} NO
Initial strains at nodes are not interpreted as initial stresses.
YES
Initial strains at nodes are interpreted as initial stresses, but stresses do not result in deformation.
DEFORMATION
Nodal initial strains are to be interpreted as initial stress which result in deformation.
FSINTERACTION Determines whether the analysis involves fluid-structure interaction. {YES/NO}
[NO]
Note: FSINTERACTION = YES is automatically set if FSBOUNDARY is used. IRINT Frequency of saving ADINA results to restart file. >0
Restart file overwritten every IRINT timesteps.
<0
Restart file appended every IRINT timesteps.
DEFAULT
[DEFAULT]
Number of steps in first time step block (see TIMESTEP ) for explicit timestepping (see ANALYSIS DYNAMIC-DIRECT-INTEGRATION ). 1 otherwise.
CMASS [NO] Controls whether the total mass, total volume, moments and products of inertia, centroid, and center of mass are calculated by ADINA for each element group. {YES/NO} SHELLNDOF [AUTOMATIC] Specifies the default number of degrees of freedom to be associated with shell midsurface nodes. This default may be overridden by SHELLNODESDOF, which specifies the number of
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MASTER
Chap. 5 Control data
degrees of freedom for shell midsurface nodes. 5 or FIVE
Shell midsurface nodes will have 3 translation degrees of freedom (global or skew) together with two rotation degrees of freedom corresponding to a local midsurface coordinate system – see SHELLNODESDOF.
6 or SIX
Shell midsurface nodes will have 3 translation and 3 rotation degrees of freedom corresponding to the global or assigned skewsystem.
0 or AUTOMATIC
Shell midsurface nodes will have five degrees of freedom, unless modeling considerations, determined automatically, such as branch shell structures or direct specification of rotation degrees of freedom (see SHELLNODESDOF ), require that six degrees of freedom be employed.
AUTOMATIC
[OFF, (FSINTERACTION=NO)] [ATS, (FSINTERACTION=YES)] Selects a method of automatic incrementation control during analysis. {OFF/ATS/LDC/ TLA/TLA-S} OFF
No automatic incrementation; user-defined time step sequence is followed.
ATS
Automatic time step control is enabled – see command AUTOMATIC TIME-STEPPING.
LDC
Automatic load-displacement control is enabled – see command AUTOMATIC LOAD-DISPLACEMENT.
TLA
The program ignores any time step and time function specified. Instead, 50 time steps of size 0.2 are used with a linear ramp time function (100% load at time of 10.0), and following settings are used. - ATS with an acceleration scheme is used - maximum number of equilibrium iterations = 30 - line search is used - limits maximum incremental displacement in each iteration to 5% of largest model length
TLA-S
Total load application with stabilization. In addition to TLA settings, the following stabilization settings are used. - stiffness matrix stabilization factor of 1.0e-10 is used - low-speed dynamics option is used - contact damping is used
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MASTER
Sec. 5.2 Analysis details
See command AUTOMATIC TOTAL-LOAD-APPLICATION for changing the settings used in the TLA or TLA-S scheme. SOLVER [SPARSE] Selects the type of solution algorithm used to solve the equilibrium equation system. {SKYLINE/ITERATIVE/SPARSE/MULTIGRID/3D-ITERATIVE/NONSYM-SP} SKYLINE
A skyline direct solution algorithm (active column Gauss elimination) is used.
ITERATIVE
An iterative solution (incomplete Cholesky preconditioned conjugate gradient method) is used.
SPARSE
A sparse-matrix solver is used.
MULTIGRID
A multigrid solver is used.
3D-ITERATIVE
An iterative solver is used for models with relatively large number of 3-D higher order elements.
NONSYM-SP
A nonsymmetric sparse solver is used.
Note: See SOLVER ITERATIVE for input of parameters controlling the operation of the iterative solver. CONTACT-ALGORITHM [CONSTRAINT-FUNCTION] Selects the default algorithm used for contact groups. See the Theory and Modeling Guide for further details. {CONSTRAINT-FUNCTION/SEGMENT-METHOD/RIGID-TARGET} It is recommended to use the CONTACT-CONTROL command’s CONTACT-ALGORITHM parameter instead for this purpose as this parameter may be obsolete in future releases. TRELEASE [0.0] When the element death option is utilized, an element will “die” (i.e., have zero stiffness contribution) at a given time TDEATH associated with the element. By default (TRELEASE = 0.0) an element “dies” immediately when the solution time reaches TDEATH. However, when TRELEASE > 0.0, an element will “die” over the solution time interval from TDEATH to (TDEATH + TRELEASE). {≥ 0.0} RESTART-LDC Determines whether or not the load vector is transferred to a restart run. NO
[NO]
The load vector is not written at the end of an analysis, nor is it read as an external load vector in a restart analysis.
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Chap. 5 Control data
YES
MASTER
The load vector is written at the end of an analysis, and it is read as an external load vector in a restart analysis.
FRACTURE Controls whether or not the analysis involves fracture mechanics. {YES/NO}
[NO]
LOAD-CASE [NO] Controls whether or not multiple load cases are used in a linear analysis. If LOAD-CASE = SIMPACK, the SIMPACK interface will be used. {YES/NO/SIMPACK} LOAD-PENETRATION [NO] Controls whether or not load penetration is employed in the analysis, whereby distributed (pressure) load is transferred upon element death. {YES/NO} MAXSOLMEM This parameter is obsolete. MTOTM This parameter is obsolete. RECL This parameter is obsolete. SINGULARITY-STIFFNESS [YES] Assign “drilling” stiffness to rotational degrees of freedom with zero stiffness associated with shell nodes connected to rigid links, beams, or pipes. {NO/YES} STIFFNESS-FACTOR [1E-4] Stiffness factor value used when SINGULARITY-STIFFNESS = YES. The actual stiffness used is obtained by multiplying this factor by the rotational stiffness at the shell nodes. MAP-OUTPUT [NO] Indicates whether the mapping file is written. If the file is written, the frequency follows the frequency of the porthole file. {NO/YES/REMESH/NODAL/ZOOM-INITIAL/ZOOMANALYSIS/FSB} NO
No mapping file output.
YES
ADINA will output mapping file.
REMESH
AUI read nodal deformation file to recreate geometry for remeshing.
NODAL
ADINA will output mapping file only for nodal results. This type of
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MASTER
Sec. 5.2 Analysis details
mapping file can be used as initial conditions for a subsequent analysis using a different mesh. ZOOM-INITIAL ADINA will output mapping file for use by a zoom model. ZOOM-ANALYSIS ADINA will perform analysis for a zoom model. A mapping file created in a previous analysis (with MAP-OUTPUT = ZOOM-INITIAL) is required. If the boundary of the zoom model coincides with the boundary of the original model, the ZOOM-BOUNDARY command must also be specified (see figure at ZOOM-BOUNDARY command). FSB
MASTER command will read previous mapping file and update FSI-BOUNDARY with deformed coordinate. Note that this option is only used with FSINTERACTION = YES and the adaptive-mesh option is used in the ADINA-F model.
MAP-FORMAT Indicates whether the mapping file is written in text or binary format. {YES/NO} NO
binary file.
YES
text file.
NODAL-DEFORMATION-FILE Specifies the name of the nodal deformation file. If MAP-OUTPUT=REMESH AUI will read this file. When the program reads the nodal deformation file to recreate geometry for remeshing, the following actions are taken: - all elements and their nodes are deleted. - all volumes and surfaces are deleted. - all lines which contain nodes are modified such that the line now passes through the new nodal positions. Note: MAP-OUTPUT=REMESH is currently restricted only for 2-D problem where the model uses only AUI native geometry (i.e. lines and surfaces). POROUS-COUPLING Porous-coupling. {NO/YES}
[NO]
ZOOM-LABEL Current zoom model label number .
[1]
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Chap. 5 Control data
MASTER
AXIS-CYCLIC [0] Label number of cyclic symmetry axis defined by axis-rotation command. Default AXISCYCLIC = 0 means use global X axis. PERIODIC Specifies whether periodic loads are to be applied to cyclic parts. {NO/YES}
[NO]
NO
different loads are used for different cyclic parts.
YES
the load applied on the first cyclic part is rotated about the cyclic axis and applied to the other cyclic parts. Unlike basic cyclic symmetry analysis, a periodic symmetry analysis can be nonlinear. It can also be used with explicit dynamic time integration.
VECTOR-SHELL Flag for calculation of shell-vector direction GEOMETRY
shell-vector direction from surface/face normal direction
ELEMENT
shell-vector direction from element
[GEOMETRY]
EPSI-FIRST [NO] Indicates whether the analysis is first solved with the applied initial strain before loads are applied. If EPSI-FIRST=YES, then the automatic time stepping (ATS) method can also be used to scale the initial strains in case the solution fails to converge when the full initial strains are applied in one step.{NO/YES} STABILIZE [AUTOMATIC] The flag to set the option to stabilize the stiffness matrix. {AUTOMATIC/NO/YES} AUTOMATIC
Automatically use stabilization if the ratio of the maximum to minimum diagonals of the factorized stiffness matrix is greater than 1.0E11.
NO
Do not use stabilization.
YES
Use stabilization.
STABFACTOR [1.0E-10] The stabilization factor used if STABILIZE when is set to YES or AUTOMATIC. RESULTS [PORTHOLE] Specifies the output option for the results. {PORTHOLE/OP2/OP2+PORT/UNV/ UNV+PORT}
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MASTER
Sec. 5.2 Analysis details
PORTHOLE
ADINA porthole file format
OP2
Nastran .OP2 file format
OP2+PORT
Nastran OP2 file and ADINA porthole file formats
UNV
I-deas universal file format
UNV+PORT
I-deas universal file and ADINA porthole file formats
FEFCORR Perform fixed-end-force correction for beams. {YES/NO}
[NO]
BOLTSTEP The number of steps to iterate for calculation of bolt force.
[1]
EXTEND-SSCURVE [YES] Automatically extend the stress-strain curve to strain value of 100.0 by default. {NO/YES} CONVERT-SSVAL [NO] Option to convert stress-strain curve input from engineering stress/strain to true stress/ strain. {NO/YES} The plastic-multilinear, multilinear-plastic-creep and the multilinear-plastic-creep material models are affected by the setting of this parameter as follows: When CONVERT-SSVAL=NO, stressi and straini are interpreted as true stresses and strains. Stresses and strains entered in the SCURVE command are also intrepreted as true stresses and strains. When CONVERT-SSVAL=YES, stressi and straini are interpreted as engineering stresses and strains. Stresses and strains entered in the SCURVE command are also intrepreted as engineering stresses and strains. DEGEN [YES] Indicator for spatial isotropy correction of degenerate 8-node 2D elements or 20-node 3D elements. {YES/NO/UNUSED} TMC-MODEL [NO] Specifies whether the model contains thermal properties and the type of thermal-mechanical coupling analysis. {NO/ONEWAY/ITERATIVE/HEAT}
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MASTER
Chap. 5 Control data
NO
No heat transfer analysis is performed by the program.
ONEWAY
The program performs first a heat transfer step to calculate temperatures, then a stress/displacement (mechanical) step. Note that the heat transfer step size can be different than the mechanical step size. Also, heat transfer can be a transient analysis and mechanical analysis can be a static analysis (or any combination thereof).
ITERATIVE
An iterative thermo-mechanical coupling is used. The program iterates between heat transfer and mechanical solutions. The same step size is used in both cases. A solution is obtained if both temperature and displacement results converge. Note that the option is available for contact with friction, or thermo-plastic and rubber materials only.
HEAT
The program ignores any structural loads and boundary conditions and performs a pure heat transter analysis.
ENSIGHT-OUTPUT [NO] Indicates whether an EnSight output file is written and which format is used. If the file is written, it will be written at end of each time step when the porthole file is written. {NO/UNFORMATTED/FORMATTED} NO
No EnSight output file is written
UNFORMATTED
An unformatted EnSight output file is written
FORMATTED
A formatted EnSight output file is written
Auxiliary commands LIST MASTER
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DOF-ACTIVE
Sec. 5.2 Analysis details
DOF-ACTIVE nodei
dofi
The command is used to identify the active degree of freedom (DOF) of reduced model. It is only used when LOAD-CASE = SIMPACK in the MASTER command. nodei Node label number. dofi Type of DOF. {X-TRANSLATION/Y-TRANSLATION/Z-TRANSLATION/R-ROTATION/Y-ROTATION/Z-ROTATION}
TMC-CONTROL defines parameters that control TMC analysis. ANALYSIS Selects the type of heat transfer analysis to be performed. {STEADY-STATE/TRANSIENT} STEADY-STATE
Steady-state analysis.
TRANSIENT
Time dependent analysis.
[STEADY-STATE]
TIMESTEP [CURRENT] Flag to specify the time step for heat transfer analysis. {CURRENT/SPECIFIED} CURRENT
Use the same time step as ADINA.
SPECIFIED
Specify the time step using the TSTEP-NAME parameter.
TSTEP-NAME Specifies the time step for heat transfer analysis. It is used only when TIMESTEP = SPECIFIED. AUTOMATIC Enables automatic incrementation control during analysis. {OFF/ATS}
[OFF]
OFF
No automatic incrementation, user-defined timestep sequence is followed.
ATS
Automatic timestep control is enabled, see MAXSUBD parameter below.
SOLVER [SPARSE] Selects the type of solution algorithm used to solve the equilibrium equation system. {SPARSE/ITERATIVE} SPARSE
A sparse-matrix solver is used.
ITERATIVE
An iterative solution (incomplete Cholesky preconditioned conjugate gradient method) is used.
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TMC-CONTROL
Sec. 5.2 Analysis details
Note: See command TMC-SOLVER ITERATIVE for input of parameters controlling the operation of the iterative solver. HEAT-MATRIX [CONSISTENT] Selects the type of heat capacity matrix to be used in transient analysis. {CONSISTENT/ LUMPED} CONSISTENT
Consistent heat capacity matrix.
LUMPED
Lumped (diagonalized) heat capacity matrix.
METHOD [BACKWARD-EULER] Time integration method used in transient analysis. {BACKWARD-EULER / FORWARDEULER / TRAPEZOIDAL / ALPHA / ALPHA / COMPOSITE} BACKWARD-EULER
Euler backward integration.
FORWARD-EULER
Euler forward integration.
TRAPEZOIDAL
Trapezoidal rule.
ALPHA
Alpha-family method.
COMPOSITE
Bathe composite method.
MAXSUBD [10] Specifies the maximum permitted subdivision of any given timestep when AUTOMATIC = ATS, i.e., for a time step of magnitude ∆T, the algorithm will not attempt to subdivide below a time step of magnitude ∆T/2MAXSUBD. ALPHA Time integration parameter for METHOD=ALPHA. {0 ≤ ALPHA ≤ 1.0}
[1.0]
TSTART [DEFAULT] Start time of the heat transfer solution. DEFAULT indicates a start time that is the start time for the structural solution. {DEFAULT / TSTART ≥ 0.0} GAMMA Coefficient used for the Bathe composite time integration method. {0.0 < GAMMA < 1.0}
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Chap. 5 Control data
TEMP-CUTOFF If TEMP-CUTOFF = YES, temperature CUT-OFF will be used. {NO/YES} CUTOFF Temperature will be cut-off above CUT-OFF.
TMC-CONTROL
[NO] [1.0D30]
TEMP-RELAX Temperature relaxation factor to overcome convergence difficulties. {0.0 ≤ TEMP-RELAX ≤ 1.0}
ANALYSIS DYNAMIC-DIRECT-INTEGRATION specifies time integration parameters for a dynamic, direct time-integration, analysis. METHOD [NEWMARK] Selects the method to be used for direct time integration, see Theory and Modeling Guide. {NEWMARK/CENTRAL-DIFFERENCE/WILSON/COMPOSITE} NEWMARK
Newmark method.
CENTRAL-DIFFERENCE
Central difference method (explicit analysis).
WILSON
Wilson-θ method.
COMPOSITE
Bathe composite method.
Note: For the central-difference method: - substructures and cyclic symmetry cannot be used; - a lumped mass matrix is used automatically; - there are further restrictions on analysis features, material models and element settings. See the Theory and Modeling Guide for more details. Note: The Wilson-θ method cannot be used for nonlinear analysis. DELTA ALPHA Coefficients for the Newmark method. {DELTA ≥ 0.5}{ALPHA > 0.0} The following choices are often employed:
[0.5] [0.25]
DELTA = 0.5, ALPHA = 0.25
The constant-average-acceleration scheme (also termed the trapezoidal rule).
DELTA = 0.5, ALPHA = 0.5
Good for contact-impact problems.
Note: The Newmark method is unconditionally stable in linear analysis, if: DELTA ≥ 0.5, ALPHA ≥ 0.25 × (DELTA + 0.5)2 THETA Coefficient for the Wilson-θ method. {1.39 ≤ THETA ≤ 2.01}
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ANALYSIS DYNAMIC-DIRECT-INTEGRATION
Sec. 5.2 Analysis details
TIMESTEP [TOTALTIME] Indicates the method of time step selection for explicit analysis (i.e., METHOD = CENTRALDIFFERENCE). {USER/AUTOMATIC/TOTALTIME} USER
User defined timesteps. (See TIMESTEP )
AUTOMATIC
ADINA automatically calculates the time step magnitude in explicit analysis based on stability considerations. The total number of time steps specified in the TIMESTEP command will be used.
TOTALTIME
The magnitude of the timesteps is calculated automatically by the program. The analysis runs until the total time specified in the TIMESTEP command is reached. The number of steps specified in the TIMESTEP command determines how often results are saved to the porthole file.
NCRSTEP [1] Defines how often the time step magnitude is updated in explicit analysis (the time step magnitude is updated every NCRSTEP step(s)). This parameter is not used if TIMESTEP=USER. {NCRSTEP = 1, 2, 3, ...} CRSTEP [0.0] Factor used to scale the calculated time step in transient explicit analysis. This parameter is not used if TIMESTEP=USER. {0.0 ≤ CRSTEP ≤ 4.0} For the default value CRSTEP = 0.0, CRSTEP will be set to 1.0 always. MASS-SCALE [1.0] Specifies the factor to scale the mass (densities) of the entire model (at the beginning of the analysis) to increase the critical time step size required for stability when the explicit time integration scheme is used. See caution below. {≥ 1.0} DTMIN1 [0.0] The minimum time step size used to determine if mass scaling will be applied to elements (at the beginning of the analysis) whose critical time step size is smaller than DTMIN1. The amount of mass scaling is calculated for each element so that the critical time step size is equal to DTMIN1. See caution below. {≥ 0.0} DTMIN2 [0.0] The minimum time step size used to determine if an element will be removed in an explicit time integration analysis. In explicit time integration, the smaller an element size is, the smaller will
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ANALYSIS DYNAMIC-DIRECT-INTEGRATION
the critical time step size be. If the critical time step size for an element is smaller than DTMIN2, the element will be removed in the analysis. See caution below. {≥ 0.0} Notes: — MASS-SCALE, DTMIN1 and DTMIN2 may be used together. — DTMIN1 and DTMIN2 are applied after MASS-SCALE is applied. — If DTMIN1 and DTMIN2 are both used, DTMIN1 should be greater than DTMIN2. If DTMIN2 ≥ DTMIN1 is specified, DTMIN1 will be ignored. CAUTION: Specifying MASS-SCALE > 1.0, DTMIN1 > 0.0 or DTMIN2 > 0.0 may change the model significantly. Hence, extra care should be exercised in examining the results when any of these parameters are used. GAMMA Coefficient for the Bathe composite method. {0.0 < GAMMA < 1.0} Note:
[0.5]
The Bathe composite method uses Newmark coefficients with the additional constant GAMMA. It is recommended to use the default value of GAMMA (i.e., 0.5).
Auxiliary commands LIST ANALYSIS Lists the data for the current analysis option.
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FREQUENCIES specifies control data for a frequency solution to be carried out for the structure linearized at time TSTART. In order to input data via this command the MASTER command ANALYSIS parameter should have been previously set to FREQUENCIES, MODAL-TRANSIENT, MODAL-PARTICIPATION-FACTORS or MODAL-STRESSES. METHOD [SUBSPACE-ITERATION] Specifies the method of frequency calculation. {DETERMINANT-SEARCH/ SUBSPACE-ITERATION/INPUT/LANCZOS-ITERATION} Please consult the Theory and Modeling Guide for a further description of these methods. The selection METHOD = INPUT will cause ADINA to read frequencies and mode-shapes from file, e.g., for use in a subsequent mode superposition analysis; all other parameters of this command are ignored. NEIGEN [1] The number of frequencies and corresponding mode shapes to be calculated. The actual number of frequencies calculated may be reduced whenever the maximum, specified either by the cut-off frequency (CUTOFF) or the upper bound on the solution interval (FMAX – for the subspace-iteration method), has been exceeded. NMODE [0] The number of mode shapes to be printed in the results output file. Frequency results are always printed. {≤ NEIGEN} IPRINT [NO] Specifies whether or not intermediate solution information is printed. Such information may be of interest in tracing the solution behavior. {YES/NO} RIGID-BODY [NO] Specifies whether or not rigid-body modes are allowed. Should be used when the lowest frequency may be zero, or any part of the model would be insufficiently supported if all contact, mesh glueing and generalized constraints are removed. {YES/NO} RSHIFT [0.0] The rigid body mode shift to be applied when RIGID-BODY = YES. RSHIFT = 0.0 will result in a value being automatically determined by the analysis program. {≤ 0.0}
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FREQUENCIES
Sec. 5.2 Analysis details
CUTOFF [1.0E8] The cut-off circular frequency (unit = radians/time). The frequency calculation is stopped if frequency CUTOFF has been exceeded. NITEMM [24 or 60] The maximum number of iterations per eigenpair (frequency, mode shape) allowed during solution. Default = 60 if METHOD = DETERMINANT; otherwise, default = 24. NVECTOR [DEFAULT] The number of iteration vectors to be used simultaneously by the subspace-iteration method. DEFAULT = min(2×NEIGEN, NEIGEN+8) = 16
if INTERVAL = NO if INTERVAL = YES
STURM-CHECK [NO] Specifies whether or not a Sturm-sequence check is to be performed to verify that all the lowest frequencies have been found by the subspace-iteration method. {YES/NO} ACCELERATE [NO] Specifies whether or not acceleration schemes (shifting and overrelaxation) are to be employed during subspace-iteration. Note that if acceleration is applied, then the Sturm-sequence check is automatically applied. Furthermore, if NVECTOR < min(2×NEIGEN, NEIGEN+8) then acceleration is always used. {YES/NO} TOLERANCE [DEFAULT] The convergence tolerance used by the subspace-iteration and the Lanczos-iteration methods in the iteration for frequency values. DEFAULT = 1.0E-6 if INTERVAL = NO and METHOD = SUBSPACE-ITERATION = 1.0E-10if INTERVAL = YES and METHOD = SUBSPACE-ITERATION = 1.0E-9 if METHOD = LANCZOS-ITERATION STARTTYPE [LANCZOS] Specifies the method of generating starting vectors for the subspace-iteration method. STANDARD LANCZOS
Standard starting vectors are used. The Lanczos method is used to generate starting vectors.
NSTVECT [0] The number of user-provided starting iteration vectors for the subspace-iteration method. The NSTVECT vectors, read from file, replace the first NSTVECT starting vectors generated by the analysis program.
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FREQUENCIES
INTERVAL [NO] Specifies whether or not the lowest frequency calculation by the subspace-iteration method and the Lanczos iteration method is confined to a specified interval (FMIN, FMAX). {YES/ NO} FMIN [0.0] If INTERVAL = YES, FMIN gives the lower bound frequency (unit = radians/time) of the interval in which the subspace-iteration method and the Lanczos iteration method calculates the lowest frequencies. FMAX [DEFAULT] If INTERVAL = YES, FMAX gives the upper bound frequency (unit = radians/time) of the interval in which the subspace-iteration method and the Lanczos iteration method calculates the lowest frequencies. DEFAULT = CUTOFF. MODALSTRESSES [NO] Indicates whether or not to calculate modal stresses for post-processing. {YES/NO} STATIC [NO] Indicates whether or not to perform static analysis load-steps following the frequency/ modeshape calculation. {YES/NO} NSHIFT [AUTO] Specifies whether to use automatic shifting procedure for the Lanczos-iteration method. When the number of frequencies (NEIGEN) to be calculated is large, using the automatic shifting procedure can reduce the computation time significantly. If NSHIFT=AUTO, then the procedure is used if (NSHIFT-BLOCK * 2) ≤ NEIGEN. Currently, this procedure is applicable for frequency calculations for potential-based fluid only. {AUTO/YES/NO} NSHIFT-BLOCK [50] Specifies the number of frequencies to be calculated for each shift in the Lanczos-iteration method. {>0} Note: The parameters NVECTOR, ACCELERATE, STARTTYPE, and NSTVECT are applicable only to the subspace-iteration method. They are ignored by both the determinant-search and Lanczos methods. The parameters TOLERANCE, INTERVAL, FMIN, FMAX and STURM-CHECK are also ignored by the determinant-search method. Auxiliary commands LIST FREQUENCIES Lists the current setting of parameters for a frequency solution if previously enabled via the command MASTER ANALYSIS = FREQUENCIES.
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BUCKLING-LOADS specifies control data for evaluating static buckling loads and corresponding mode shapes based on the linearized state of stress and deformation of the model at time TSTART+∆t, following an evaluation of the static response at the same time, i.e., after the first step of the analysis. In order to input data via this command, the MASTER command ANALYSIS parameter should have been previously set to BUCKLING-LOADS. The restart option may be used to perform a buckling analysis for the linearized system at step “n”, where n > 1. The first run solves for the static response after (n-1) steps. The restart run then enables the buckling analysis to solve for the buckling response linearized at step “n”. The solution of the eigenvalue problem required for the determination of critical load factors employs the subspace-iteration or Lanczos-iteration method (see FREQUENCIES). The Sturm-sequence check is applied to verify that the lowest required buckling loads have been evaluated. The acceleration (shifting and over-relaxation) schemes are used if the subspace-iteration method is chosen. NEIGEN [1] The number of lowest positive critical buckling loads (i.e., acting in the direction of the applied loads for the first solution step), and corresponding mode shapes to be calculated. NMODE [0] The number of mode shapes to be printed in the results output file. The critical buckling load factors are always printed. {≤ NEIGEN} IPRINT [NO] Specifies whether or not intermediate solution information is printed. Such information may be of interest in tracing the solution behavior. {YES/NO} NITEMM [40] The maximum number of iterations per eigenpair (frequency, mode shape) allowed during solution for the subspace-iteration method. NVECTOR [DEFAULT] The number of iteration vectors to be used simultaneously for the subspace-iteration method. {≥ 0} DEFAULT = NEIGEN*3 + 18
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BUCKLING-LOADS
Sec. 5.2 Analysis details
TOLERANCE [1.0E-6] The convergence tolerance used by the subspace-iteration method in the iteration for frequency values. STARTTYPE [LANCZOS] Specifies the method of generating starting vectors for the subspace-iteration method. STANDARD
Standard starting vectors are used.
LANCZOS
The Lanczos method is used to generate starting vectors.
NSTVECT [0] The number of user-provided starting iteration vectors for the subspace-iteration method. The NSTVECT vectors, read from file, replace the first NSTVECT starting vectors generated by the analysis program. MODALSTRESSES [NO] Indicates whether or not to calculate modal stresses for post-processing. {YES/NO} METHOD Buckling analysis method. {CLASSICAL/SECANT}
Auxiliary commands LIST BUCKLING-LOADS Lists the current setting of parameters for a buckling analysis if enabled via the command MASTER ANALYSIS = BUCKLING-LOADS.
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ANALYSIS MODAL-TRANSIENT
Chap. 5 Control data
ANALYSIS MODAL-TRANSIENT
NMODES ERROR-INTERVAL FREQUENCIES
ANALYSIS MODAL-TRANSIENT provides control data for a mode superposition analysis. NMODES Number of modes for a mode superposition analysis.
[0]
Note that when NMODES = 0 by default, the number of modal participation factors calculated by ADINA is the number of requested modes in the FREQUENCIES command. ERROR-INTERVAL [0] Interval of calculating error in external load representation in mode superposition analysis. 0 > 0
No external load error calculation. Calculate relative error at this interval of timesteps.
FREQUENCIES [YES] Indicates whether ADINA is to first perform a frequency analysis (in the same run). Otherwise the frequencies and mode shapes are assumed available, on file, from a previous analysis. See command FREQUENCIES for control of the frequency/mode-shape calculations. {YES/NO}
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Provides control data for a modal participation factor analysis. EXCITATION [GROUND-MOTION] Defines the type of excitation load. {GROUND-MOTION/APPLIED-LOAD} NMODES [0] Number of modes for a modal participation factor analysis. Note that when NMODES = 0 by default, the number of modal participation factors calculated by ADINA is the number of requested modes in the FREQUENCIES command. STATIC Indicates whether static load-step calculations are to be performed. {YES/NO}
[NO]
CORRECTION [NO] Indicates whether static-correction calculations are to be performed. Calculations of residual displacements, accelerations, forces, and stresses will be made to evaluate the contribution to the response from the remaining modes above NMODES included in a response spectrum analysis assuming this contribution is static, thus not dynamically amplified. {YES/NO} FREQUENCIES [YES] Indicates whether ADINA is to first perform a frequency analysis (in the same run). Otherwise the frequencies and mode shapes are assumed available, on file, from a previous analysis. See command FREQUENCIES for control of the frequency/mode-shape calculations. {YES/NO} DUSIZE [0.0] This parameter is used in nonlinear analysis to specify the size of the displacement perturbation used in calculating nonlinear modal stresses. The unit of DUSIZE is length. If DUSIZE=0.0, then ADINA computes the displacement perturbation factor automatically. If you specify DUSIZE, you should choose DUSIZE so that if the mode shapes are scaled to be of size DUSIZE, the deformations corresponding to the scaled mode shapes are small. When the analysis is not a restart analysis, or if the displacements at restart time TSTART are zero, it is recommended that you enter DUSIZE. This is because ADINA's automatic calculation can lead to very small or very large displacement perturbations. When the analysis is a restart analysis and the displacements at restart time TSTART are nonzero, ADINA's automatic calculation of DUSIZE is usually quite good, however you can also enter DUSIZE if desired. See the ADINA Theory and Modeling Guide, Section 6.2.4 for more information.
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ANALYSIS MODAL-STRESSES
ANALYSIS MODAL-STRESSES
FREQUENCIES DUSIZE
ANALYSIS MODAL-STRESSES provides control data for modal stress calculations. FREQUENCIES [YES] Indicates whether ADINA is to first perform a frequency analysis (in the same run). Otherwise the frequencies and mode shapes are assumed available, on file, from a previous analysis. See command FREQUENCIES for control of the frequency/mode-shape calculations. {YES/ NO} DUSIZE [0.0] This parameter is used in nonlinear analysis to specify the size of the displacement perturbation used in calculating nonlinear modal stresses. The unit of DUSIZE is length. If DUSIZE=0.0, then ADINA computes the displacement perturbation factor automatically. If you specify DUSIZE, you should choose DUSIZE so that if the mode shapes are scaled to be of size DUSIZE, the deformations corresponding to the scaled mode shapes are small. When the analysis is not a restart analysis, or if the displacements at restart time TSTART are zero, it is recommended that you enter DUSIZE. This is because ADINA's automatic calculation can lead to very small or very large displacement perturbations. When the analysis is a restart analysis and the displacements at restart time TSTART are nonzero, ADINA's automatic calculation of DUSIZE is usually quite good, however you can also enter DUSIZE if desired. See the ADINA Theory and Modeling Guide, Section 6.2.4 for more information.
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KINEMATICS defines the kinematic formulation. An individual element group may select a different formulation via the appropriate EGROUP command. DISPLACEMENTS SMALL
Small displacements and rotations are assumed.
LARGE
Large displacements and rotations are assumed.
STRAINS
[SMALL]
[SMALL]
SMALL
Small strains are assumed.
LARGE
Large strains are assumed.
Note: Large strains are only admissible for element groups of type TWODSOLID, THREEDSOLID and SHELL with certain material models — please refer to the descriptions of the MATERIAL parameter in the commands EGROUP TWODSOLID, EGROUP THREEDSOLID AND EGROUP SHELL. PRESSURE-UPDATE [NO] Specifies whether pressure correction terms are added to the shell stiffness matrix in frequency analysis. Note that this setting cannot be overridden at the element group level. {NO/YES} INCOMPATIBLE-MODES [AUTOMATIC] Specifies whether incompatible modes are included in formulation of 4-node 2D and shell elements and 8-node 3D elements. The default AUTOMATIC sets INCOMPATIBLE-MODES = NO for explicit analysis, and otherwise sets INCOMPATIBLE-MODES = YES. {AUTOMATIC/NO/YES} UL-FORMULATION [DEFAULT] Specifies the large strain formulation to be used for 2D solid, 3D solid and shell elements. {DEFAULT/ULH/ULJ} DEFAULT
ULJ is used if explicit transient analysis or rigid-target contact algorithm of version 8.3 is used. Otherwise, ULH is used.
ULH
Updated Lagrangian Hencky formulation is used.
ULJ
Updated Lagrangian Jaumann formulation is used.
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KINEMATICS
RIGIDLINK-6DOF [NO] Specifies whether all six degrees of freedom are active for a master node on a rigid link when the node is also attached to an element (e.g., 3D solid) where not all six degrees of freedom are active. {NO/ALL} NO
Only the active degrees of freedom of the attached element are assigned to the master node on a rigid link.
ALL
All six degrees of freedom are active for the master nodes of a rigid link.
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Sec. 5.3 Options
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MASS-MATRIX
Chap. 5 Control data
MASS-MATRIX
TYPE ETA
MASS-MATRIX selects the type of mass matrix to be used in dynamic analysis. For static analyses, the mass matrix type is used only in evaluating centrifugal and massproportional loads. See the Theory and Modeling Guide. TYPE Selects the type of mass matrix. LUMPED
Lumped (diagonalized) mass matrix.
CONSISTENT
Consistent mass matrix.
[CONSISTENT]
Note: The lumped mass matrix is always used in explicit dynamic analysis, and in substuctures. Note: The element integration orders specified for element groups do not affect the calculation of the mass matrix. ETA [DEFAULT] Multiplier (≥ 0.0) for the lumped rotational masses of all BEAM, ISOBEAM, PLATE, SHELL, and PIPE elements. ETA is applicable only if a dynamic analysis is to be performed with a lumped mass matrix, see Theory and Modeling Guide. DEFAULT = 0.0 1.0
for the NEWMARK or WILSON-θ integration method and for frequency analysis for the central difference (explicit) integration method.
Auxiliary commands LIST MASS-MATRIX Lists the current mass matrix type.
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RAYLEIGH-DAMPING
RAYLEIGH-DAMPING
Sec. 5.3 Options
ALPHA BETA
egroupi α i βi RAYLEIGH-DAMPING specifies coefficients which define a consistent damping matrix C as a linear combination of the system mass matrix M and the system stiffness matrix K, i.e., C = α ⋅ M + β ⋅ K + C conc + C gen
where M
= Total system mass matrix (lumped or consistent), including any specified concentrated masses.
K
= Stiffness matrix based on the elements in all element groups.
α, β
= Rayleigh damping factors.
Cconc
= Damping matrix contribution from concentrated dampers (see DAMPERS ).
Cgen
= Damping matrix contribution from GENERAL or SPRING elements.
See the Theory and Modeling Guide for further details on the use of the damping matrix. Different Rayleigh damping coeffients may be specified for individual element groups. The default coefficients are given by parameters ALPHA, BETA. ALPHA The Rayleigh damping factor α.
[0.0]
BETA The Rayleigh damping factor β.
[0.0]
Note: The specification of Rayleigh damping is ignored for both a frequency analysis and a mode superposition analysis. egroupi Label number of an element group. αi Raleigh damping factor α for element group egroupi.
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[ALPHA]
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βi Raleigh damping factor β for element group egroupi.
RAYLEIGH-DAMPING
[BETA]
Auxiliary commands LIST RAYLEIGH-DAMPING Lists the Rayleigh damping factors α, β. DELETE RAYLEIGH-DAMPING Sets the Rayleigh damping factors α, β to 0.0.
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MODAL-DAMPING
Sec. 5.3 Options
MODAL-DAMPING modei factori MODAL-DAMPING defines modal damping factors to be used in mode superposition analysis. modei The mode number. factori Damping factor for mode “modei”, representing the fraction of critical damping. For example, factori = 0.1 gives 10% damping for the mode. Note:
The mode superposition analysis option must be enabled for the data from this command to be considered. See MASTER.
Note:
At least NMODES damping factors should be given, where NMODES is the number of modes participating in the mode superposition analysis. See ANALYSIS MODAL-TRANSIENT.
Auxiliary commands LIST MODAL-DAMPING Lists the assigned modal damping factors. DELETE MODAL-DAMPING Deletes all modal damping factors.
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FAILURE MAXSTRESS defines a failure criterion of maximum stress type for SHELL elements (EGROUP SHELL) in conjunction with material models: ISOTROPIC, ORTHOTROPIC, THERMO-ISOTROPIC and THERMO-ORTHOTROPIC. See Theory and Modeling Guide for details. NAME [(current highest failure label number) + 1] Label number of the failure criterion to be defined. If the label number of an existing failure criterion is given, then the previous failure criterion definition is overwritten. SUBTYPE Indicates the stress/strain conditions. STRESS2
Plane stress.
STRESS3
General 3-D stress.
[STRESS2]
SIGAMT Maximum allowable tension stress in material a-direction.
[0.0]
SIGAMC Maximum allowable compression stress in material a-direction.
[0.0]
SIGBMT Maximum allowable tension stress in material b-direction.
[0.0]
SIGBMC Maximum allowable compression stress in material b-direction.
[0.0]
SIGCMT Maximum allowable tension stress in material c-direction.
[0.0]
SIGCMC Maximum allowable compression stress in material c-direction.
[0.0]
SIGABM Maximum allowable shear stress in the material ab-plane.
[0.0]
SIGACM Maximum allowable shear stress in the material ac-plane.
[0.0]
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FAILURE MAXSTRESS
Chap. 5 Control data
SIGBCM Maximum allowable shear stress in the material bc-plane.
[0.0]
Auxiliary Commands LIST FAILURE DELETEFAILURE
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FAILURE MAXSTRAIN defines a failure criterion of maximum strain type for SHELL elements ( EGROUP SHELL ) in conjunction with material models: ISOTROPIC, ORTHOTROPIC, THERMO-ISOTROPIC and THERMO-ORTHOTROPIC. See Theory and Modeling Guide for details. NAME [current highest failure label number) + 1] Label number of the failure criterion to be defined. If the label number of an existing failure criterion is given, then the previous failure criterion definition is overwritten. SUBTYPE Indicates the stress/strain conditions STRESS2
Plane stress.
STRESS3
General 3-D stress.
[STRESS2]
EPSAMT Maximum allowable tension strain in material a-direction.
[0.0]
EPSAMC Maximum allowable compression strain in material a-direction.
[0.0]
EPSBMT Maximum allowable tension strain in material b-direction.
[0.0]
EPSBMC Maximum allowable compression strain in material b-direction.
[0.0]
EPSCMT Maximum allowable tension strain in material c-direction.
[0.0]
EPSCMC Maximum allowable compression strain in material c-direction.
[0.0]
EPSABM Maximum allowable shear strain in the material ab-plane.
[0.0]
EPSACM Maximum allowable shear strain in the material ac-plane.
[0.0]
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FAILURE MAXSTRAIN
Chap. 5 Control data
EPSBCM Maximum allowable shear strain in the material bc-plane.
[0.0]
Auxiliary Commands LIST FAILURE DELETEFAILURE
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FAILURE TSAI-HILL
Sec. 5.3 Options
FAILURE TSAI-HILL
NAME SUBTYPE SIGAM SIGBM SIGCM SIGABM SIGACM SIGBCM
FAILURE TSAI-HILL defines a failure criterion of type Tsai-Hilltype for SHELL elements ( EGROUP SHELL ) in conjunction with material models: ISOTROPIC, ORTHOTROPIC, THERMO-ISOTROPIC and THERMO-ORTHOTROPIC. See Theory and Modeling Guide for details. NAME [(current highest failure label number) + 1] Label number of the failure criterion to be defined. If the label number of an existing failure criterion is given, then the previous failure criterion definition is overwritten. SUBTYPE Indicates the stress/strain conditions. STRESS2
Plane stress.
STRESS3
General 3-D stress.
[STRESS2]
SIGAM Maximum allowable stress in material a-direction.
[0.0]
SIGBM Maximum allowable stress in material b-direction.
[0.0]
SIGCM Maximum allowable stress in material c-direction.
[0.0]
SIGABM Maximum allowable shear stress in the material ab-plane.
[0.0]
SIGACM Maximum allowable shear stress in the material ac-plane.
[0.0]
SIGBCM Maximum allowable shear stress in the material bc-plane.
[0.0]
Auxiliary Commands LIST FAILURE DELETEFAILURE
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FAILURE TSAI-WU
Chap. 5 Control data
FAILURE TSAI-WU
NAME SUBTYPE SIGAMT SIGAMC SIGBMT SIGBMC SIGCMT SIGCMC SIGABM SIGACM SIGBCM FAB FAC FBC HOFFMAN
FAILURE TSAI-WU defines a failure criterion of type Tsai-Wu type for SHELL elements ( EGROUP SHELL ) in conjunction with material models: ISOTROPIC, ORTHOTROPIC, THERMO-ISOTROPIC and THERMO-ORTHOTROPIC. See Theory and Modeling Guide for details. NAME [(current highest failure label number) + 1] Label number of the failure criterion to be defined. If the label number of an existing failure criterion is given, then the previous failure criterion definition is overwritten. SUBTYPE Indicates the stress/strain conditions. STRESS2
Plane stress.
STRESS3
General 3-D stress.
[STRESS2]
SIGAMT Maximum allowable tension stress in material a-direction.
[0.0]
SIGAMC Maximum allowable compression stress in material a-direction.
[0.0]
SIGBMT Maximum allowable tension stress in material b-direction.
[0.0]
SIGBMC Maximum allowable compression stress in material b-direction.
[0.0]
SIGCMT Maximum allowable tension stress in material c-direction.
[0.0]
SIGCMC Maximum allowable compression stress in material c-direction.
[0.0]
SIGABM Maximum allowable shear stress in the material ab-plane.
[0.0]
SIGACM Maximum allowable shear stress in the material ac-plane.
[0.0]
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FAILURE TSAI-WU
Sec. 5.3 Options
SIGBCM Maximum allowable shear stress in the material bc-plane.
[0.0]
FAB Interaction strength between a- and b- material directions.
[0.0]
FAC Interaction strength between a- and c- material directions.
[0.0]
FBC Interaction strength between b- and c- material directions.
[0.0]
HOFFMAN Specifies whether or not the Hoffman convention should be used. {YES/NO}
[YES]
Auxiliary Commands LIST FAILURE DELETEFAILURE
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FAILURE HASHIN
Chap. 5 Control data
FAILURE HASHIN
NAME SIGAMT SIGAMC SIGBMT SIGBMC SIGABM SIGTRM
FAILURE HASHIN defines a failure criterion of type Hashin for SHELL elements ( EGROUP SHELL ) in conjunction with material models: ISOTROPIC, ORTHOTROPIC, THERMO-ISOTROPIC and THERMO-ORTHOTROPIC. See Theory and Modeling Guide for details. NAME [(current highest failure label number) + 1] Label number of the failure criterion to be defined. If the label number of an existing failure criterion is given, then the previous failure criterion definition is overwritten. SIGAMT Maximum allowable tension stress in material a-direction.
[0.0]
SIGAMC Maximum allowable compression stress in material a-direction.
[0.0]
SIGBMT Maximum allowable tension stress in material b-direction.
[0.0]
SIGBMC Maximum allowable compression stress in material b-direction.
[0.0]
SIGABM Maximum allowable shear stress in ab-plane.
[0.0]
SIGTRM Maximum allowable transverse stress.
[0.0]
Auxiliary Commands LIST FAILURE DELETEFAILURE
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FAILURE USERSUPPLIED
Sec. 5.3 Options
FAILURE USERSUPPLIED
NAME NSURFACE
coef1k coef2k coef3k coef4k coef5k coef6k
(k = 8×NSURFACE)
FAILURE USERSUPPLIED defines a user supplied failure criterion for SHELL elements ( EGROUP SHELL ) in conjunction with material models: ISOTROPIC, ORTHOTROPIC, THERMO-ISOTROPIC and THERMO-ORTHOTROPIC. See Theory and Modeling Guide for details. NAME [(current highest failure label number) + 1] Label number of the failure criterion to be defined. If the label number of an existing failure criterion is given, then the previous failure criterion definition is overwritten. NSURFACE The number of failure surfaces. {≤ 4}
[1]
coef1k coef2k coef3k coef4k coef5k coef6k For each failure surface 8 data input lines are entered in the following order: 1:
α1...α6
Coefficients αi of the stress condition.
2:
F1...F6
Linear terms coefficients Fi of the failure surface
3:
F11...F16
Quadratic terms coefficients F1j of the failure surface.
4:
F21...F26
Quadratic terms coefficients F2j of the failure surface.
F61...F66
Quadratic terms coefficients F6j of the failure surface.
... 8:
Auxiliary Commands LIST FAILURE DELETEFAILURE
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TEMPERATURE-REFERENCE
TEMPERATURE-REFERENCE TINIT TLOAD TGINIT TGLOAD NCURTL NCURTGL TEMPERATURE-REFERENCE defines reference temperatures and temperature gradients, for both initial thermal conditions and thermal loads. TINIT [0.0] The initial temperature of a structure, in whatever temperature units you employ. Differing initial temperatures may be specified by commands INITIAL-CONDITION, SETINITCONDITION. TLOAD [0.0] The prescribed reference temperature for a thermal load on a structure, in whatever temperature units you employ. Differing prescribed temperatures may be specified by commands LOAD TEMPERATURE, APPLY-LOAD. TGINIT [0.0] The initial temperature gradient through the thickness of a shell type structure, in whatever temperature/length units you employ. Differing initial temperature gradients may be specified by commands INITIAL-CONDITION, SET-INITCONDITION. TGLOAD [0.0] The prescribed reference temperature gradient for a thermal load on a shell type structure, in whatever temperature/length units you employ. Differing prescribed temperature gradients may be specified by commands LOAD TGRADIENT, APPLY-LOAD. NCURTL Timefunction label number for the reference load temperature.
[0]
NCURTGL Timefunction label number for the reference load temperature gradient.
[0]
Auxiliary commands LISTTEMPERATURE-REFERENCE Lists the reference temperatures and temperature gradients.
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SOLVER ITERATIVE
SOLVER ITERATIVE
Sec. 5.4 Solver details
MAX-ITERATIONS EPSIA EPSIB EPSII SHIFT NVEC
SOLVER ITERATIVE defines control data for the iterative solution of the matrix system of equilibrium equations. This command is applicable when the iterative solver is used, i.e., SOLVER=ITERATIVE, MULTIGRID or 3D-ITERATIVE in the MASTER command. MAX-ITERATIONS [0] The maximum number of iterations for the iterative solver to converge. If MAX-ITERATIONS=0, then MAX-ITERATIONS=1000 is used if SOLVER=ITERATIVE or MULTIGRID and MAX-ITERATIONS=200 if SOLVER=3D-ITERATIVE. {MAX-ITERATIONS ≥ 0} EPSIA [1.0E-6] EPSIB [1.0E-4] EPSII [1.0E-8] Convergence tolerances for the iterative solver, see the Theory and Modeling Guide for further details. Smaller tolerances than the defaults may be required for contact analysis. Note: For the 3D-iterative solver, only EPSIB is used in the convergence checking. SHIFT [1.0] Factor used to make preconditioning more effective within the iterative solver. Values of SHIFT > 1.0 make the preconditioning matrix more diagonally dominant. (Not used for the 3D-iterative solver.) NVEC Note: The shift factor SHIFT can be effective with an ill-conditioned stiffness matrix, such as may be encountered with a shell structure, which is much stiffer in membrane action than in bending action. A typical value of SHIFT = 1.02 has proved beneficial in this situation. Auxiliary commands LIST SOLVER Lists the type of SOLVER (all types available as described in the MASTER command, SOLVER parameter) enabled, and gives the corresponding control parameters, if any.
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PPROCESS
Chap. 5 Control data
PPROCESS
NPROC MINEL MAXEL
PPROCESS specifies control data for parallel processing solutions. It allows for the splitting up of element groups into smaller sub-groups, i.e., the model is partitioned for distributed solution. NPROC [0] Number of processors used. Equivalently, the number of subgroups generated for each element group. NPROC = 0 indicates single processor solution (equivalent to NPROC = 1), in which case this command has no effect - EGCONTROL may be used to effect group splitting in this case. MINEL [0] Each element group with MINEL or more elements can be split into subgroups. Element groups with fewer than MINEL elements are not split. (MINEL = 0 is equivalent to MINEL = 10 × NPROC). MAXEL [999999] Each element group (with MINEL or more elements) is split into I × NPROC subgroups, where the multiplier I is chosen so that each subgroup contains no more than MAXEL elements. Auxiliary commands LIST PPROCESS Lists the current parallel processing control data.
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Sec. 5.4 Solver details
TMC-SOLVER ITERATIVE
TMC-SOLVER ITERATIVE
MAX-ITERATIONS EPSIA EPSIB EPSII SHIFT
TMC-SOLVER ITERATIVE defines control data for the iterative solution of the matrix system of equilibrium equations for heat transfer analysis. To enable the use of the iterative solver, TMC-CONTROL SOLVER = ITERATIVE must be specified. MAX-ITERATIONS The maximum permitted number of iterations for the iterative solver to converge. EPSIA EPSIB EPSII Convergence tolerances for the iterative solver.
[1000] [1.0E-6] [1.0E-4] [1.0E-8]
SHIFT [1.0] Factor used to make preconditioning more effective within the iterative solver. Values of SHIFT > 1.0 make the preconditioning matrix more diagonally dominant. Auxiliary commands LIST TMC-SOLVER Lists the type of TMC-SOLVER (iterative) enabled, and gives the corresponding control parameters, if any.
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AUTOMATIC LOAD-DISPLACEMENT
AUTOMATIC LOAD-DISPLACEMENT
Sec. 5.5 Automatic control
POINT DOF DISPLACEMENT ALPHA DISPMAX CONTINUE RPRINT TYPE NODE SUBDIVISIONS
AUTOMATIC LOAD-DISPLACEMENT defines parameters for the automatic load-displacement control (LDC) procedure, whereby the level of externally applied load is continually adjusted to solve for the nonlinear equilibrium path of a model until, or beyond, collapse. The LDC method can be used only for static analysis in which there are no thermal effects or time-dependent material models (i.e., creep or strain rate dependent materials.) The automatic load-displacement control procedure is enabled when MASTER AUTOMATIC = LDC is specified. (See Theory and Modeling Guide for further details on the operation of the LDC method.) POINT The label number of a geometry point at which a displacement for the first solution step is prescribed. Note that a node will have to be defined at the point location, otherwise an error message will result whenever the model is validated. DOF Indicates which degree of freedom at the requested point or node has the prescribed value given by parameter DISPLACEMENT. DOF refers to the degree of freedom system (global or skew) at the point or node. {1/2/3/4/5/6} 1 2 3 4 5 6
DISPLACEMENT The prescribed displacement for the degree of freedom DOF at the point or node for the first solution step. The value input influences the establishment of successive equilibrium positions using the LDC method. In particular, the sign (positive/negative) of the value often plays a critical role. (See Theory and Modeling Guide for further details). ALPHA [3.0] Factor used to limit the maximum incremental displacement during a solution step. If the incremented displacements exceed 100 x ALPHA times the displacements in the first time step, the current time step will be repeated with a reduced load factor. DISPMAX The maximum (absolute magnitude) of the displacement for degree of freedom DOF at the ADINA R & D, Inc.
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AUTOMATIC LOAD-DISPLACEMENT
point or node which is allowed during analysis. ADINA stops if DISPMAX is exceeded when the LDC method is employed. {> 0.0} CONTINUE [NO] Determines whether or not the solution is terminated when the first critical point on the equilibrium path is reached. {YES/NO} RPRINT [NO] Determines whether or not the reference load vector corresponding to all mechanical loads is printed during analysis. {YES/NO} TYPE [POINT] Selects the type of entity (point or node) indicating the location of the controlling displacement. {POINT/NODE} NODE The label number of a node at which a displacement for the first solution step is prescribed. SUBDIVISIONS Number of subdivisions
[10]
Note: The LDC method terminates normally when one of the following conditions is met: The maximum allowed displacement DISPMAX has been attained. The first critical point on the equilibrium path has been reached and (CONTINUE = NO). The requested time step sequence has been completed. The number of subdivisions has been reached without convergence. Note: The LDC method cannot be used in conjunction with the following analysis types or features: Dynamic analysis Linearized buckling analysis Time-dependent material models (creep, strain rate dependent) Analysis including temperature effects User-supplied or pipe internal pressure loading Auxiliary commands LISTAUTOMATIC Lists the settings for automatic incrementation.
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AUTOMATIC TIME-STEPPING controls the automatic time-stepping procedure, whereby timesteps are subdivided in the event of convergence failure within a prescribed number of equilibrium iterations. See Section 7.2.1 of the Theory and Modeling Guide for further details. The automatic time-stepping procedure is enabled when MASTER AUTOMATIC = ATS is specified. When enabled, this procedure will cause ADINA to subdivide the time step when no iteration convergence is reached in the solution (see commands ITERATION and TOLERANCES ). This procedure is applicable for nonlinear static and implicit transient analysis. MAXSUBD [10] The maximum permitted subdivision of any given time step, i.e., for a time step of magnitude MAXSUBD ∆t, the algorithm will not attempt to subdivide below a time step of magnitude (∆t/2 ). ACCURACY This parameter is obsolete. DISTOL Maximum allowed displacement difference, used in accuracy checking (i.e., when ACCURACY = YES).
[0.001]
DTMAX [3.0] A factor that limits the maximum time step that can be attained during analysis. If the userspecified time step is ∆t, then the ATS procedure will not use a time step larger than (DTMAX × ∆t). This option can only be used if the ATS setting is to return to the previous time step before division (RESTORE=YES). {≥ 1.0} Note: 1. This option is only used in static analysis. It cannot be used in a dynamic analysis or if low speed dynamics is used (RESPS=YES). 2. This option is not used if more than one time step block has been specified (see TIMESTEP ). RESTORE [AUTOMATIC] Indicates whether the original time step, attempted before ATS subdivision occurred, will be used again for the next time step after convergence.
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AUTOMATIC TIME-STEPPING
NO
The ATS method will continue to use the reduced (subdivided) time step which gave convergence.
YES
The ATS method will use the time step which was current prior to subdivision.
AUTOMATIC
The choice of time step restoration is made by ADINA dependent on other problem characteristics. Currently, RESTORE = YES is the automatic choice for contact problems.
ORIGINAL
The ATS method will use a time step size such that the time step will match the original next time step specified by the user.
RESPS [NO] Indicates whether or not the low-speed dynamics option is to be used. Applicable only for nonlinear statics analysis.{NO/YES} RESFAC Low-speed dynamics smoothing factor, used when RESPS = YES. DIVFAC Specifies the division factor used to calculate time step subincrements.
[1.0E-4] [2.0]
LSMASSF [1.0] Low-speed dynamics inertia factor used when RESPS=YES. {0.0 ≤ LSMASSF ≤ 1.0} Auxiliary commands LISTAUTOMATIC Lists the settings for automatic incrementation.
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Controls the total-load-application (TLA) procedure. The TLA procedure is used when AUTOMATIC = TLA or TLA-S is specified in the MASTER command. The TLA procedure is useful for a nonlinear static analysis where the user does not need to explicitly specify the time step sequence. The program uses a certain number of time steps (50 by default) and automatically increases or reduces the next incremental load level depending on how well the solution converges in the current step. In addition, stabilization options are applied when TLA-S (TLA with stabilization) is selected. When the TLA procedure is used, the program uses the following: - 50 time steps of step size 0.2 each are used - the ATS procedure is used with maximum permitted subdivision for any given step MAXSUBD = 64 (see AUTOMATIC TIME-STEPPING command) - maximum number of equilibrium iterations is 30 - line search is used - maximum incremental displacement in each iteration is limited to 5% of largest model length When TLA-S is selected, the program uses the following in addition to all the above TLA settings: - stiffness matrix stabilization factor of 1.0e-10 is used - low-speed dynamics damping factor of 1.0e-4 is used - contact damping (automatically calculated by the program) is used The default values used by TLA and TLA-S that may be overridden are specified in the following parameters. NSTEPS [50] Specifies the number of time steps to use for the solution. The step size is automatically adjusted to obtain a total time of 10.0. {> 0} MAXITE [30] Specifies the maximum number of equilibrium iterations allowed to achieve convergence in
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any time step (subdivided or accelerated). {1 ≤ MAXITE ≤ 999} MAXDISPF [0.05] Specifies the maximum displacement factor. The maximum incremental displacement allowed in any iteration is equal to MAXDISPF * (maximum model dimension) {≥ 0.0} The default values used by TLA-S that may be overridden are specified in the following parameters. STABF [1.0e-10] Specifies the stiffness matrix stabilization factor. If STABF = 0.0, then the stiffness matrix stabilization feature is not used. {≥ 0.0} LSDAMPF [1.0e-4] Specifies the low-speed dynamics damping factor. If LSDAMPF = 0.0, then the low-speed dynamics option is not used. {≥ 0.0} CTDAMPF [1.0e-3] Specifies the contact damping factor. The amount of contact damping used in the solution is equal to CTDAMPF * (damping calculated by the program). If CTDAMPF = 0.0, then contact damping is not used. {≥ 0.0} LSMASSF Low-speed dynamics inertia factor. {0.0 ≤ LSMASSF ≤ 1.0}
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TIMESTEP
TIMESTEP
Sec. 5.6 Time dependence
NAME
nstepi ∆ti TIMESTEP defines a time step sequence which controls the time/load-step incrementation during analysis. The sequence is defined as a number of periods for which a given number of constant time steps is specified. The currently active time step sequence is set to that named by the TIMESTEP command. NAME [DEFAULT] Identifying time step sequence name. If the name of an existing time step sequence is given, then the previous sequence definition is appended to. nstepi Number of steps to be taken in the ith time step sequence period. ∆ ti {∆ti > 0} Constant time step magnitude, in time units, for the ith time step sequence period. Note: A database is initialized with a time step sequence named “DEFAULT” which initially specifies a single time step of magnitude 1.0 time units. Auxiliary commands LISTTIMESTEP NAME Lists a given time step sequence. If no name is specified, then a list of all defined time step sequence names is given. DELETETIMESTEP NAME Deletes a given time step sequence. SETTIMESTEP NAME Sets the currently active time step sequence, i.e., that which will be passed to the analysis program. SHOW TIMESTEP Lists the currently active time step sequence.
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TIMEFUNCTION
Chap. 5 Control data
TIMEFUNCTION
NAME IFLIB FPAR1 FPAR2 FPAR3 FPAR4 FPAR5 FPAR6
timei valuei TIMEFUNCTION defines a timefunction, which may be referenced, e.g., by an applied load. The timefunction curve is defined as piecewise linear through the data points (timei, valuei), and may be multiplied by one of a set of modifying functions. NAME [(current highest TIMEFUNCTION label number) + 1] Label number of the timefunction to be defined. If the label number of an existing timefunction is given, then the previous curve definition is overwritten. IFLIB [1] Indicator for the library modifying function, which multiplies the input timefunction curve values. 1
A constant multiplier equal to 1.0, i.e., the input timefunction is unmodified; f (t ) = f * (t )
2
A sinusoidal multiplier; f ( t ) = f * ( t ) ⋅ sin(ωt + φ)
3
A short circuit multiplier, type 1; f (t ) = f * (t ) ⋅
4
(a + b ⋅ exp(− t τ))
A short circuit multiplier, type 2; µ0 f (t ) = f * (t ) ⋅ ⋅ 2 ⋅ I ⋅ (sin(ωt − φ + α ) + exp( − t τ) ⋅ sin(φ − α )) 4π *
where f (t) is interpolated from the input timefunction curve given by data points (timei, valuei), and the resulting function f(t) is that used by ADINA. IFLIB = 3,4 may be used to model the electromagnetic load due to a short circuit current. FPAR1, ... , FPAR6 Modifying function parameters:
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TIMEFUNCTION
Sec. 5.7 Iteration
IFLIB = 2: [FPAR1 = 0.0, FPAR2 = 0.0] FPAR1 = Angular frequency, ω, in degrees/(unit time). FPAR2 = Phase angle, φ, in degrees. IFLIB = 3: [FPAR1 = 0.0, FPAR2 = 0.0, FPAR3 = 1.0] FPAR1 = Constant a. FPAR2 = Constant b. FPAR3 = Constant τ, in time units. IFLIB = 4: [FPAR5 = 1.0, FPAR6 = 4π π ×10-7] FPAR1 = RMS of short circuit current, I. FPAR2 = Angular frequency, ω, in degrees/(unit time). FPAR3 = Phase angle, φ, in degrees. FPAR4 = Impedance angle, α, in degrees. FPAR5 = Time constant, τ, in time units. FPAR6 = Magnetic permeability, µ0. (Volt.second / meter.Ampere). timei Time at data point “i”. valuei Value at time “timei”. Auxiliary commands LISTTIMEFUNCTION DELETETIMEFUNCTION
ITERATION selects the equilibrium iteration scheme to be employed for a non-linear ADINA analysis. METHOD [FULL-NEWTON] Selects one of the following iteration schemes (see the Theory and Modeling Guide for a discussion of iteration schemes). MODIFIED-NEWTON
Modified Newton iteration method.
BFGS
BFGS (Broyden-Fletcher-Goldfarb-Shanno) matrix update method with line-searches.
FULL-NEWTON
Full Newton iteration method.
LINE-SEARCH [DEFAULT] Flags the use of line searches within the iteration scheme. {YES/NO/DEFAULT} DEFAULT = NO YES
MAX-ITERATIONS [15] Specifies the maximum number of iterations within a time step. ADINA will terminate execution if this maximum number is reached without achieving convergence, unless one of the following conditions is satisfied: (a) The automatic time-stepping method has been enabled ( MASTER AUTOMATIC = ATS), whereby the time step is subdivided a given number of times to try to reach convergence. (b) The load-displacement control method has been enabled ( MASTER AUTOMATIC = LDC), whereby ADINA will automatically restart from the last step with established equilibrium, using different constraint conditions. (A maximum of 10 such restarts will be attempted per step.) {1 ≤ MAX - ITERATIONS ≤ 999} PRINTOUT [LAST] Controls the printout of incremental energy, norms of unbalanced forces and moments, etc., during equilibrium iteration.
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ITERATION
Sec. 5.7 Iteration
NONE
No printout.
LAST
Printout for last iteration of step.
ALL
Printout of intermediate values for each iteration.
Note: For the modified Newton and the BFGS methods of equilibrium iteration, STIFFNESS-STEPS and EQUILIBRIUM-STEPS may be used to restrict the reformation of the stiffness matrix and the equilibrium iteration to only be carried out at specific solution steps. Otherwise, the stiffness matrix reformation and equilibrium iteration are carried out at every step. Note: For the full Newton iteration method, equilibrium iteration and stiffness matrix reformation are always carried out at each solution step, and input to STIFFNESS-STEPS, EQUILIBRIUM-STEPS is effectively ignored. Note: Full Newton iteration, without line-searches, will be used, regardless of the choice made by this command, for the following situation: the automatic load-displacement control method (see commands MASTER, AUTOMATIC LOAD-DISPLACEMENT ) has been selected. PLASTIC-ALGORITHM This flag sets the algorithm used in plasticity. 1
Original algorithm
2
Modified algorithm
[1]
The PLASTIC-ALGORITHM flag is used under the following conditions: Implicit time integration (static or dynamic), and 1) METHOD=FULL-NEWTON (with or without line searches), and 2) 2D solid elements, 3D solid elements or shell elements under the following conditions: - Large displacement, large strain kinematics - 2D solid elements: ULJ formulation, material PLASTIC-ORTHOTROPIC - 3D solid elements: ULJ formulation, material PLASTIC-ORTHOTROPIC - 3D solid elements: ULH formulation, materials MROZ-BILINEAR, PLASTIC-BILINEAR,
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PLASTIC-MULTILINEAR - Shell elements: ULJ formulation, material PLASTIC-ORTHOTROPIC - Shell elements: ULH formulation, materials PLASTIC-BILINEAR, PLASTICMULTILINEAR For a given load step size, convergence is affected by PLASTIC-ALGORITHM. If the iterations do not converge with PLASTIC-ALGORITHM=1 because the Jacobian determinant in the elements becomes non-positive, switching to PLASTIC-ALGORITHM=2 can sometimes obtain convergence. Hence PLASTIC-ALGORITHM=2 allows larger load steps than PLASTIC-ALGORITHM=1, in general. But if the iterations already converge with PLASTIC-ALGORITHM=1, switching to PLASTIC-ALGORITHM=2 slows down convergence. The converged solution is not affected by the choice of PLASTIC-ALGORITHM. The typical use of PLASTIC-ALGORITHM=2 is in metal forming. In metal forming, the metal being formed is typically very thin and modeled either with shell elements or with thin 3D elements. PLASTIC-ALGORITHM=2 allows large load steps, and hence fewer load steps, to obtain the solution. Auxiliary commands LIST ITERATION Lists the current values of the ITERATION command parameters.
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STIFFNESS-STEPS
Sec. 5.7 Iteration
STIFFNESS-STEPS blocki firsti lasti incrementi STIFFNESS-STEPS controls the output timesteps at which the effective stiffness matrix is reformed by ADINA. This is achieved by specifying a sequence of time step blocks, each of which determines a given frequency of stiffness matrix reformation over a given range of timesteps. blocki The time step block number. The block number must be in the range 1 ≤ blocki ≤ 10, i.e., a maximum of 10 time step blocks can be defined. firsti The initial time step number for the time step block blocki. {≥ 1, ≥ lasti-1} lasti The final time step number for the time step block blocki. {≥ firsti} incrementi The time step increment for the time step block blocki. {≥ 1} For each time step block, ADINA will re-form the effective stiffness matrix for timesteps firsti, firsti + incrementi, firsti + (2 × incrementi), ... and so on until the resulting time step number is greater than or equal to lasti. Note that the stiffness matrix will be reformed at time step lasti only if (lasti - firsti) is an integer multiple of incrementi. The time step block data is checked to see that each block satisfies lasti ≥ firsti
(i = 1, ..., 10)
incrementi ≥ 1 and that adjacent blocks do not overlap, i.e., firsti ≥ lasti
(i = 2, ..., 10)
If these input conditions are not satisfied, then an error message will be given and the input will not be accepted.
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STIFFNESS-STEPS
Furthermore, it is required that the highest value for lasti (for the highest block number) be greater than or equal to the total number of solution timesteps (see TIMESTEP ). If not, then it will be set to that value, with no resulting error condition. Note: Command is only applicable when modified Newton or BFGS iterations method are used. Auxiliary commands LIST STIFFNESS-STEPS DELETE STIFFNESS-STEPS
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EQUILIBRIUM-STEPS
Sec. 5.7 Iteration
EQUILIBRIUM-STEPS blocki firsti lasti incrementi EQUILIBRIUM-STEPS controls the output timesteps at which equilibrium iterations are performed when the modified-Newton or BFGS iteration method is used. This is achieved by specifying a sequence of time step blocks, each of which determines a given frequency of equilibrium iteration over a given range of timesteps. blocki The time step block number. The block number must be in the range 1 ≤ blocki ≤ 10, i.e., a maximum of 10 time step blocks can be defined. firsti The initial time step number for the time step block blocki. {≥ 1; ≥ lasti-1} lasti The final time step number for the time step block blocki. {≥ firsti} incrementi The time step increment for the time step block blocki. {≥ 1} For each time step block, ADINA will carry out equilibrium iteration for time steps firsti, firsti + incrementi, firsti + (2 × incrementi), ... and so on until the resulting time step number is greater than or equal to lasti. Note that equilibrium iteration will be performed at time step lasti only if (lasti - firsti) is an integer multiple of incrementi. The time step block data is checked to see that each block satisfies lasti ≥ firsti
(i = 1, ..., 10)
incrementi ≥ 1 and that adjacent blocks do not overlap, i.e., firsti ≥ lasti
(i = 2, ..., 10)
If these input conditions are not satisfied, then an error message will be given and the input will not be accepted.
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EQUILIBRIUM-STEPS
Furthermore, it is required that the highest value for lasti (for the highest block number) be greater than or equal to the total number of solution timesteps (see TIMESTEP ). If not, then it will be set to that value, with no resulting error condition. Auxiliary commands LIST EQUILIBRIUM-STEPS DELETE EQUILIBRIUM-STEPS
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TMC-ITERATION selects the equilibrium iteration scheme to be employed for a heat transfer analysis. METHOD [MODIFIED-NEWTON] Selects the iteration scheme. {MODIFIED-NEWTON /FULL-NEWTON} MODIFIED-NEWTON
Modified Newton iteration.
FULL-NEWTON
Full Newton iteration.
MAX-ITERATIONS The maximum number of iterations within a time step.
[15]
STEP-REFORMING The maximum number of time steps between reforming conductivity, heat capacity, convection and radiation matrices.
[1]
STEP-EQUILIBRIUM The maximum number of time steps between equilibrium iterations. Note: The FULL-NEWTON iteration scheme can be more effective when temperaturedependent material properties are used, or RADIATION elements are present.
[1]
RTOL RTOL is the temperature convergence tolerance. TMCTOL TMC is the iteration tolerance. The default for TMCTOL is RTOL: this means that if TMCTOL= 0.0, TMCTOL=RTOL. LINE-SEARCH Flags the use of line searches within the iteration scheme. {NO/YES}
TOLERANCES GEOMETRIC specifies certain geometric tolerances used during the construction of a model. COINCIDENCE [1.0E-5] Tolerance used when comparing two locations to see if they are coincident. The default value is usually sufficient for most models, but may be reduced, e.g, if distinct locations are extremely close in comparison to the overall dimension of the model. EPSILON [1.0E-9] A small value representing zero in many geometry property tests. This value is not normally required to be changed from the default value. SHELL-ANGLE [5.0] A small angular measure, in degrees, used in comparing normal vectors to determine the number of degrees of freedom to be automatically assigned to a shell midsurface node at which shell elements meet. BOLT-ANGLE [0.5] A small angular measure, in degrees, used in comparing shell element normal vectors to determine whether any impinging beam-shaft elements give rise to additional constraints relating the rotational degree of freedom normal to the shell surface to adjacent translational degrees of freedom. If a shell element normal differs from the average normal at a node by more than BOLT-ANGLE degrees, no additional bolt constraints will be generated. PHI-ANGLE This parameter is obsolete, but retained for backwards compatibility. Use the PHI-MODEL-COMPLETION command, PHI-ANGLE parameter instead.
[30]
EMF-DMIN [0.001] Specifies minmum distance between two electric conductors. If the distance between two conducting nodes in the model is less than EMF-DMIN, EMF-DMIN will be used. NCTOL-TYPE [RELATIVE-LOCAL] Option to determine the tolerance for node coincidence checking. {RELATIVE-LOCAL/ RELATIVE-GLOBAL/ ABSOLUTE} A node at (XB,YB,ZB) is close to a geometric location (XA,YA,ZA) if |XB-XA| ≤ COINCIDENCE * XLEN
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Sec. 5.8 Tolerances
|YB-YA| ≤ COINCIDENCE * YLEN |ZB-ZA| ≤ COINCIDENCE * ZLEN where, (XLEN, YLEN, ZLEN) are decided by the following: RELATIVE-LOCAL
(XLEN, YLEN, ZLEN) are the lengths of the bounding box for the current geometry.
RELATIVE-GLOBAL
(XLEN, YLEN, ZLEN) are the lengths of the bounding box for the model.
ABSOLUTE
(XLEN, YLEN, ZLEN) are (1.0, 1.0, 1.0).
Auxiliary commands LIST TOLERANCES GEOMETRIC Lists the tolerance data for the model geometry.
TOLERANCES ITERATION specifies the convergence criteria and corresponding tolerances controlling the equilibrium iteration scheme within the analysis program ADINA. CONVERGENCE [ENERGY] Selects the convergence criterion to be used, and thereby which of the other parameters are considered. ENERGY
Energy convergence (ETOL, STOL).
EF
Energy and force (moment) convergence (ETOL, RTOL, RNORM, RMNORM, STOL).
ED
Energy and displacement (translation, rotation) convergence (ETOL, DTOL, DNORM, DMNORM, STOL).
FORCE
Force (moment) convergence (RTOL, RNORM, RMNORM, STOL).
In addition, when contact is present, the RCTOL and RCONSM parameters are also used. ETOL [0.0] Relative energy tolerance. ETOL=0.0 means ETOL=1.0E-6 when the load-displacement control method (MASTER AUTOMATIC=LDC) is used and ETOL=1.0E-3 otherwise. RTOL Relative force and moment tolerance.
[0.01]
RNORM [0.0] Reference force. RNORM is automatically calculated by the program if RNORM=0.0. RMNORM [0.0] Reference moment. RMNORM is automatically calculated by the program if RMNORM=0.0. RCTOL Relative contact force tolerance.
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DNORM [0.0] Reference translation. DNORM is automatically calculated by the program if DNORM=0.0. DMNORM [0.0] Reference rotation. DMNORM is automatically calculated by the program if DMNORM=0.0. STOL Line search convergence tolerance.
[0.5]
RCONSM Reference contact force.
[0.01]
ENLSTH [0.0] Line search energy threshold. This parameter is only used if line search is activated (e.g., when ITERATION LINE-SEARCH=YES is specified). During each equilibrium iteration, if the unbalanced energy is less than ENLSTH, no line search will be performed. {>= 0.0} Notes: 1. RNORM and RMNORM cannot both be zero. 2. DNORM and DMNORM cannot both be zero. LSLOWER Lower bound for line search. {0.0 ≤
[1.0e-3] LSLOWER < 1.0}
LSUPPER [1.0 or 8.0] Upper bound for line search. If there is contact, the default is 1.0; otherwise, if there is no contact, the default is 8.0. {LSUPPER ≥ 1.0} MAXDISP [0.0] Specifies the maximum incremental displacement that is allowed in an iteration. This feature is generally useful for contact analysis where rigid body motion before the bodies come into contact may result in excessive displacements. A value of 0.0 means there is no limit on incremental displacements. { ≥ 0.0 } Auxiliary commands LIST TOLERANCES ITERATION Lists the tolerance data for the iteration scheme within the analysis program ADINA.
PRINTOUT controls the output printed by ADINA. VOLUME Sets the defaults for the remaining parameters of this command. MAXIMUM
The following defaults are set: ECHO PRINTDEFAULT INPUT-DATA OUTPUT DISPLACEMENTS VELOCITIES ACCELERATIONS IDISP ITEMP ISTRAIN IPIPE
MINIMUM
[MINIMUM]
= = = = = = = = = = =
YES YES 0 ALL YES YES YES YES YES YES YES
The following defaults are set: ECHO PRINTDEFAULT INPUT-DATA OUTPUT DISPLACEMENTS VELOCITIES ACCELERATIONS IDISP ITEMP ISTRAIN IPIPE
= = = = = = = = = = =
NO NO 4 SELECTED YES YES YES NO NO NO NO
ECHO [NO] Determines whether the input data file is echoed at the beginning of the ADINA results file. {YES/NO}
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PRINTOUT
Sec. 5.9 Analysis output
PRINTDEFAULT [NO] Printing of individual element results is controlled by the data entry “print” of the element data commands. This parameter defines the default action for those elements with that data entry left undefined. YES
Print element results.
NO
No element results printed.
STRAINS
Element strains are printed in addition to element stresses (only applicable to certain material models).
INPUT-DATA Level of printout of input mesh data. 0 1 2 3 4
Detailed printing of all generated input data. As for 0, except equation numbers are not printed. As for 0, except nodal data are not printed. As for 0, except equation numbers and nodal data are not printed. No printing of input mesh data.
OUTPUT ALL
[4]
[SELECTED] All nodal point solution variables and requested element stresses, via element data commands, are printed at all solution steps.
SELECTED Results are printed as requested by the parameters of this command in conjunction with other commands, e.g., PRINT-STEPS, PRINTNODES. DISPLACEMENTS Controls whether or not the program will print displacements (when OUTPUT = SELECTED). {YES/NO}
[YES]
VELOCITIES [YES] Controls whether or not the program will print velocities (when OUTPUT = SELECTED). {YES/NO} ACCELERATIONS [YES] Controls whether or not the program will print accelerations (when OUTPUT = SELECTED). {YES/NO}
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PRINTOUT
IDISP [NO] Controls whether or not initial displacements, velocities and accelerations (as indicated by parameters DISPLACEMENTS, VELOCITIES, and ACCELERATIONS) are printed out. {YES/NO} ITEMP [NO] Controls whether or not initial temperatures and temperature gradients are printed out. {YES/NO} ISTRAIN [NO] Controls whether or not initial strains, flexural strains and strain gradients are printed out. {YES/NO} IPIPE Controls whether or not initial pipe internal pressures are printed out. {YES/NO}
[NO]
STORAGE Controls whether or not storage requirements are printed out. {YES/NO}
[NO]
LARGE-STRAINS [NONE] Indicates whether or not extended results for element stresses and strains are to be printed for large strain analyses. {NONE/PRINT} ENERGIES [NO] Indicates whether the energies due to the use of low-speed dynamics option (inertia and damping), contact damping or assigned stiffness to the normal rotational degree of freedom of shell nodes are printed. {NO/YES} Auxiliary commands LIST PRINTOUT
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PRINT-STEPS
PRINT-STEPS
Sec. 5.9 Analysis output
SUBSTRUCTURE REUSE
blocki firsti lasti incrementi PRINT-STEPS controls the output time steps at which results are printed by the analysis program. This is achieved by specifying a sequence of time step “blocks”, each of which determines a given frequency of time step output over a given range of time steps. Note that the results printout can be controlled independently for the main structure and any substructure reuses. SUBSTRUCTURE [current substructure label number] The label number of the substructure to which the time step block data is assigned. REUSE [current substructure reuse label number] The label number of the substructure reuse to which the time step block data is assigned. blocki The time step block number. The block number must be in the range 1 ≤ blocki ≤ 10, i.e., a maximum of 10 time step blocks can be defined for printout control. firsti The initial time step number for the time step block “blocki”. {≥ 1; ≥ lasti-1} lasti The final time step number for the time step block “blocki”. {≥ firsti} incrementi The time step increment for the time step block “blocki”. {≥ 1} For each time step block, the analysis program will print results for time steps firsti, firsti + incrementi, firsti + (2 × incrementi), ... etc., until the resulting time step number is greater than or equal to lasti. Note that printout will be given at time step lasti only if (lasti - firsti) is an integer multiple of incrementi. The time step block data is checked to see that each block satisfies lasti ≥ firsti (i = 1,...,10) incrementi ≥ 1
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Chap. 5 Control data
PRINT-STEPS
and that adjacent blocks do not overlap, i.e.: firsti≥ last(i-1) (i = 2,...,10) If these conditions are not satisfied, then an error message will be given and the input will not be accepted. Furthermore, it is required that the highest value for lasti (for the highest block number) be greater than or equal to the total number of solution timesteps (see TIMESTEP ). If not, then it will be set to that value, with no resulting error condition. Auxiliary commands LIST PRINT-STEPS DELETE PRINT-STEPS
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PORTHOLE controls the saving, by ADINA, of input data and solution results on the porthole file for later post-processing by ADINA-PLOT. VOLUME Sets defaults for remaining parameters of this command. MAXIMUM
The following defaults are set: SAVEDEFAULT = YES INPUT-DATA = 1 DISPLACEMENTS = YES VELOCITIES = YES ACCELERATIONS = YES TEMPERATURES = YES
MINIMUM
The following defaults are set: SAVEDEFAULT = NO INPUT-DATA = 0 DISPLACEMENTS = NO VELOCITIES = NO ACCELERATIONS = NO TEMPERATURES = NO
[MAXIMUM]
SAVEDEFAULT [YES] Saving of individual element results is controlled by the data entry “save” of the element data commands. This parameter defines the default action for those elements with that data entry left undefined. {YES/NO} FILEUNIT This parameter is no longer used. FORMATTED [NO] Controls whether the porthole file records are formatted or written in unformatted binary. {YES/NO} INPUT-DATA This parameter is obsolete and should not be used. This parameter is used only in restart analysis.
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PORTHOLE
0
Save only the master control information. Note that when INPUT-DATA = 0, the resulting porthole file cannot be read by ADINA-PLOT.
1
Save all input data on the porthole.
DISPLACEMENTS [YES] Controls whether or not initial and calculated displacements are saved. {YES/NO} VELOCITIES Controls whether or not initial and calculated velocities are saved. {YES/NO}
[YES]
ACCELERATIONS Controls whether or not initial and calculated accelerations are saved. {YES/NO}
[YES]
TEMPERATURES Controls whether or not temperatures are saved on the porthole file. {YES/NO}
[YES]
Note: TEMPERATURES is also used to control the saving of pipe internal pressures. MAX-STEPS [0] Indicates the maximum number of time-step results saved in each porthole file. MAXSTEPS=0 means no limit on the number of steps that can be saved on the porthole file, i.e., only one porthole file is created. Notes: 1. If MAX-STEPS > 0, multiple porthole file may be created with filenames jobname_1.por, jobname_2.por, etc. 2.
MAX-STEPS is also used to control the maximum number of time-step results saved in each universal file.
SHELLVECTORS [NO] Indicates whether or not shell element node director vectors are to be saved on the porthole file. Note this only refers to those director vectors calculated in large displacement analysis during the solution response, the initial shell element node director vectors will still be saved on the porthole file. These vectors are required to plot shell elements with a top-bottom depiction, but can require considerable storage for large shell models with many output steps. When SHELLVECTORS=NORMALS, only the normals of the shell direction vectors are saved in the porthole file. {YES/NO/NORMALS}
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PORTHOLE
Sec. 5.9 Analysis output
ELEM-RESULT [DEF-GRAD] Controls whether deformation gradients, stretches or strains are saved in the porthole file for 2-D and 3-D solid elements with certain material models/kinematic formulations. {DEF-GRAD/STRETCH} The following table lists the material models and kinematic formulations affected by this parameter: ————————————————————————————————————— Material model Output when ELEM-RESULT=STRETCH ————————————————————————————————————— ARRUDA-BOYCE Green-Lagrange strains CAM-CLAY(*) Stretches CREEP (*) Stretches CREEP-VARIABLE (*) Stretches DRUCKER-PRAGER (*) Stretches GURSON (*) Stretches HYPER-FOAM Green-Lagrange strains MOONEY-RIVLIN Green-Lagrange strains MROZ-BILINEAR (*) Stretches MULTILINEAR-PLASTIC-CREEP (*) Stretches MULTILINEAR-PLASTIC-CREEP-VARIABLE (*) Stretches PLASTIC-BILINEAR (*) Stretches PLASTIC-CREEP (*) Stretches PLASTIC-CREEP-VARIABLE (*) Stretches PLASTIC-MULTILINEAR (*) Stretches OGDEN Green-Lagrange strains USER-SUPPLIED (+) Green-Lagrange strains USER-SUPPLIED (*) Stretches THERMO-PLASTIC (*) Stretches VISCOELASTIC (*) Stretches —————————————————————————————————————— * = KINEMATICS DISP=LARGE STRAINS = LARGE + = KINEMATICS DISP=LARGE STRAINS = SMALL When ELEM-RESULT = DEF-GRAD, then all of the material models/kinematic formulations in the above table output deformation gradients. Auxiliary commands LIST PORTHOLE Lists the current settings for the PORTHOLE parameters.
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NODESAVE-STEPS
Chap. 5 Control data
NODESAVE-STEPS
ELEMSAVE
blocki firsti lasti incrementi NODESAVE-STEPS controls the output timesteps at which nodal results are saved on the porthole file by the analysis program. This is achieved by specifying a sequence of time step “blocks”, each of which determines a given frequency of time step output over a given range of time steps. ELEMSAVE [NO] Indicates whether element results are also saved using the same time step blocks. {NO/ COPY/OVERWRITE} NO
Time step blocks for saving element results are specified independently in ELEMSAVE-STEPS command.
COPY
Time step blocks specified in this command are copied to the ELEMSAVE-STEPS command if no time step block are specified in that command.
OVERWRITE
Time step blocks specified in this command will overwrite any time step blocks in the ELEMSAVE-STEPS command.
blocki The time step block number. The block number must be in the range 1 ≤ blocki ≤ 10, i.e., a maximum of 10 time step blocks can be defined for porthole control. firsti The initial time step number for the time step block “blocki”. {≥ 1; ≥ last(i-1)} lasti The final time step number for the time step block “blocki”. {≥ firsti} incrementi The time step increment for the time step block “blocki”. {≥ 1} For each time step block, the analysis program will save nodal results for timesteps firsti, firsti + incrementi, firsti+(2 × incrementi), ... and so on until the resulting time step number is greater than or equal to lasti.
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NODESAVE-STEPS
Sec. 5.9 Analysis output
Note that nodal results will be saved at time step lasti only if (lasti - firsti) is an integer multiple of incrementi. The time step block data is checked to see that each block satisfies lasti ≥ firsti incrementi ≥ 1
(i = 1,...,10)
and that adjacent blocks do not overlap, i.e.: firsti ≥ last(i-1)
(i = 2,...,10)
If these conditions are not satisfied, then an error message will be given and the input will not be accepted. Furthermore, it is required that the highest value for lasti (for the highest block number) be greater than or equal to the total number of solution timesteps (see TIMESTEP ). If not, then it will be set to that value, with no resulting error condition. Auxiliary commands LIST NODESAVE-STEPS DELETE NODESAVE-STEPS
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ELEMSAVE-STEPS
Chap. 5 Control data
ELEMSAVE-STEPS
NODESAVE
blocki firsti lasti incrementi ELEMSAVE-STEPS controls the output timesteps at which element results are saved on the porthole file by the analysis program. This is achieved by specifying a sequence of time step “blocks”, each of which determines a given frequency of time step output over a given range of timesteps. NODESAVE [NO] Indicates whether nodal results are also saved using the same time step blocks. {NO/ COPY/OVERWRITE} NO
Time step blocks for saving nodal results are specified independently in NODESAVE-STEPS command.
COPY
Time step blocks specified in this command are copied to the NODESAVE-STEPS command if no time step block are specified in that command.
OVERWRITE
Time step blocks specified in this command will overwrite any time step blocks in the NODESAVE-STEPS command.
blocki The time step block number. The block number must be in the range 1 ≤ blocki ≤ 10, i.e., a maximum of 10 time step blocks can be defined for porthole control. firsti The initial time step number for the time step block “blocki”. Note that firsti must be greater than or equal to 1. lasti The final time step number for the time step block “blocki”. {≥ 1; ≥ last(i-1)} incrementi The time step increment for the time step block “blocki”. {≥ 1} For each time step block, the analysis program will save element results for timesteps: firsti, firsti + incrementi, firsti+(2 × incrementi), ... and so on, until the resulting time step number is greater than or equal to lasti.
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ELEMSAVE-STEPS
Sec. 5.9 Analysis output
Note that element results will be saved at time step lasti only if (lasti - firsti) is an integer multiple of incrementi. The time step block data is checked to see that each block satisfies: lasti ≥ firsti incrementi ≥ 1
(i = 1,...,10)
and that adjacent blocks do not overlap, i.e.: firsti ≥ last(i-1)
(i = 2,...,10)
If these conditions are not satisfied, then an error message will be given and the input will not be accepted. Furthermore it is required that the highest value for lasti (for the highest block number) be greater than or equal to the total number of solution timesteps (see TIMESTEP ). If not, then it will be set to that value, with no resulting error conditions. Auxiliary commands LIST ELEMSAVE-STEPS DELETE ELEMSAVE-STEPS
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PRINTNODES
Chap. 5 Control data
PRINTNODES BLOCKS
SUBSTRUCTURE REUSE
blocki firsti lasti incrementi PRINTNODES POINTS
SUBSTRUCTURE REUSE
pointi PRINTNODES LINES
SUBSTRUCTURE REUSE
linei PRINTNODES SURFACES
SUBSTRUCTURE REUSE
surfacei PRINTNODES VOLUMES
SUBSTRUCTURE REUSE
volumei PRINTNODES EDGES
SUBSTRUCTURE REUSE BODY
edgei PRINTNODES FACES
SUBSTRUCTURE REUSE BODY
facei PRINTNODES BODIES
SUBSTRUCTURE REUSE
bodyi PRINTNODES NODESETS
SUBSTRUCTURE REUSE
nodeseti PRINTNODES selects nodes for which solution results shall be printed by ADINA. This is achieved by specifying a sequence of node blocks (sets of node labels) or by reference to a set of geometry entities to which the nodes are associated, i.e. via mesh generation. SUBSTRUCTURE [(current substructure label number)] The label number of the substructure to which the nodal data is assigned. REUSE [(current substructure reuse label number)] The label number of the substructure reuse to which the nodal data is assigned. BODY A solid geometry body label number.
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PRINTNODES
Sec. 5.9 Analysis output
blocki A node block number. firsti The initial node number for the node block blocki. {≥ 1; ≥ last(i-1)} lasti The final node number for the node block blocki. {≥ firsti} incrementi The node increment for the node block blocki. {≥ 1} pointi A point label number. linei A line label number. surfacei A surface label number. volumei A volume label number. edgei An edge label number; an edge of a solid body “BODY”. facei A face label number; a face of a solid body “BODY”. bodyi A body label number. nodeseti A node set label number. Auxilliary Commands LIST PRINTNODES BLOCKS / POINTS / LINES / SURFACES / VOLUMES / EDGES / FACES / BODIES. DELETE PRINTNODES BLOCKS / POINTS / LINES / SURFACES / VOLUMES / EDGES / FACES / BODIES.
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CONTACT-OUTPUT-NODES
CONTACT-OUTPUT-NODES TYPE namei bodyi This command is used to select nodes for output of contact results. TYPE The type of entity used for selecting nodes where the contact result is to be output. {NODE/NODESET/POINT/LINE-EDGE/SURFACE-FACE} Note: If TYPE = NODE or NODESETor POINT , the second column bodyi is ignored. When TYPE = LINE-EDGE or SURFACE-FACE, if bodyi = 0, this means that the geometry is a line or a surface. namei Label number of the node for which the contact result is output. bodyi Label number of the body for namei.
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REACTION-NODES
Sec. 5.9 Analysis output
REACTION-NODES TYPE namei bodyi This command is used with the REACTIONS parameter in the MASTER command to select the reaction forces to be printed. TYPE The type of entity used for selecting nodes where the reaction force is to be printed. {NODE/NODESET/POINT/LINE-EDGE/SURFACE-FACE} Note: If TYPE = NODE or NODESET or POINT , the second column bodyi is ignored. When TYPE = LINE-EDGE or SURFACE-FACE, if bodyi = 0, this means that the geometry is a line or a surface. namei Label number of the node for which the reaction force is printed. bodyi Label number of the body for namei.
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SAVENODES
SAVENODES BLOCKS
Sec. 5.9 Analysis output
SUBSTRUCTURE REUSE
blocki firsti lasti incrementi SAVENODES POINTS
SUBSTRUCTURE REUSE
pointi SAVENODES LINES
SUBSTRUCTURE REUSE
linei SAVENODES SURFACES
SUBSTRUCTURE REUSE
surfacei SAVENODES VOLUMES
SUBSTRUCTURE REUSE
volumei SAVENODES EDGES
SUBSTRUCTURE REUSE BODY
edgei SAVENODES FACES
SUBSTRUCTURE REUSE BODY
facei SAVENODES BODIES
SUBSTRUCTURE REUSE
bodyi SAVENODES NODESETS
SUBSTRUCTURE REUSE
nodeseti SAVENODES selects nodes for which solution results shall be saved by the ADINA on the porthole file. This is achieved by specifying a sequence of node blocks (set of node labels), or by reference to a set of geometry entities to which the nodes are associated, i.e. via mesh generation. SUBSTRUCTURE [(current substructure label number)] The label number of the substructure to which the nodal data is assigned. REUSE [(current substructure reuse label number)] The label number of the substructure reuse to which the nodal data is assigned. BODY A solid geometry body label number. ADINA R & D, Inc.
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SAVENODES
blocki A node block number. firsti The initial node number for the node block blocki. {≥ 1; ≥ last(i-1)} lasti The final node number for the node block blocki. {≥ firsti} incrementi The node increment for the node block blocki. {≥ 1} pointi A point label number. linei A line label number. surfacei A surface label number. volumei A volume label number. edgei An edge label number; an edge of solid body “BODY”. facei A face label number; a face of solid body “BODY”. bodyi A body label number. nodeseti A node set label number. Auxilliary Commands LIST SAVENODES BLOCKS / POINTS / LINES / SURFACES / VOLUMES / EDGES / FACES / BODIES. DELETE SAVENODES BLOCKS / POINTS / LINES / SURFACES / VOLUMES / EDGES / FACES / BODIES.
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DISK-STORAGE indicates auxiliary file storage and input/output control for program ADINA. FACTORIZED-MATRIX [NONE] Indicates whether or not the factorized linear effective stiffness matrices are to be saved for subsequent use in restart analyses. This option provides for improved solution efficiency for large problems for which the factorization calculations may be skipped for a restart. NONE
No factorized linear stiffness matrices are saved.
SAVE
The factorized linear effective stiffness matrices are saved for future use by a restart of the analysis.
Note that this option of saving the linear factorized stiffness matrices is not allowed in an eigenvalue solution or when the central-difference method is used. Furthermore, static-todynamic or dynamic-to-static restarts are not allowed. GLOBAL-MATRIX [NONE] Indicates whether or not the global, assembled, stiffness and mass matrices are to be saved to a file. For non-linear analyses the stiffness matrix can be saved at a selected time-step via parameter NSTEPKM. Only available when SOLVER = SKYLINE in the MASTER command, and for analyses not involving contact conditions. NONE
The assembled global system matrices are not saved.
SAVE
The global stiffness and mass matrices are written to file, in formatted form.
TEMPERATURES [NONE] Indicates whether or not nodal temperature data is to be input from a file. Material models which are temperature dependent require the temperature field to be specified. Prescribed or initial nodal temperatures may be simply described directly by LOAD TEMPERATURE, APPLY-LOAD, INITIAL-CONDITION, SET-INITCONDITION, but a more complex temperature distribution may benefit from being input from file (e.g., created by the heat transfer analysis program ADINA-T). Note that any nodal temperature data input from file is added to that already specified directly to the database, if any. NONE
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No temperature data is input from file.
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READ
DISK-STORAGE
Temperatures are read from file. The data records of that file must contain the solution time and the nodal temperatures at that time. The solution times for this input case must correspond to the times of the ADINA analysis given by time TSTART (see MASTER) and increments thereafter determined by the defined time step sequence.
INTERPOLATE Temperatures are read from file, but unlike the case TEMPERATURES = READ, the solution times need not correspond to the discrete solution times of the ADINA analysis as given by TSTART and the time step sequence – linear interpolation is performed to give the nodal temperatures at the ADINA solution times. TGRADIENTS [NONE] This parameter acts in the same manner as parameter TEMPERATURES except that through-thickness temperature gradients for shell mid-surface nodes are considered. Note that any nodal temperature gradient data input from file is added to that already specified directly to the database, if any. {NONE/READ/INTERPOLATE} FORCES [NONE] This parameter acts in the same manner as parameter TEMPERATURES except that nodal forces are considered. The number and associated (possibly skew) degree-of-freedom directions of the force components (with a maximum of 6 components) are specified by parameter FDIRECTIONS. Note that any nodal force data input from file is added to that already specified directly to the database, if any. {NONE/READ/INTERPOLATE} DISPLACEMENTS [NONE] Indicates whether or not nodal displacements are written to file, e.g., for use by analysis program ADINA-F, to control a moving boundary in a fluid-structure-interaction analysis. NONE
No displacement vectors are written to file.
WRITE
Displacement vectors will be written to file.
PIPE-INTERNAL-PRESSURES [NONE] This parameter acts in the same manner as parameter TEMPERATURES except that pipe internal pressures are considered. Note that any nodal pipe internal pressure data input from file is added to that already specified directly to the database, if any. {NONE/READ / INTERPOLATE} FDIRECTIONS [123456] Indicates which degree-of-freedom directions are to be associated with the nodal force components input from file (i.e., when parameter FORCES = READ or INTERPOLATE). The parameter value is an integer number with up to six digits (and no embedded blanks) with the
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DISK-STORAGE
Sec. 5.9 Analysis output
associated directions given as follows: 1 2 3 4 5 6
X-translation (or a-translation for skew system). Y-translation (or b-translation for skew system). Z-translation (or c-translation for skew system). X-rotation (or a-rotation for skew system). Y-rotation (or b-rotation for skew system). Z-rotation (or c-rotation for skew system).
NSTEPKM [1] Indicates the time-step at which a non-linear stiffness matrix is written to file when GLOBALMATRIX = SAVE. The stiffness matrix at the start of the indicated step is stored – any automatic sub-increments are not counted, the time-step sequence specified by command TIMESTEP is all that is considered by this parameter. Thus, NSTEPKM = 1 corresponds to saving the initial stiffness matrix, corresponding to time TSTART. LARGE-STRAINS [NONE] Indicates whether or not extended results of element stresses and strains are to be saved in a file for large strain analyses, and, if so, whether the file is formatted or binary. {NONE/ FORMATTED/BINARY} MEMOPT [AUTOMATIC] Specifies option to write element group data on disk to reduce memory required by the program. {AUTOMATIC/EG-OUT} AUTOMATIC
Program automatically decides when element group data is written on disk.
EG-OUT
Element group data is written on disk to reduce memory usage.
Auxiliary commands LIST DISK-STORAGE
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MONITOR
Chap. 5 Control data
MONITOR
NAME DESCRIPTION TYPE VARIABLE STOPFLAG STOPVALUE OPERATION SET1
Defines a monitor that can be used to print out the minimum or maximum value of a variable during solution. In addition, there is an option to stop the program when the variable reaches a specified value. For element-based variables, only variables in 2D and 3D solid element can be monitored. NAME The monitor label. {>0}
[(current highest monitor label number) + 1]
DESCRIPTION Description of this monitor. TYPE [NONE] Type of quantity to be monitored. {NONE/ELAV-MODEL/ELAV-GROUP/NODE-MODEL} NONE ELAV-MODEL ELAV-GROUP NODE-MODEL
Monitoring is not active Nodal averaged element quantity – whole model Nodal averaged element quantity – element group Nodal quantity – whole model
VARIABLE Name of variable just like post-processing. For element-based variables, the choices are STRESS-XX STRESS-XY STRESS-XZ STRESS-YY STRESS-YZ STRESS-ZZ STRESS-EFFECTIVE STRESS-PRINCIPAL STRAIN-XX STRAIN-YY STRAIN-ZZ STRAIN-XY STRAIN-XZ STRAIN-YZ STRAIN-PRINCIPAL For nodal-based variables, the choices are: DISP-X DISP-Y DISP-Z DISP-MAGNITUDE ROT-X ROT-Y ROT-Z ROT-MAGNITUDE VEL-X VEL-Y VEL-Z VEL-MAGNITUDE VEL-TX VEL-TY VEL-TZ VEL-T-MAGNITUDE ACC-X ACC-Y ACC-Z ACC-MAGNITUDE ACC-TX ACC-TY ACC-TZ ACC-T-MAGNITUDE STOPFLAG Whether or not to stop analysis based on monitored value. {NO/YES}
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MONITOR
NO YES
Sec. 5.10 Solution monitoring
No stopping. Variable used for informational use only (printed to .out file) Stop analysis once variable reaches STOPVALUE
STOPVALUE Value at which to stop analysis, used if STOPFLAG=YES. OPERATION Operation for combining data. {AMAX/MAX/MIN} AMAX MAX MIN
[AMAX]
Absolute maximum Maximum Minimum
SET1 [0] Additional data to define monitor. Format depends on TYPE. SET1 = element group number if TYPE= ELAV-GROUP. Otherwise, it is not used. Note that only the first 8 active monitors will be used.
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MONITOR-CONTROL
Chap. 5 Control data
MONITOR-CONTROL
NSTEP-EXPLICIT
Sets control parameters for solution monitoring. NSTEP-EXPLICIT [100] Frequency of solution monitoring in explicit analysis. {1 ≤ NSTEP-EXPLICIT ≤ 99999}
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Chapter 6 Geometry definition
SYSTEM
Chap. 6 Geometry definition
SYSTEM
NAME TYPE MODE XORIGIN YORIGIN ZORIGIN PHI THETA XSI AX AY AZ BX BY BZ P1 P2 P3 MOVE
SYSTEM defines a local coordinate system. Coordinates of geometry points and nodes, input via COORDINATES, refer to the current local coordinate system, as defined by the last preceding use of command SYSTEM. The current system may also be changed via SET SYSTEM. NAME [(highest system label number) + 1] Label number of the local coordinate system. Label number 0 is reserved to identify the global Cartesian coordinate system, and therefore can be used only with the SET SYSTEM command – you cannot redefine the global system.
z
ZL
ZL r
(r, Q, z)
f
Q
(r, Q, f) r
YL
YL XL
XL
Q
Cylindrical coordinates
Spherical coordinates
Relation to the base local coordinate system:
Relation to the base local coordinate system:
XL = z YL = r cosQ ZL = r sinQ
XL = r cosQ sinf YL = r sinQ sinf ZL = r cosf
TYPE [CARTESIAN] The type of local coordinate system. Each type has an underlying base Cartesian system (XL, YL, ZL). See Figure. CARTESIAN
A local Cartesian system, with axes aligned with the base system (XL, YL, ZL).
CYLINDRICAL
A cylindrical local coordinate system with coordinates (r, Θ, z).
SPHERICAL
A spherical local coordinate system with coordinates (r, Θ, φ).
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SYSTEM
MODE [1] Selects the method of local coordinate system definition. This controls which parameters actually define the system – other parameters are ignored. 1
System defined by origin and direction vectors (XORIGIN, YORIGIN, ZORIGIN, AX, AY, AZ, BX, BY, BZ).
2
System defined by origin and Euler angles (XORIGIN, YORIGIN, ZORIGIN, PHI, THETA, XSI).
3
System defined by three geometry points (P1, P2, P3)
XORIGIN YORIGIN ZORIGIN The global system coordinates of the origin of the local coordinate system.
[0.0] [0.0] [0.0]
PHI [0.0] THETA [0.0] XSI [0.0] Euler angles (in degrees) used to define the orientation of the basic system (XL, YL, ZL) with respect to the global Cartesian coordinate system axes. See Figure. Parameters are used only when MODE=2. AX AY AZ Global system components of a vector along the XL-direction.
[1.0] [0.0] [0.0]
BX BY BZ Global system components of a vector in the XL-YL plane.
[0.0] [1.0] [0.0]
P1 P2 P3 Label numbers of geometry points which define the local coordinate system. P1 is the origin of the system, the XL axis is taken from P1 to P2. P3, together with P1, P2, then defines the XL-YL plane. The YL axis is taken orthogonal to the XL axis and points to the same side as P3 of the line between P1 and P2. The ZL axis is then defined by the right hand rule, i.e., using a cross product of unit vectors along the XL,YL axes.
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SYSTEM
Sec. 6.1 Coordinate systems
MOVE [YES] If a local coordinate system is redefined, the geometry points and nodes which refer to this local system would ordinarily be moved to new global positions, since their coordinates refer to the previous definition of the local coordinate system. However, when MOVE = NO the geometry points and nodes can be made to retain their global position, with their local coordinates modified accordingly. {YES/NO} Auxiliary commands SET SYSTEM NAME [0] Once a local coordinate system has been defined, it may be selected as being the currently active system by issuing the command SET SYSTEM. The currently active system is initially the global Cartesian system. SHOW SYSTEM Lists the currently active system. LIST SYSTEM DELETE SYSTEM
FIRST LAST FIRST LAST
Euler Angles
Z'
Z
Y'
PHI
Z'
Y'
THETA Z''
PHI Y X, X'
X' THETA
PHI = rotation about X-axis
X'' YL
XSI
Y'
THETA = rotation about Y'-axis
Z'' XSI ZL
XSI = rotation about X''-axis X''=XL
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COORDINATES POINT
Chap. 6 Geometry definition
COORDINATES POINT (ENTRIES (ENTRIES (ENTRIES (ENTRIES
NAME NAME NAME NAME
SYSTEM
X Y Z SYSTEM) XL YL ZL SYSTEM) R THETA XL SYSTEM) R THETA PHI SYSTEM)
(SYSTEM = global Cartesian (0)) (SYSTEM = local Cartesian) (SYSTEM = local cylindrical) (SYSTEM = local spherical)
ni xi yi zi sysi COORDINATES POINT defines coordinates for geometry points. The coordinates given refer to the local system specified by parameter SYSTEM. SYSTEM [currently active system] Label number of the required local coordinate system. This specifies the coordinate system to which any appended data line coordinates refer (and determines which column heading names are allowed by any ENTRIES data line). ENTRIES Defines, as column headings, the input for the subsequent tabular entries. The heading names depend on the type of local coordinate system specified by parameter SYSTEM. Note:
Less than five entry column headings may be given (e.g., to specify points in a coordinate plane), with previous values retained for omitted entries, but the column heading NAME must always be specified.
ni Label number for the desired geometry point, input under the column heading NAME. xi yi zi Coordinate values in local coordinate system “sysi”.
[0.0] [0.0] [0.0]
[SYSTEM] sysi Local coordinate system label number. Note “sysi” defaults to the system specified by parameter SYSTEM, which in turn defaults to the currently active coordinate system. Auxiliary commands LIST COORDINATES POINT FIRST LAST SYSTEM GLOBAL Lists the coordinates of geometry points with label numbers in a given range, and which are defined in terms of a specified local coordinate system. The coordinates may be listed in terms of the global Cartesian system (GLOBAL = YES). If no range is specified, only label numbers will be listed.
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COORDINATES POINT
Sec. 6.2 Points
DELETE COORDINATES POINT FIRST LAST SYSTEM Deletes all geometry points, and their coordinate data, with label numbers in a given range. Note that a geometry point will not be deleted if it is referenced by a higher order geometry entity (e.g. it is the end point of a line), or a node or other model entity is associated with that point.
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LINE STRAIGHT
Chap. 6 Geometry definition
LINE STRAIGHT
NAME P1 P2
LINE STRAIGHT defines a straight geometry line between two geometry points. P2
(u = 1)
u
P1
(u = 0)
NAME [(current highest geometry line label number) + 1] Label number of the straight geometry line to be defined. P1 P2 Label numbers of the geometry points which are the ends of the straight geometry line. The label numbers P1, P2 must be distinct, but the points may be coincident. A “null” geometry line is defined by this command when the end points P1, P2 are coincident, i.e., they have identical global coordinates. The line has zero length, but may be used in mesh generation, yielding coincident nodes and zero length element edges. Auxiliary commands LIST LINE DELETE LINE STRAIGHT
FIRST LAST ALL FIRST LAST
COPY LINE
NAME TRANSFORMATION NEWNAME PCOINCIDE PTOLERANCE Copies line NAME to NEWNAME via transformation TRANSFORMATION. The endpoints of the new line may optionally be checked for point coincidence. MOVE LINE NAME TRANSFORMATION PCOINCIDE PTOLERANCE Moves line NAME via transformation TRANSFORMATION. The end points of the moved line may optionally be checked for point coincidence.
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LINE ARC
LINE ARC
Sec. 6.3 Lines
NAME MODE P1 P2 P3 CENTER RADIUS ANGLE CHORD PCOINCIDE PTOLERANCE MODIFY-LINES DELETE-POINTS
LINE ARC defines a geometry line as a circular arc, or as an arc with varying radius. NAME [(current highest line label number) + 1] Label number of the arc geometry line. MODE [1] Selects the method of arc geometry line definition. This controls which parameters actually define the arc, other parameters are ignored. See Figure. {1/2/3/4/5/6/7} 1
Arc defined by start point, end point, and center (P1, P2, CENTER).
2
Arc defined by start point, end point, and intermediate point (P1, P2, P3).
3
Arc defined by start point, center, included angle, and a point defining the plane of the arc (P1, CENTER, ANGLE, P3).
4
Arc defined by start point, center, chord length, and a point defining the plane of the arc (P1, CENTER, CHORD, P3).
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LINE ARC
5
Arc defined by start point, end point, radius, and a point defining the plane of the arc (P1, P2, RADIUS, P3).
6
Arc defined by start point, end point, included angle, and a point defining the plane of the arc (P1, P2, ANGLE, P3).
7
Arc defined by two co-planar, non-parallel straight or extruded lines and radius (RADIUS).
P1 Label number of the geometry point at the start of the arc geometry line. P2 Label number of the geometry point at the end of the arc geometry line. P3 Label number of a geometry point either through which the arc geometry line passes (MODE = 2), or, together with the start point and end point or center, defines the plane of the arc (MODE = 3,4,5,6). Note: P3 = 0 corresponds to the origin of the currently active local coordinate system. CENTER Label number of the geometry point at the center of the arc geometry line. RADIUS Radius of the arc geometry line. ANGLE Included angle of the arc geometry line. CHORD Chord length of the arc geometry line. PCOINCIDE [YES] If MODE > 1 then a geometry point will be located at the center or end of the arc. This parameter indicates whether to check the location against existing geometry point coordinates, and use an existing point (YES), rather than generate a new geometry point (with a new label) (NO). {YES/NO} PTOLERANCE [1.0E-5] If PCOINCIDE = YES, this parameter provides a tolerance value for checking the global coordinates of a location against those of existing geometry points.
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LINE ARC
Sec. 6.3 Lines
MODIFY-LINES [YES] Indicates whether or not lines will be modified in order to connect with the created arc. This parameter is used only when MODE=7. {YES/NO} DELETE-POINTS [YES] Indicates whether or not the original points on lines should be deleted if these points are not used after lines are modified. This parameter is used only when MODE=7 and MODIFYLINES=YES. {YES/NO} linei Label number of the lines to define the arc (MODE=7). Notes: All MODES All geometry points referenced by this command – P1, P2, P3, CENTER – must be distinct. Thus the arc is open – to define a complete (closed) circle, command LINE CIRCLE should be used. MODE = 1 The arc defined is circular only if P1 and P2 are equidistant from CENTER – otherwise an arc is defined in which the radius is linearly interpolated across the included angle. The points P1, P2, and CENTER must not be collinear. The included angle is always chosen to be less than 180 degrees – thus a different mode should be used if a semi-circle or an arc subtending an angle greater than 180 degrees is required. No other geometry points are required; the chord length, included angle, and radius (for a circular arc) are calculated. MODE = 2 The arc is defined to pass through the intermediate point P3. A point at the center of the arc is generated. Parameter CENTER may be used to specify the label number of a newly generated point – it defaults to the next highest label number. If so specified, however, CENTER must not be the label number of an existing geometry point. Furthermore, if PCOINCIDE = YES and a geometry point already exists at the arc center – the coincidence check is governed by the tolerance value PTOLERANCE – then that geometry point will be taken to be the center of the arc, ignoring any label specified via parameter CENTER.
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LINE ARC
Chap. 6 Geometry definition
The points P1, P2, and P3 must not be collinear. MODE = 3 The plane of the arc is defined by the points P1, CENTER, and P3, which must not be collinear. Furthermore, ANGLE is measured positive in the direction from P1 to P3. A point at the end of the arc is generated. Parameter P2 may be used to specify the label number of a newly generated point – it defaults to the next highest label number. If so specified, however, P2 must not be the label number of an existing geometry point. Furthermore, if PCOINCIDE = YES and a geometry point already exists at the end of the arc – the coincidence check is governed by the tolerance value PTOLERANCE – then that geometry point will be taken to be the end of the arc, ignoring any label specified via parameter P2. MODE = 4 The plane of the arc is defined by the points P1, CENTER, and P3, which must not be collinear. Furthermore, the end point of the arc is taken to be the same side of the line between the points P1 and CENTER as the point P3. A point at the end of the arc is generated – see MODE = 3. MODE = 5 The plane of the arc is defined by the points P1, P2 and P3, which must not be collinear. The center of the arc is taken to be the same side of the line between the points P1 and P2 as the point P3. A point at the center of the arc is generated – see MODE = 2. MODE = 6 The plane of the arc is defined by the points P1, P2, and P3, which must not be collinear. Furthermore, ANGLE is measured positive in the direction from P1 to P3. A point at the center of the arc is generated – see MODE = 2. Auxiliary commands LIST LINE DELETE LINE ARC
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LINE ARC
Sec. 6.3 Lines
COPY LINE
NAME TRANSFORMATION NEWNAME PCOINCIDE PTOLERANCE Copies line NAME to NEWNAME via transformation TRANSFORMATION. The endpoints of the new line may optionally be checked for point coincidence.
MOVE LINE NAME TRANSFORMATION PCOINCIDE PTOLERANCE Moves line NAME via transformation TRANSFORMATION. The end points of the move line may optionally be checked for point coincidence.
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LINE CIRCLE
Chap. 6 Geometry definition
LINECIRCLE
NAME MODE P1 P2 P3 CENTER RADIUS PCOINCIDE PTOLERANCE
LINE CIRCLE defines a circle geometry line.
P3 (Mode = 1,3) P3 (Mode = 2)
Radius P1
P2 (Mode = 3)
Center
P2 (Mode = 2)
NAME [(current highest geometry line label number) + 1] Label number of the circle to be defined. MODE [1] Selects the method of circle definition. This controls which parameters actually define the circle, other parameters are ignored. See Figure. 1
Circle defined by center, starting point, and a point defining the plane of the circle (CENTER, P1, P3).
2
Circle defined through three points (P1, P2, P3).
3
Circle defined by center, radius, and by two points – one defining the ‘pole’ direction (which intersects the circle at its starting point), and the other defining the plane of the circle (CENTER, RADIUS, P2, P3).
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LINE CIRCLE
Sec. 6.3 Lines
P1 P2 P3 Label numbers of the geometry points which define the circle. CENTER Label number of a geometry point at the center of the circle. RADIUS The radius of the circle. PCOINCIDE [YES] A geometry point will be located at the center (MODE = 2), or the starting point (MODE = 3) of the circle. This parameter indicates whether to check the location against existing geometry point coordinates, and use an existing point (YES) rather than generate a new geometry point (with a new label) (NO). {YES/NO} PTOLERANCE [1.0E-5] If PCOINCIDE = YES, this parameter provides a tolerance value for checking the global coordinates of a location against those of existing geometry points. Note:
A circle is a closed geometry line, a circular arc may be defined by command LINE ARC.
Auxiliary commands LIST LINE DELETE LINE CIRCLE
FIRST LAST ALL FIRST LAST
COPY LINE NAME TRANSFORMATION NEW NAME PCOINCIDE PTOLERANCE Copies line NAME to NEWNAME via transformation TRANSFORMATION. The end points of the new line may optionally be checked for point coincidence. MOVE LINE NAME TRANSFORMATION PCOINCIDE PTOLERANCE Move line name via transformation TRANSFORMATION. The end points of the moved line may optionally be checked for point coincidence.
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LINE CURVILINEAR
Sec. 6.3 Lines
LINE CURVILINEAR
NAME P1 P2 SYSTEM ANGLE
LINE CURVILINEAR defines a geometry line as an interpolated curve in a given local coordinate system; coordinates of points on the curve are linearly interpolated between two geometry points.
P2 ( h21, h22, h23 )
ZL u
j
h i = curvilinear coordinates
YL XL
P1 ( h11, h12, h13 )
ZL
ZL
P1, P2
P1, P2 Q XL
R
R YL
R,Q constant
P1 = P2, ANGLE = THETA
YL XL
f
R,f constant
P1 = P2, ANGLE = PHI
NAME [(current highest geometry line label number) + 1] Label number of the curvilinear geometry line to be defined. P1 P2 Label numbers of the geometry points which are the ends of the curvilinear geometry line.
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LINE CURVILINEAR
Chap. 6 Geometry definition
SYSTEM [current coordinate system] The label number of a coordinate system in which the curve is to be interpolated. ANGLE [THETA] In the case of a spherical coordinate system, if P1 = P2, a circle will be generated by interpolating through 360° in one of the coordinate angles. This parameter selects which angle to use. See Figure. {THETA/PHI} Note:
The geometry line will be a circle in the case where P1 = P2 with a cylindrical or spherical coordinate system. In the case of a Cartesian local system (including the global system) P1 = P2 is not allowed, and the geometry line will be straight.
Auxiliary commands LIST LINE DELETE LINE CURVILINEAR
FIRST LAST ALL FIRST LAST
COPY LINE NAME TRANSFORMATION NEWNAME PCOINCIDE PTOLERANCE Copies line NAME to NEWNAME via transformation TRANSFORMATION. The endpoints of the new line may optionally be checked for point coincidence. MOVE LINE NAME TRANSFORMATION PCOINCIDE PTOLERANCE Moves line NAME via transformation TRANSFORMATION. The end points of the moved line may optionally be checked for point coincidence.
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KNOTS
Sec. 6.3 Lines
KNOTS i
NAME NKNOTS ui
Defines a vector of knot values to be used for non-uniform rational B-spline definition, see LINE POLYLINE (TYPE=NURBS). NAME [(current highest knot vector label )+ 1] Label number of the knot vector. NKNOTS The number of input knot values. { ≥ 4 } i Index of the input knot value. { 1 ≤ i ≤ NKNOTS } ui Knot value for index “i”.
LINE POLYLINE defines a geometry line as a polyline, i.e., a curve controlled by a series of geometry points.
SEGMENTED
QBSPLINE
CBSPLINE
BIARC
BEZIER
SPLINE
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LINE POLYLINE
Sec. 6.3 Lines
NAME [(current highest geometry line label number) + 1] Label number of the polyline geometry line to be defined. TYPE Selects the type of curve to be defined.
[SEGMENTED]
SEGMENTED
The points are connected in sequence by a series of straight line segments. At least two points must be specified.
QBSPLINE
A quadratic B-spline is derived from the control points. Note that the curve passes through the first and last points but not necessarily through the intervening control points. At least three points must be specified.
CBSPLINE
A cubic B-spline is derived from the control points. Note that the curve passes through the first and last points but not necessarily through the intervening control points. At least four points must be specified.
BIARC
Each consecutive pair of points is connected by two circular arcs. The tangent direction of the curve may be specified at any given point. The tangent directions are otherwise calculated by the program. At least three non-collinear points must be specified. Furthermore, all the control points must lie in the same plane, and any specified tangent vector must also lie in that plane – an error message is given if either of these conditions is violated.
BEZIER
A Bezier curve is derived from the control points. Note that the curve passes through the first and last points but not necessarily through the intervening control points. At least three points must be specified.
NURBS
A non-uniform rational B-spline curve is derived from the control points, weights, and knots.
SPLINE
A spline is derivied from the control points. Note that the curvarture of curve is continous at these points. At least two points must be specified.
DEGREE The degree of the B-spline basis functions, must be input for TYPE = NURBS.
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LINE POLYLINE
Chap. 6 Geometry definition
KNOTS The label number of the knot vector (see command KNOTS). The total number of knots used in the spline definition must equal (DEGREE+(number of control points)+1). pointi Label number of geometry point used to interpolate/control the desired curve. The data lines are input in the order of the sequence of points. [0.0] tangxi tangyi [0.0] tangzi [0.0] Vector specifying, with reference to the global Cartesian coordinate system, the tangent direction to the curve at point “pointi “. This vector only influences the shape of the polyline of type BIARC. Input of tangxi = tangyi = tangzi = 0.0 will result in the program automatically calculating the tangent direction from the slope of the quadratic curve interpolated through the point and its immediate neighbors in the sequence. Note:
A polyline may be closed be selecting the first and last points in the sequence to refer to the same geometry point.
Note:
For BIARC interpolation a straight line segment may be defined by making the tangent line at a point pass through its neighbor point.
weighti The weight at each control point. Auxiliary commands LIST LINE DELETE LINE POLYLINE
FIRST LAST ALL FIRST LAST
COPY LINE NAME TRANSFORMATION NEWNAME PCOINCIDE PTOLERANCE Copies line NAME to NEWNAME via transformation TRANSFORMATION. The end points of the new line may optionally be checked for point coincidence. MOVE LINE NAME TRANSFORMATION PCOINCIDE PTOLERANCE Moves line NAME via transformation TRANSFORMATION. The end points of the moved line may optionally be checked for point coincidence.
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LINE SECTION
LINE SECTION
Sec. 6.3 Lines
NAME PARENT USTART UEND PCOINCIDE PTOLERANCE COUPLED P1 P2
LINE SECTION defines a geometry line to be part of another geometry line.
up = 1 up =
up =
USTART P1 (u = 0)
UEND u
P2
(u = 1)
up = 0
NAME [(current highest geometry line label number) + 1] Label number of the section geometry line to be defined. PARENT The line upon which the section line is defined. USTART [0.0] The line parameter (0.0 ≤ USTART ≤ 1.0) indicating the starting position on the line PARENT. UEND [1.0] The line parameter (0.0 ≤ UEND ≤ 1.0) indicating the end position on the line PARENT. PCOINCIDE [YES] This parameter indicates whether or not to check the location of the section line end points against existing geometry point coordinates, and use an existing point (YES) rather than generate a new geometry point (with a new label) (NO). {YES/NO} PTOLERANCE [TOLERANCES GEOMETRIC] If PCOINCIDE = YES, this parameter provides a tolerance value for checking the global coordinates of a location against those of existing geometry points. COUPLED If COUPLED=YES, then the parent line cannot be modified. {YES/NO}
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LINE SECTION
Chap. 6 Geometry definition
P1 Label number of the geometry point corresponding to USTART.
[0]
P2 Label number of the geometry point corresponding to UEND.
[0]
Auxiliary commands LIST LINE DELETE LINE SECTION
FIRST LAST ALL FIRST LAST
COPY LINE NAME TRANSFORMATION NEWNAME PCOINCIDE PTOLERANCE Copies line NAME to NEWNAME via transformation TRANSFORMATION. The end points of the new line may optionally be checked for point coincidence. MOVE LINE NAME TRANSFORMATION PCOINCIDE PTOLERANCE Moves line NAME via transformation TRANSFORMATION. The end points of the moved line may optionally be checked for point coincidence.
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LINE COMBINED
LINE COMBINED
Sec. 6.3 Lines
NAME COUPLED
linei LINE COMBINED defines a geometry line as a combination of other geometry lines. The defining or “parent” lines must form a connected sequence. The combined line may be closed, by virtue of having connected first and last line subsegments.
L2
(u = 0)
P2
(u = 1)
u
L1 P1
P3 LINE COMBINED L1 // L2
NAME [(current highest geometry line label number) + 1] Label number of the combined geometry line to be defined. COUPLED If COUPLED=YES, then the parent line cannot be modified. {YES/NO}
[YES]
linei Label number of a parent geometry line. Auxiliary commands LIST LINE FIRST LAST ALL DELETE LINE COMBINED FIRST LAST COPY LINE NAME TRANSFORMATION NEWNAME PCOINCIDE PTOLERANCE Copies line NAME to NEWNAME via transformation TRANSFORMATION. The end point of the new line may optionally be checked for point coincidence. MOVE LINE NAME TRANSFORMATION PCOINCIDE PTOLERANCE Moves line NAME via transformation TRANSFORMATION. The end points of the moved line may optionally be checked for point coincidence.
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LINE REVOLVED
Chap. 6 Geometry definition
LINE REVOLVED
NAME MODE POINT ANGLE SYSTEM AXIS ALINE AP1 AP2 X0 Y0 Z0 XA YA ZA PCOINCIDE PTOLERANCE
LINE REVOLVED defines a geometry line (a circular arc) by rotating a geometry point about an axis. AXIS P2 (u = 1) u ANGLE
POINT (u = 0)
NAME [(current highest geometry line label number) + 1] Label number of the revolved geometry line. MODE [AXIS] Selects the method of defining the axis of revolution used to define the geometry line. This controls which parameters actually define the revolved line, other parameters are ignored. AXIS
The axis of revolution is taken as a given axis of a coordinate system. (POINT, ANGLE, SYSTEM, AXIS).
LINE
The axis of revolution is taken as the straight line between the end points of a given geometry line (which is not necessarily straight, but must be open – i.e., have non-coincident end points). (POINT, ANGLE, ALINE).
POINTS
The axis of revolution is taken as the straight line between two given (non-coincident) geometry points. (POINT, ANGLE, AP1, AP2).
VECTORS
The axis of revolution is defined by a position vector and a direction vector. (POINT, ANGLE, X0, Y0, Z0, XA, YA, ZA).
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LINE REVOLVED
Sec. 6.3 Lines
POINT Label number of the initial geometry point to be rotated about the desired axis. ANGLE Angle of rotation (in degrees). Note ANGLE must be in the range -360 ≤ ANGLE ≤ 360 (with ANGLE = 360 or -360 defining a closed line, i.e., a circle). The sign of the angle is given by considering the right hand rule – i.e., if you curl your fingers around the axis of revolution, with the thumb pointing along the axis, then a positive angle is in the direction of the curl of the fingers. SYSTEM [currently active coordinate system] Label number of a coordinate system. One of the axes of this coordinate system may be used to define the axis of revolution, via parameter AXIS, when MODE = AXIS. AXIS [XL] Selects which of the base axes (XL, YL, ZL) of the local coordinate system, given by parameter SYSTEM, is used as the axis of revolution. {XL/YL/ZL} ALINE Label number of a geometry line which defines the axis of revolution. The direction of the axis is taken from the start point of the line to the end point of the line. AP1, AP2 Label numbers of geometry points which define the axis of revolution. The direction of the axis is taken from point AP1 to point AP2. X0 [0.0] Y0 [0.0] Z0 [0.0] Global coordinates of the position vector defining a point on the axis of rotation when MODE = VECTORS. XA [1.0] YA [0.0] ZA [0.0] Components (with respect to the global coordinate system) of the axis of rotation when MODE = VECTORS. PCOINCIDE [YES] A geometry point is to be located at the other end of the line from the initial point given by POINT. This parameter indicates whether to check the location against existing geometry point coordinates, and use an existing point (YES) rather than generate a new geometry point (with a new label) (NO). {YES/NO}
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Chap. 6 Geometry definition
LINE REVOLVED
PTOLERANCE [1.0E-5] If PCOINCIDE = YES, this parameter provides a tolerance value for checking the global coordinates of a location against those of existing geometry points. Auxiliary commands LIST LINE FIRST LAST ALL DELETE LINE REVOLVED FIRST LAST COPY LINE NAME TRANSFORMATION NEWNAME PCOINCIDE PTOLERANCE Copies line NAME to NEWNAME via transformation TRANSFORMATION. The end points of the new line may optionally be checked for point coincidence. MOVE LINE NAME TRANSFORMATION PCOINCIDE PTOLERANCE Moves line NAME via transformation TRANSFORMATION. The end points of the moved line may optionally be checked for point coincidence.
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LINE EXTRUDED
Sec. 6.3 Lines
LINE EXTRUDED
NAME POINT DX DY DZ SYSTEM PCOINCIDE PTOLERANCE
LINE EXTRUDED defines a geometry line by displacing a geometry point in a given direction.
ZL
P2 (u = 1) P2 = POINT+ (DX, DY) u YL
XL
POINT: (u = 0)
NAME [(current highest geometry line label number) + 1] Label number of the extruded geometry line. POINT Label number of the initial geometry point to be displaced. DX [1.0] DY [0.0] DZ [0.0] Components of displacement vector with reference to the base coordinates (XL, YL, ZL) of system SYSTEM. Note that this is the actual displacement vector, i.e., it specifies both magnitude and direction. SYSTEM [currently active coordinate system] Label number of a coordinate system which is referenced by the displacement vector (DX, DY, DZ). PCOINCIDE [YES] A geometry point is to be located at the other end of the line from the initial point given by POINT. This parameter indicates whether to check the location against existing geometry point coordinates, and use an existing point (YES) rather than generate a new geometry point (with a new label) (NO). {YES/NO} PTOLERANCE [TOLERANCES GEOMETRIC] If PCOINCIDE = YES, this parameter provides a tolerance value for checking the global coordinates of a location against those of existing geometry points.
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LINE EXTRUDED
Auxiliary commands LIST LINE FIRST LAST ALL DELETE LINE EXTRUDED FIRST LAST COPY LINE NAME TRANSFORMATION NEWNAME PCOINCIDE PTOLERANCE Copies line NAME to NEWNAME via transformation TRANSFORMATION. The end points of the new line may optionally be checked for point coincidence. MOVE LINE NAME TRANSFORMATION PCOINCIDE PTOLERANCE Moves line NAME via transformation TRANSFORMATION. The end points of the moved line may optionally be checked for point coincidence.
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LINE TRANSFORMED
LINE TRANSFORMED
Sec. 6.3 Lines
NAME PARENT TRANSFORMATION PCOINCIDE PTOLERANCE NCOPY
linei LINE TRANSFORMED defines a geometry line to be a geometrical transformation of another (existing) geometry line. The transformed geometry line is identified by its label number NAME. If NCOPY is greater than 1, the other newly defined transformed geometry lines are identified by the current highest geometry line label number + 1. NAME [(current highest geometry line label number) + 1] Label number of the transformed geometry line. PARENT The line which, after transformation, gives the line to be defined. TRANSFORMATION Label number of a geometrical transformation, see TRANSFORMATION. PCOINCIDE [NO] This parameter indicates whether or not to check the location of the transformed line end points against existing geometry point coordinates, and use an existing point (YES) rather than generate a new geometry point (with a new label) (NO). {YES/NO} PTOLERANCE [TOLERANCES GEOMETRIC] If PCOINCIDE = YES, this parameter provides a tolerance value for checking the global coordinates of a location against those of existing geometry points. NCOPY [1] Parameter defines number of lines to be generated by the transformation - transformation is repeated NCOPY times. linei Line label number to be transformed. Auxiliary commands LIST LINE DELETE LINE TRANSFORMED
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LINE TRANSFORMED
COPY LINE
NAME TRANSFORMATION NEWNAME PCOINCIDE PTOLERANCE Copies line NAME to NEWNAME via transformation TRANSFORMATION. The end point of the new line may optionally be checked for point coincidence. MOVE LINE NAME TRANSFORMATION PCOINCIDE PTOLERANCE Moves line NAME via transformation TRANSFORMATION. The end points of the moved line may optionally be checked for point coincidence.
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SPLIT-LINE
Sec. 6.3 Lines
SPLIT-LINE
NAME USPLIT LINE1 LINE2 COUPLED
SPLIT-LINE creates two geometry lines of type SECTION by “splitting” a given line into two parts connected at some point on the given line, specified via a parameter value along the line.
P2 (u = 1)
LINE 1 u
u = USPLIT
LINE 2
P1 (u = 0) NAME Label number of the geometry line to be split. Note that this line is not altered by this command. Two new lines are created coincident with the line NAME. USPLIT [0.5] A parameter value indicating the point along line NAME at which splitting takes place. The parameter value can range between 0.0 (the starting point of line NAME) to 1.0 (the end point of line NAME), but cannot be 0.0 or 1.0, i.e., the splitting point on the line must create two new lines of non-zero length. LINE1 [(highest line label number) + 1] The label number of the new line created ranging from the starting point of line NAME (u = 0.0) to the splitting point (u = USPLIT). Note that LINE1 must not have been previously defined. LINE2 [(highest line label number) + 2] The label number of the new line created ranging from the splitting point (u = USPLIT) to the end point (u = 1.0) of line NAME. Note that LINE2 must not have been previously defined. COUPLED If COUPLED=YES, then the parent line cannot be modified. {YES/NO}
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[YES]
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Chap. 6 Geometry definition
LNTHICKNESS
LNTHICKNESS linei thicki dthick1i dthick2i LNTHICKNESS defines line thicknesses (useful for defining axisymmetric shell thicknesses, for example).
u
ick2
thic k+
ck 1
dthi
P2
dth
k+
thic P1
linei The line label number. thicki The line thickness.
[0.0]
dthick1i The deviation of the thickness at the start point of “linei”.
[0.0]
dthick2i The deviation of the thickness at the end point of “linei”.
[0.0]
Note:
For a constant thickness only the data line entry “thicki” need be specified. The thickness may be varied linearly along the line by specifying non-zero deviations and the ends of the line.
Auxiliary commands LIST LNTHICKNESS DELETE LNTHICKNESS
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SURFACE PATCH
Sec. 6.4 Surfaces
SURFACE PATCH
NAME EDGE1 EDGE2 EDGE3 EDGE4
SURFACE PATCH defines a geometry surface to be bounded by edges which are specified geometry lines.
EDGE1
P2
P1
EDGE2 v P3
EDGE4 u
EDGE3
P4
NAME [(current highest geometry surface label number) + 1] Label number of the geometry surface. EDGE1 [existing surface edge, if any] EDGE2 EDGE3 EDGE4 Label numbers of geometry lines comprising edges of the geometry surface. To indicate a missing edge, either the corresponding parameter is not specified or, equivalently, a zero label number may be given. See Figure. Note: The edge geometry lines must form a connected sequence, i.e., their end points must match. Otherwise an error condition results. At least two edges must be specified. If two adjacent edges are specified, then a unique connecting edge is searched for to form a triangular surface patch. If two opposite edges (EDGE1 and EDGE3, or EDGE2 and EDGE4) are specified then the missing two edges are searched for to form a quadrilateral surface patch, unless the given edges are connected, in which case a single connecting edge is searched for to yield a triangular surface patch. If three edges are specified, then a unique connecting edge is searched for, unless the three edges by virtue of their connection already form a triangular surface patch. In each case of a “missing” edge, if no line is found to represent the surface edge, then a straight line will be created with label number incremented from the current highest line label number.
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SURFACE PATCH
Chap. 6 Geometry definition
If more than one line could represent the missing surface edge, then a warning message is given with no surface created. Auxiliary commands LIST SURFACE DELETE SURFACE
FIRST LAST FIRST LAST OPTION
When deleting surfaces, OPTION = ALL will delete any vertex points or edge lines which have no other dependent geometry; otherwise (OPTION = SURFACE), only the surface itself will be deleted.
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SURFACE VERTEX
Sec. 6.4 Surfaces
SURFACE VERTEX
NAME P1 P2 P3 P4 EDGE1 EDGE2 EDGE3 EDGE4
SURFACE VERTEX defines a geometry surface to be bounded by edges which are specified by their end geometry points – the vertices of the surface. This command is similar to SURFACE PATCH – the underlying surface representation is identical – only the method of definition differs. If no geometry line exists between adjacent geometry points, then the command will automatically generate straight geometry lines between the appropriate geometry point pairs.
P2
EDGE1
P1
EDGE2 v EDGE4 P3
u
EDGE3
P4 P2
EDGE1
P1 (P4)
EDGE2
EDGE3 v
u P3
NAME [(highest geometry surface label number) + 1] Label number of the geometry surface. P1, P2, P3, P4 Label numbers of geometry points which are the vertices of the geometry surface. See Figure. P1, P2, P3 must be specified, and correspond to existing geometry points. A triangular surface patch is defined by repeating one pair of consecutive points (i.e., P2 = P1, P3 = P2, P4 = P3, or P1 = P4). Note that P4 defaults to P1, automatically giving a triangular surface patch if only P1, P2, P3 are specified. ADINA R & D, Inc.
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SURFACE VERTEX
Chap. 6 Geometry definition
EDGEi [existing surface edges, if any] Label numbers of the surface edges (i = 1, 2, 3, 4), i.e., geometry lines, input if required – see below. The parameters are related to the surface vertices as follows: EDGE1
Line from P1 to P2.
EDGE2
Line from P2 to P3.
EDGE3
Line from P3 to P4.
EDGE4
Line from P4 to P1.
If a pair of adjacent vertices is not connected by a geometry line, then a new straight line is generated between them. The label number of the new edge is given by the appropriate EDGEi parameter. Note that in this case the parameter must not refer to an existing line. If no label is given then the highest line label number successively incremented by 1 is used. If more than one line connects a pair of adjacent vertices, then the choice of line may be made via the appropriate EDGEi parameter. In this case the parameter must refer to one of the lines connecting the relevant pair of vertices. Auxiliary commands LIST SURFACE DELETE SURFACE
FIRST LAST FIRST LAST OPTION
When deleting surfaces, OPTION = ALL will delete any vertex points or edge lines which have no other dependent geometry; otherwise (OPTION = SURFACE), only the surface itself will be deleted.
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SURFACE GRID
Sec. 6.4 Surfaces
SURFACE GRID NAME MPOINT NPOINT TYPE EDGE1 EDGE2 EDGE3 EDGE4 1 1 point1 ... irowi jcoli pointi ... MPOINT NPOINT pointMN SURFACE GRID defines a geometry surface as a grid (array) of geometry points, which control the shape of the surface. NAME [(current highest geometry surface label number) + 1] Label number of the geometry surface to be defined. MPOINT Number of rows in the array of surface grid control points.
[4]
NPOINT Number of columns in the array of surface grid control points.
[4]
TYPE Selects the type of surface to be defined.
[POLYFACE]
POLYFACE
The grid of control points is connected by a quadrilateral polygo nal mesh. MPOINT and NPOINT each have a minimum value of 2 for this surface type.
QBSPLINE
A quadratic B-spline surface is derived from the grid of control points. MPOINT and NPOINT each have a minimum value of 3 for this surface type.
CBSPLINE
A cubic B-spline surface is derived from the grid of control points. MPOINT and NPOINT each have a minimum value of 4 for this surface type.
BEZIER
A Bezier surface is derived from the grid of control points. MPOINT and NPOINT each have a minimum value of 3 for this surface type.
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SURFACE GRID
Chap. 6 Geometry definition
EDGEi [existing edge surfaces, if any] Label numbers of the surface edges (i = 1, 2, 3, 4), i.e., geometry lines, input if required – see below. The parameters are related to the surface control points as follows (see Figure): EDGE1
Polyline defined by points (i, j):
i = MPOINT, j = 1, 2, ..., NPOINT
EDGE2
polyline defined by points (i, j):
i = 1, 2, ..., MPOINT, jcol = 1
EDGE3
polyline defined by points (i, j):
i = 1, j = 1, 2, ..., NPOINT
EDGE4
polyline defined by points (i, j):
i = 1,2,...,MPOINT, jcol = NPOINT
If a set of edge control points does not already define a polyline of the corresponding type (see note and table below) then a new polyline is generated. The label number of the new edge is given by the appropriate EDGEi parameter. Note that in this case the parameter must not refer to an existing line. If no label is given then the highest line label number successively incremented by 1 is used. If more than one polyline of the corresponding type is defined by a set of edge control points, then the choice of polyline is made via the appropriate EDGEi parameter. In this case the parameter must refer to one of the polylines defined by the relevant set of edge control points.
(MPOINT,1)
EDGE1 (MPOINT,NPOINT)
EDGE2
EDGE4
(1,1)
EDGE3
(1,NPOINT)
Surface-grid definition
TYPE=POLYFACE, MPOINT=3, NPOINT=4
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SURFACE GRID
Sec. 6.4 Surfaces
irowi, jcoli Row and column number, respectively, of the point “pointi” entry in the array of control points. The following range of values are allowed: 1 1
≤ ≤
irowi jcoli
≤ ≤
MPOINT NPOINT
pointi Label number of geometry point used to interpolate/control the desired surface. Note:
A point label is required input for each entry (irow, jcol) in the array of points; irow = 1, 2, ..., MPOINT; jcol = 1, 2, ..., NPOINT.
Note:
A line of type POLYLINE may be created at each edge of the surface, according to the following rule:
Surface Grid Type
Edge Polyline Type
POLYFACE
SEGMENTED
QBSPLINE
QBSPLINE
CBSPLINE
CBSPLINE
BEZIER
BEZIER
Auxiliary commands LIST SURFACE DELETE SURFACE
FIRST LAST FIRST LAST OPTION
When deleting surfaces, OPTION = ALL will delete any vertex points or edge lines which have no other dependent geometry; otherwise (OPTION = SURFACE), only the surface itself will be deleted.
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SURFACE EXTRUDED
Chap. 6 Geometry definition
SURFACE EXTRUDED
NAME LINE DX DY DZ SYSTEM PCOINCIDE PTOLERANCE NDIV OPTION ELINE
linei SURFACE EXTRUDED defines a geometry surface by displacing a geometry line in a given direction.
ZL
YL
v (DX, DY, DZ)
XL
LINE u
NAME [(current highest geometry surface label number) + 1] Label number of the extruded geometry surface. LINE Label number of the initial geometry line to be displaced, thereby defining the extruded surface. DX [1.0] DY [0.0] DZ [0.0] Components of displacement vector with respect to the base coordinates (XL, YL, ZL) of coordinate system SYSTEM. Note that this is the actual displacement vector, i.e., it specifies both magnitude and direction. SYSTEM [currently active coordinate system] Label number of a coordinate system which is referenced by the displacement vector (DX, DY, DZ).
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SURFACE EXTRUDED
Sec. 6.4 Surfaces
PCOINCIDE [YES] Geometry points are to be located at the other end of the surface from the initial line given by LINE. This parameter indicates whether to check point’s location against existing geometry point coordinates, and use an existing point (YES) rather than generate a new geometry point (with a new label) (NO). {YES/NO} PTOLERANCE [1.0E-5] If PCOINCIDE = YES, this parameter provides a tolerance value for checking the global coordinates of a location against those of existing geometry points. NDIV [DEFAULT] Number of subdivisions assigned to the surface in the extruded direction. The DEFAULT number of subdivisions is taken from the parameter NDIV in the command SUBDIVIDE DEFAULT. This parameter is only used when OPTION=VECTOR. OPTION This parameter offers options to the surface extrusion:
[VECTOR]
VECTOR
surfaces are defined by displacing geometry lines in a given direction.
LINE
surfaces are defined by displacing geometry lines along a line.
ELINE The geometry line label. This parameter is only used when OPTION=LINE linei Label numbers of geometry lines. The data line input allows for more than one line to be extruded. Auxiliary commands LIST SURFACE DELETE SURFACE
FIRST LAST FIRST LAST OPTION
When deleting surface, OPTION = ALL will delete any vertex points or edge lines which have no other dependent geometry; otherwise (OPTION = SURFACE), only the surface itself will be deleted.
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SURFACE REVOLVED
Chap. 6 Geometry definition
SURFACE REVOLVED
NAME MODE LINE ANGLE SYSTEM AXIS ALINE AP1 AP2 X0 Y0 Z0 XA YA ZA PCOINCIDE PTOLERANCE NDIV
linei
AXIS
ANGLE LINE u
v
SURFACE REVOLVED defines a geometry surface by rotating a geometry line about some axis. NAME [(current highest geometry surface label number) + 1] Label number of the revolved geometry surface. MODE [AXIS] Selects the method of defining the axis of revolution used to define the geometry surface. This controls which parameters actually define the revolved surface. Other parameters are ignored. AXIS
The axis of revolution is taken as a given coordinate axis of a coordinate system. (LINE, ANGLE, SYSTEM, AXIS).
LINE
The axis of revolution is taken as the straight line between the end points of a given geometry line (which is not necessarily straight, but must be open, i.e., have non-coincident end points). (LINE, ANGLE, ALINE).
POINTS
The axis of revolution is taken as the straight line between two given (non-coincident) geometry points. (LINE, ANGLE, AP1, AP2).
VECTORS
The axis of revolution is defined by a position vector and a direction vector. (LINE, ANGLE, X0, Y0, Z0, XA, YA, ZA).
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SURFACE REVOLVED
Sec. 6.4 Surfaces
LINE Label number of the initial geometry line to be rotated about the axis thereby defining the revolved surface. ANGLE Angle of rotation (in degrees). Note ANGLE must be in the range -360 ≤ ANGLE ≤ 360. The sign of the angle is given by considering the right hand rule – i.e., if you curl your fingers around the axis of revolution, with the thumb pointing along the axis, then a positive angle is in the direction of the curl of the fingers. SYSTEM [currently active coordinate system] Label number of a coordinate system. One of the axes of this coordinate system may be used to define the axis of revolution, via parameter AXIS, when MODE = AXIS. AXIS [XL] Selects which of the basic axes (XL, YL, ZL) of the local coordinate system, given by parameter SYSTEM, is used as the axis of revolution. {XL/YL/ZL} ALINE Label number of a geometry line which defines the axis of revolution. The direction of the axis is taken from the start point of the line to the end point of the line. AP1, AP2 Label numbers of geometry points which define the axis of revolution. The direction of the axis is taken from point AP1 to point AP2. X0 [0.0] Y0 [0.0] Z0 [0.0] Global coordinates of the position vector defining a point on the axis of rotation when MODE = VECTORS. XA [1.0] YA [0.0] ZA [0.0] Components (with respect to the global coordinate system) of the axis of rotation when MODE = VECTORS. PCOINCIDE [YES] Geometry points/lines are to be located at the edges of the surface beside the initial line given by LINE. This parameter indicates whether to check the edge point location against existing geometry, and use an existing point (YES) rather than generate a new geometry point (with a new label) (NO). {YES/NO}
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Chap. 6 Geometry definition
SURFACE REVOLVED
PTOLERANCE [1.0E-5] If PCOINCIDE = YES, this parameter provides a tolerance value for checking the global coordinates of a location against those of existing geometry points. NDIV [DEFAULT] Number of subdivisions assigned to the surface in the revolved direction. The DEFAULT number of subdivisions is taken from the parameter NDIV in the command SUBDIVIDE DEFAULT. linei Label numbers of geometry lines. The data line input allows for more than one line to be revolved. Auxiliary commands LIST SURFACE DELETE SURFACE
FIRST LAST FIRST LAST OPTION
When deleting surface, OPTION = ALL will delete any vertex points or edge lines which have no other dependent geometry; otherwise (OPTION = SURFACE), only the surface itself will be deleted.
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SURFACE TRANSFORMED
SURFACE TRANSFORMED
Sec. 6.4 Surfaces
NAME PARENT TRANSFORMATION PCOINCIDE PTOLERANCE NCOPY
surfacei SURFACE TRANSFORMED defines a geometry surface to be a geometrical transformation of another existing geometry surface. The transformed geometry surface is identified by its label number NAME. If NCOPY is greater than 1, the other newly defined transformed geometry surfaces are identified by the current highest geometry surface label number + 1. NAME [(current highest geometry surface label number) + 1] Label number of the geometry surface to be defined. PARENT The surface which, after transformation, gives the surface being defined. TRANSFORMATION Label number of a geometrical transformation, see commands TRANSFORMATION. PCOINCIDE [NO] This parameter indicates whether to check the location of the transformed surface vertices against existing geometry point coordinates, and use an existing point (YES) rather than generate a new geometry point (with a new label) (NO). {YES/NO} PTOLERANCE [1.0E-5] If PCOINCIDE = YES, this parameter provides a tolerance value for checking the global coordinates of a location against those of existing geometry points. NCOPY [1] Parameter defines number of surfaces to be generated by the transformation - transformation is repeated NCOPY times. surfacei Label numbers of surface to be transformed. Auxiliary commands LIST SURFACE DELETE SURFACE
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FIRST LAST FIRST LAST OPTION
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SFTHICKNESS
Chap. 6 Geometry definition
SFTHICKNESS namei thicki dthick1i dthick2i dthick3i dthick4i SFTHICKNESS defines surface thicknesses. namei The surface label number. thicki The surface thickness.
[0.0]
dthick1i The deviation of thickness for surface “surfacei” at surface vertex 1.
[0.0]
dthick2i The deviation of thickness for surface “surfacei” at surface vertex 2.
[0.0]
dthick3i The deviation of thickness for surface “surfacei” at surface vertex 3.
[0.0]
dthick4i The deviation of thickness for surface “surfacei” at surface vertex 4.
[0.0]
Note:
Input of surface thickness is given as a constant thickness together with deviations from that value at each of the vertices. Thus the thickness at vertex1 = thick + dthick1. To input constant surface thicknesses, only the first two entries on the data line input need be entered (since the default deviations are zero). To input varying surface thickness you could enter a constant thickness of 0.0 and set the deviations to the vertex thicknesses, or use some median thickness with non-zero deviations.
Note:
Thickness is measured in the direction of the normal vector at the vertex, determined by the right-hand rule in relation to the ordering of the surface vertices.
Auxiliary commands LIST SFTHICKNESS
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CHECK-SURFACES
Sec. 6.4 Surfaces
CHECK-SURFACES CHECK-SURFACES checks geometry surface connections looking for two adjoining surfaces which are oppositely oriented such that the surface normals would be opposite. Such conditions would likely be the source of a modeling error when elements of type SHELL are generated on such surfaces. The command has no parameters and reports geometry surface pairs which should be more closely examined and re-oriented if necessary.
P3
P4 n1
v
v u
u
v1
S2
S1
P1
P2
u1
Surface S1 S2
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P6
v2
n2 u2
P5
Vertices P1-P2-P3-P4 P2-P3-P6-P5
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VOLUME PATCH
Chap. 6 Geometry definition
VOLUME PATCH
NAME SHAPE FACE1 FACE2 FACE3 FACE4 FACE5 FACE6
VOLUME PATCH defines a geometry volume to be bounded by faces which are specified geometry surfaces.
SHAPE = HEX
SHAPE = PRISM
FACE 2
P2 FACE 3 P4
E5
C FA
P6
FACE 1 P4
P3 P5
P1
P2
FACE 3
FACE 1
P3
FACE 2
P1
FACE 4
E5
FAC
P5
FACE 4 P7
P8
P6
FACE 6
SHAPE = TETRA P2
FACE 3 P3
SHAPE = PYRAMID
FACE 1 FACE 4
P4
P2
FACE 3 P1 FACE 2
P3
FACE 2
FACE 1 FACE 4
P1 P4
FACE 5
P5
NAME [(current highest geometry volume label number) + 1] Label number of the geometry volume. 6-50
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VOLUME PATCH
Sec. 6.5 Volumes
SHAPE [HEX] Selects the shape of the volume to be defined. This controls which of the parameters (geometry surface label numbers) are actually used to define the volume, other parameters are ignored. The faces of the volume must connect as shown in the Figures. HEX
Hexahedral “brick” volume (FACE1, FACE2, FACE3, FACE4, FACE5, FACE6). Note that each face must be a quadrilateral geometry surface.
PRISM
Prismatic volume (FACE1, FACE2, FACE3, FACE4, FACE5). Note that faces FACE2 and FACE4 must be triangular geometry surfaces, whilst faces FACE1, FACE3, and FACE5 must be quadrilateral geometry surfaces.
TETRA
Tetrahedral volume (FACE1, FACE2, FACE3, FACE4). Note that each face must be a triangular geometry surface.
PYRAMID
5-faced volume (FACE1, FACE2, FACE3, FACE4, FACE5). Note that face FACE1 must be a quadrilateral geometry surface, whilst faces FACE2, FACE3, FACE4, and FACE5 must be triangular geometry surfaces.
FACE1 FACE2 FACE3 FACE4 FACE5 FACE6 Label numbers of geometry surfaces comprising the faces of the geometry volume. See Figure. Note:
The faces must be connected, i.e., the edges of adjacent faces (geometry surfaces) must coincide (i.e., refer to a common geometry line), otherwise an error condition results.
Auxiliary commands LIST VOLUME DELETE VOLUME
FIRST LAST FIRST LAST OPTION
When deleting volume, OPTION = ALL will delete any vertex points, edge lines or face surfaces which have no other dependent geometry; otherwise (OPTION = VOLUME), only the volume itself will be deleted.
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VOLUME VERTEX
Chap. 6 Geometry definition
VOLUME VERTEX
NAME SHAPE VERTEX1 VERTEX2 VERTEX3 VERTEX4 VERTEX5 VERTEX6 VERTEX7 VERTEX8
VOLUME VERTEX defines a geometry volume in terms of its vertices. This command is similar to VOLUME PATCH – the underlying volume geometry point representation is identical, only the method of definition differs. If no geometry line exists between adjacent geometry points, then the command will automatically generate straight geometry lines between the appropriate geometry point pairs. If the volume edges do not comprise the edges of existing geometry surfaces at the faces of the volume, then the command will automatically generate geometry surfaces at the volume faces with the required edges (existing or generated).
SHAPE = HEX
SHAPE = PRISM
P2
P1
P4
P3
P4
P3
P5
P6
P7
P5
P8
P6
SHAPE = TETRA
SHAPE = PYRAMID P2
P3
P2 P1
P4
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P2
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AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
VOLUME VERTEX
Sec. 6.5 Volumes
NAME [(current highest geometry volume label number) + 1] Label number of the geometry volume. SHAPE [HEX] Selects the shape of the volume to be defined. This controls which of the parameters (geometry point label numbers) are actually used to define the volume – other parameters are ignored. The vertices of the volume must connect as shown in the Figure. HEX
Hexahedral “brick” volume.
PRISM
Prismatic volume.
TETRA
Tetrahedral volume.
PYRAMID
5-faced volume.
VERTEXi (i = 1…8) Label numbers of geometry points which are the vertices of the geometry volume. See Figure for vertex numbering. Auxiliary commands LISTVOLUME DELETE VOLUME
FIRST LAST FIRST LAST OPTION
When deleting volumes, OPTION = ALL will delete any vertex points, edge lines or face surfaces which have no other dependent geometry; otherwise (OPTION = VOLUME), only the volume itself will be deleted.
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VOLUME REVOLVED
Chap. 6 Geometry definition
VOLUME REVOLVED
NAME MODE SURFACE ANGLE SYSTEM AXIS ALINE AP1 AP2 X0 Y0 Z0 XA YA ZA PCOINCIDE PTOLERANCE NDIV
surfacei VOLUME REVOLVED defines one or more geometry volumes by rotating one or more geometry surfaces about an axis. The first newly defined geometry volume is identified by its label number NAME. The other newly defined geometry volumes are identified by the current highest geometry volume label number + 1. AXIS
ANGLE
P2
P1 SURFACE
P3
P4
NAME [(current highest geometry volume label number) + 1] Label number of the revolved geometry volume. MODE [AXIS] Selects the method of defining the axis of revolution used to define the geometry volume. This controls which parameters actually define the revolved volume. Other parameters are ignored. AXIS The axis of revolution is taken as a given coordinate axis of a coordinate system. (SURFACE, ANGLE, SYSTEM, AXIS). LINE
The axis of revolution is taken as the straight line between the end points of a given geometry line (which is not necessarily straight, but must be open – i.e., have non-coincident end points). (SURFACE, ANGLE, ALINE).
POINTS
The axis of revolution is taken as the straight line between two given (non-coincident) geometry points. (SURFACE, ANGLE, AP1, AP2).
VECTORS
The axis of revolution is defined by a position vector and a direction vector. (SURFACE, ANGLE, X0, Y0, Z0, XA, YA, ZA).
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VOLUME REVOLVED
Sec. 6.5 Volumes
SURFACE Label number of the initial geometry surface to be rotated about the axis, thereby defining the revolved volume. ANGLE Angle of rotation (in degrees). Note ANGLE must be in the range -360 ≤ ANGLE ≤ 360 (with ANGLE = 360 or -360 defining a closed line, i.e., a circle). The sign of the angle is given by considering the right hand rule – i.e., if you curl your fingers around the axis of revolution, with the thumb pointing along the axis, then a positive angle is in the direction of the curl of the fingers. SYSTEM [currently active coordinate system] Label number of a coordinate system. One of the axes of this coordinate system may be used to define the axis of revolution, via parameter AXIS, when MODE = AXIS. AXIS [XL] Selects which of the base axes (XL, YL, ZL) of the local coordinate system, given by parameter SYSTEM, is used as the axis of revolution. {XL/YL/ZL} ALINE Label number of a geometry line which defines the axis of revolution. The direction of the axis is taken from the start point of the line to the end point of the line. AP1, AP2 Label numbers of geometry points which define the axis of revolution. The direction of the axis is taken from point AP1 to point AP2. X0 [0.0] Y0 [0.0] Z0 [0.0] Global coordinates of the position vector defining a point on the axis of rotation when MODE = VECTORS. XA [1.0] YA [0.0] ZA [0.0] Components (with respect to the global coordinate system) of the axis of rotation when MODE = VECTORS. PCOINCIDE [YES] Geometry point are to be located at the other end of the volume from the initial surface given by SURFACE. This parameter indicates whether to check the location against existing geometry point coordinates, and use an existing point (YES) rather than generate a new geometry point (with a new label) (NO). {YES/NO}
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VOLUME REVOLVED
Chap. 6 Geometry definition
PTOLERANCE [1.0E-5] If PCOINCIDE = YES, this parameter provides a tolerance value for checking the global coordinates of a location against those of existing geometry points. NDIV [DEFAULT] Number of subdivisions assigned to the surface in the revolved direction. The DEFAULT number of subdivisions is taken from the parameter NDIV in the command SUBDIVIDE DEFAULT. surfacei Label numbers of geometry surfaces. The data line input allows for more than one surface to be revolved. Auxiliary commands LIST VOLUME DELETE VOLUME
FIRST LAST FIRST LAST OPTION
When deleting volume, OPTION = ALL will delete any vertex points, edge lines or face surfaces which have no other dependent geometry; otherwise (OPTION = VOLUME), only the volume itself will be defined.
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VOLUME EXTRUDED
VOLUME EXTRUDED
Sec. 6.5 Volumes
NAME SURFACE OPTION DX DY DZ SYSTEM PCOINCIDE PTOLERANCE NDIV LINE RATIO PROGRESSION CBIAS
surfacei VOLUME EXTRUDED defines one or more geometry volumes by displacing geometry surfaces in a given direction or along a line. Please refer to LINE description below for limitations. ZL
YL XL P1
P2
( DX, DY, DZ )
SURFACE P3
P4
NAME [(current highest geometry volume label number) + 1] Label number of the extruded geometry volume. SURFACE Label number of the initial geometry surface to be displaced, thereby defining the extruded volume. OPTION This parameter defines the type of extrusion. {VECTOR/LINE}
[VECTOR]
VECTOR
volumes are defined by displacing geometry surfaces in a given direction.
LINE
volumes are defined by displacing geometry surfaces along a line.
DX [1.0] DY [0.0] DZ [0.0] Components of displacement vector with respect to the base coordinates (XL, YL, ZL) of coordinate system SYSTEM. Note that this is the actual displacement vector, i.e., it specifies ADINA R & D, Inc.
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VOLUME EXTRUDED
both magnitude and direction. These parameters are only used when OPTION=VECTOR. SYSTEM [currently active coordinate system] Label number of a coordinate system. One of the axes of this coordinate system may be used to define the axis of revolution, via parameter AXIS, when MODE = AXIS. PCOINCIDE [YES] Geometry point are to be located at the other end of the volume from the initial surface given by SURFACE. This parameter indicates whether to check the location against existing geometry point coordinates, and use an existing point (YES) rather than generate a new geometry point (with a new label) (NO). {YES/NO} PTOLERANCE [1.0E-5] If PCOINCIDE = YES, this parameter provides a tolerance value for checking the global coordinates of a location against those of existing geometry points. NDIV [DEFAULT] Number of subdivisions assigned to the surface in the extruded direction. The DEFAULT number of subdivisions is taken from the parameter NDIV in the command SUBDIVIDE DEFAULT. This parameter is only used when OPTION=VECTOR. LINE The geometry line label. Only straight lines, extruded lines or combined lines are allowed. If a combined line is used, the combined line should be either straight or extruded. This parameter is only used when OPTION=LINE. For lines that do not meet these conditions, the command VOLUME SWEEP should be used. RATIO [1.0] Ratio of lengths of the last to first element edges along the extruded vector. The grading of element lengths is governed by parameter PROGRESSION. This parameter is only used when OPTION=VECTOR. PROGRESSION [GEOMETRIC] When element lengths are to be graded, the distribution of element lengths can be selected from the following options. This parameter is only used when OPTION=VECTOR. {ARITHMETIC/GEOMETRIC} ARITHMETIC
The difference in length of each element edge from its adjacent edges is constant.
GEOMETRIC
The ratio of lengths of adjacent element edges is constant.
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VOLUME EXTRUDED
Sec. 6.5 Volumes
CBIAS [NO] Indicates if central bias is used along the extruded vector. This parameter is only used when OPTION=VECTOR. {NO/YES} surfacei Label numbers of geometry surfaces. The data line input allows for more than one surface to be extruded. Auxiliary commands LIST VOLUME DELETE VOLUME
FIRST LAST FIRST LAST OPTION
When deleting volumes, OPTION = ALL will delete any vertex points, edge lines or face surfaces which have no other dependent geometry; otherwise (OPTION = VOLUME), only the volume itself will be defined.
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VOLUME SWEEP
Chap. 6 Geometry definition
VOLUME SWEEP
NAME SURFACE LINE DELETE-LINE ALIGNMENT PCOINCIDE PTOLERANCE NPTS
surfacei Defines one or more geometry volumes by sweeping one or more geometry surfaces along a line. The first newly defined geometry volume is identified by its label number NAME. The other newly defined geometry volumes are identified by the current highest geometry volume label number + 1.
P1
P2
LINE SURFACE
P3
P4
NAME [(current highest geometry volume label number) + 1] Label number of the swept geometry volume. SURFACE Label number of the initial geometry surface to be displaced, thereby defining the swept volume. LINE The geometry line label. Unlike the command VOLUME EXTRUDED, there is no limitation to straight lines, extruded lines or combined lines. DELETE-LINE [YES] Indicates whether or not the lines are to be deleted after applying the command VOLUME SWEEP. ALIGNMENT This parameter specifies the direction of the surface during sweeping. NORMAL
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[NORMAL]
Surface normal is at fixed angle to line tangent.
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VOLUME SWEEP
PARALLEL
Sec. 6.5 Volumes
Surface normal always points to the same direction.
PCOINCIDE [YES] Geometry points are to be located at the other end of the volume from the initial surface given by SURFACE. This parameter indicates whether to check locations against existing geometry point coordinates, and use existing points rather than generate new geometry points (with new labels). PTOLERANCE [Default given by TOLERANCES GEOMETRIC] If PCOINCIDE=YES, then this parameter provides a tolerance value for checking the global coordinates of a location against those of existing geometry points. NPTS The number of intermediate points of non-straight and non-arc lines.
[3]
surfacei Label numbers of geometry surfaces. The data line input allows for more than one surface to be swept. Auxiliary commands LIST VOLUME DELETE VOLUME
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VOLUME TRANSFORMED
VOLUME TRANSFORMED
NAME PARENT TRANSFORMATION PCOINCIDE PTOLERANCE NCOPY
volumei The command VOLUME TRANSFORMED defines a geometry volume to be a geometrical transformation of another existing geometry volume. The transformed geometry volume is identified by its label number NAME. If NCOPY is greater than 1, the other newly defined transformed geometry volumes are identified by the current highest geometry volume label number + 1. NAME [(current highest geometry volume label number) + 1] Label number of the transformed geometry volume to be defined. PARENT The volume which, after transformation, gives the volume being defined. TRANSFORMATION [(current transformation label number)] Label number of a geometrical transformation defined by command TRANSFORMATION. PCOINCIDE [NO] This parameter indicates whether to check the location of the transformed volume vertex points against existing geometry points, and use existing points (YES) rather than generate new geometry points (NO) (with a new label) . {YES/NO} PTOLERANCE [1.0E-5] If PCOINCIDE = YES, this parameter provides a tolerance value for checking the global coordinates of a location against those of existing geometry points. NCOPY [1] Parameter defines number of volumes to be generated by the transformation - transformation is repeated NCOPY times. volumei Label numbers of volume to be transformed. Auxiliary commands LIST VOLUME DELETE VOLUME
FIRST LAST FIRST LAST
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BODY SURFACES
Sec. 6.6 Solid models
BODY SURFACES
NAME
surfacei sensei This command is OBSOLETE and is available only for compatibility with old input files. Defines a solid geometry body, as an oriented collection of geometry surfaces. The set of surfaces must form a complete boundary of a solid with the proper orientation such that the oriented surface normal points out of the body. In this way the surfaces yield a boundary representation of a solid — note that a manifold representation is assumed, thus each surface edge (line) must be connected to exactly two (2) surfaces. A body may be meshed directly via the GBODY command (in which case free-form meshing is necessarily used - there is no intrinsic parametric description of the body to support mapped meshing). NAME [(current highest geometry volume label number) + 1] Label number of the body to be defined. surfacei Label number of a geometry surface. sensei Sense indicator for surfacei: +1
the surface normal points out of the body.
-1
the surface normal points into the body.
[+1]
Auxiliary commands LIST BODY DELETE BODY
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BODY VOLUMES
BODY VOLUMES
NAME
volumei This commnad is OBSOLETE and is available only for compatibility with old input files. Defines a solid geometry body, as a collection of geometry volumes. The internal faces of the body resulting from connected volumes are “cancelled out” yielding a boundary representation of a solid in terms of an oriented set of surface patches. A body may be meshed directly via the GBODY command (in which case free-form meshing is necessarily used - there is no intrinsic parametric description of the body to support mapped meshing). NAME [(current highest geometry volume label number) + 1] Label number of the body to be defined. volumei Label number of a geometry volume. Auxiliary commands LIST BODY DELETE BODY
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FACE-THICKNESS
FACE-THICKNESS
Sec. 6.6 Solid models
BODY
facei thicki FACE-THICKNESS defines solid geometry face thicknesses. BODY Solid geometry body label number.
[currently active solid body]
facei The face label number (for body BODY). thicki The face thickness (constant).
[0.0]
Auxiliary commands LIST FACE-THICKNESS
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FACELINK
Chap. 6 Geometry definition
FACELINK
NAME OPTION BODY1 FACE1 BODY2 FACE2 PCTOLERANCE
FACELINK establishes a link, for meshing purposes, between two faces of distinct solid bodies, or between a face of a solid body and a surface. Once the link is established, the program stores the mesh triangulation of whichever of the two faces/surfaces is meshed first. The meshing of the corresponding linked face/surface utilizes the same triangulation, thereby resulting in congruent triangulations and compatible meshes “across” the linked faces/surfaces. NAME The label number of the face link.
[(highest face link label number) + 1]
OPTION This parameter offers basic options for creating the facelinks:
[TWO]
ONE
Facelinks are created between the faces of a given body and the remaining adjacent faces and surfaces.
TWO
Facelinks are created between two bodies.
ALL
Facelinks are created for all the faces and surfaces in the model.
BODY1 The label number of the solid body of which FACE1 is a bounding face. Note: BODY1 = 0 implies that FACE1 is a surface. FACE1 The label number of the first face/surface of the linked pair. BODY2 The label number of the solid body of which FACE2 is a bounding face. Note: BODY2 = 0 implies that FACE2 is a surface. FACE2 The label number of the second face/surface of the linked pair. PCTOLERANCE Tolerance used to determine whether two faces match. DEFAULT
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[DEFAULT]
value set by parameter COINCIDENCE of command TOLERANCES GEOMETRIC
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FACELINK
Sec. 6.6 Solid models
Note:
BODY1, FACE1, BODY2, FACE2 are used only when OPTION=ONE or TWO.
Note:
BODY1 cannot equal BODY2, i.e., either two distinct bodies are given or one solid body face and a surface are given.
Note:
When a body is modified, the associated face links will be updated. When a body is deleted, the associated face links will be deleted. When a surface is deleted, the associated face link will be deleted
Auxiliary commands LIST FACELINK DELETE FACELINK
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SPLIT-EDGE
SPLIT-EDGE NAME BODY USPLIT SPLIT-EDGE splits an edge of a body into two edges by giving a parameter along the edge. NAME Label number of the geometry edge to be split. BODY Label number of the solid geometry body.
[current body label]
USPLIT [0.5] A parameter value indicating the point along edge NAME at which splitting takes place. The parameter value can range between 0.0 (the starting point of edge NAME) to 1.0 (the end point of edge NAME), but cannot be 0.0 or 1.0, i.e. the splitting point on the edge must create two new edges of non-zero length.
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SPLIT-FACE
Sec. 6.6 Solid models
SPLIT-FACE NAME BODY P1 P2 SPLIT-FACE splits a face of a body into two faces by giving two points on the face. NAME Label number of the geometry face to be split. BODY Label number of the solid geometry body.
[current body label]
P1 Label number of the first geometry point. P2 Label number of the second geometry point.
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BODY-DISCREP
Chap. 6 Geometry definition
BODY-DISCREP
NAME
Creates a “discrete boundary representation” for a given body. The “discrete boundary representation” (“discrete brep” in short) of a body is simply a triangular surface mesh (of the body) that has the advantage of being modifiable by command BODY-DEFEATURE. NAME Body label. Auxiliary commands LIST BODY-DISCREP DELETE BODY-DISCREP
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BODY-DEFEATURE
BODY-DEFEATURE
Sec. 6.6 Solid models
NAME SIZE DOMKEEP DOMREMV PREVIEW OPTION ANGLE SPREAD
After having obtained a “discrete boundary representation” (“discrete brep” in short) of a body with the command BODY-DISCREP, this command enables the modification of the “discrete brep”. The actual (geometric) body is never modified. The meshing is limited to 4/ 10/11-node tetrahedral elements. The main purpose of this command is the removal of “small” features which can be of the “boss” type (protrusion) or the “cut” type (may extend to being a hole). The secondary purpose is the removal of surface triangles (on the “discrete brep”) that have either a “small” length or height. NAME Body label. SIZE Any surface triangle on the “discrete brep” whose shortest length or height is below SIZE should be eliminated from the “discrete brep”. DOMKEEP [0] Domain (see DOMAIN command) of body faces that should not be modified. More exactly, the surface triangles on the “discrete brep” that are classified on a body face in the domain should not be modified. DOMREMV [0] Domain (see DOMAIN command) of body faces that should be removed. More exactly, the surface triangles on the “discrete brep” that are classified on a body face in the domain should be removed. It is recommended to use one domain per feature to remove. PREVIEW Preview flag. {YES/NO}
[NO]
YES
the command flags the surface triangles on the “discrete brep” that are targeted for removal to enable their display. It does not actually remove them.
NO
the command will remove the surface triangles that are targeted for removal.
OPTION [COARSEN] Method by which the body faces defined by DOMREMV are removed. {REMESH1/ REMESH2/COARSEN} REMESH1, REMESH2
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BODY-DEFEATURE
when the frontier of the domain is convex. It has to be used when the feature is a hole (whose frontiers should be convex). With REMESH1, the normals used to remesh the domain come from the (boundary discrete representation) faces inside the domain. With REMESH2, the normals used come from the faces immediately adjacent to the domain. COARSEN
the body faces in the domain defined by DOMREMV are removed using a coarsening algorithm that is incremental. It cannot be used when the feature is a hole.
ANGLE [30.0] This is the angle in degrees used when using the incremental coarsening algorithm. The larger the angle, the more surface triangles can be removed but the more deformed the “discrete brep” will be. When attempting to remove a feature using the COARSEN option, it is recommended to set the ANGLE to 180.0 so that the feature can be completely removed. {0.0 ≤ ANGLE ≤ 180.0} SPREAD [YES] Determines whether the removal of surface triangles in the “discrete brep” extends to other surfaces triangles outside the feature indicated by DOMREMV. {YES/NO} NO
the command only attempts to remove surface triangles that are below SIZE or that make up a feature (as indicated by DOMREMV). Other surface triangles will not be modified.
YES
the command may also modify other surface triangles if necessary.
Notes: If a DOMREMV domain is given, the command will only attempt to remove the surface triangles associated with the domain. The SIZE parameter is then only used to spread (see SPREAD parameter). If no DOMREMV domain is given, the command will attempt to remove all surface triangles whose dimensions (shortest length or height) are below SIZE.
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BODY-CLEANUP
BODY-CLEANUP
NAME SIZE DOMKEEP DOMREMV PREVIEW
The main purpose of this command is the removal of “short” body edges and/or “thin” body faces. The actual (geometric) body is never modified but its AUI representation is. NAME Body label. SIZE Any body edge whose length is below SIZE should be eliminated. Any body face whose boundary is reduced to 2 edges (after the elimination of body edges) and whose width is below SIZE should be eliminated. DOMKEEP [0] Domain (see DOMAIN command) of body edges and/or faces that should not be removed. DOMREMV Domain (see DOMAIN command) of body edges and/or faces that should be removed. PREVIEW Preview flag. {YES/NO}
[0] [NO]
YES
the command flags the body edges and/or faces that are targeted for removal to enable their display. It does not actually remove them.
NO
the command will remove them.
Notes: If a DOMREMV domain is given, the command will only attempt to remove the body edges and/or faces that are given. The SIZE parameter is not used. If no DOMREMV domain is given, the command will attempt to remove body edges and/or faces whose dimensions are below SIZE.
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BODY-RESTORE
BODY-RESTORE
Sec. 6.6 Solid models
BODY
Restores the AUI topological representation of the body corresponding to the state of the body before commands such as BODY-CLEANUP, REM-EDGE or REM-FACE are executed (on that body). BODY Body label.
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BODY-DSCADAP
BODY-DSCADAP
NAME MAXNVARS MAXNVARC MAXDIST ADAPT
Adapts (according to the mesh densities set prior) the surface triangles that make up the geometry of an STL body. The output is stored as a discrete representation (see the BODYDISCREP command) which can be then meshed with the GBODY command. This command should only be used in conjunction with the LOAD-STL command. NAME Label of body. MAXNVARS [30.0 (degrees)] Maximum normal variation used in edge swapping when adapting (improving quality of) the surface mesh. When locally changing the topology of the surface mesh, the normal variations (before and after edge swapping) may not exceed MAXNVARS. Maximum normal variation used in vertex smoothing when adapting (improving quality of) the surface mesh. When moving vertices of the surface mesh, the normal variations (before and after vertex smoothing) may not exceed MAXNVARS. {0.0 ≤ MAXNVARS ≤ 180.0} MAXNVARC [90.0 (degrees)] Maximum normal variation used in edge collapsing when adapting (coarsening) the surface mesh. When locally changing the topology of the surface mesh, the normal variations (before and after edge collapsing) may not exceed MAXNVARC. {0.0 ≤ MAXNVARC ≤ 180.0} MAXDIST [0.0] Maximum (absolute) distance allowed from new edge to "reference" mesh (STL body) when performing edge swaps. This distance threshold is used in conjunction with MAXNVARS during edge swapping. By default, MAXDIST is set to 0.0 and therefore disabled. {MAXDIST ≥ 0.0} ADAPT [YES] If set to NO, no adaptation will take place and the STL surface mesh will be stored directly as a discrete representation bypassing totally the adaptation process.
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LINE-FUNCTION
Chap. 6 Geometry definition
LINE-FUNCTION
NAME TYPE DL1 DL2 DL3 NPOINT (i = 1…NPOINT)
i fvali
LINE-FUNCTION describes the variation of a quantity along a line. It may be used, for instance, to indicate how a load is distributed along some geometry line of the model. Note that the variation is spatial; variation of a quantity in time is described by TIMEFUNCTION. This command can be applied to edges.
DL2
DL3 DL2
DL1
DL1 1
0
u
u 0
TYPE = LINEAR
0.5
1
TYPE = QUADRATIC
TYPE = TABULAR fval
Du = 1/NPOINT
3
i=3
u Du
1
NAME Label number of the line-function. TYPE [LINEAR] Selects the type of data variation, see Figure. This controls the actual parameters used – other parameters are ignored. LINEAR
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A linear variation from value DL1 to DL2.
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LINE-FUNCTION
Sec. 6.7 Spatial functions
QUADRATIC
A quadratic variation from value DL1, through value DL3, to value DL2.
TABULAR
The function values are given at a set of equally spaced points along the line. The function is linearly interpolated input values.
between the DL1 Value at the starting point of the line (u = 0 – see Figure). DL2 Value at the end point of the line (u = 1 – see Figure).
[DL1]
DL3 [DL1] Value at the middle point of the line (u = 0.5 – see Figure). This value should not be input for TYPE = LINEAR. NPOINT [3] The number of input function values, used when TYPE = TABULAR. The values are assigned at equally spaced points along the line, with linear interpolation used to determine values along the line. The first point corresponds to the starting point of the line (u = 0), and the last point to the end point of the line (u = 1). Note that NPOINT must be at least 3 (NPOINT = 2 would be equivalent to selecting TYPE = LINEAR). i Index of the input function point, which can take a value from 1 to NPOINT. fvali Value of the function at index point “i”.
[1.0]
Auxiliary commands LIST LINE-FUNCTION DELETE LINE-FUNCTION
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SURFACE-FUNCTION
Chap. 6 Geometry definition
SURFACE-FUNCTION
NAME TYPE DS1 DS2 DS3 DS4 DS5 DS6 DS7 DS8 DS9 MPOINT NPOINT
row col fvalij SURFACE-FUNCTION describes the variation of a quantity across a surface. It may be used, for instance, to indicate how a load is distributed over some geometry surface of the model. Note that the variation is spatial; variation of a quantity in time is described by TIMEFUNCTION.
DS2
DS2
DS1 (0,1)
DS3
DS4
v
DS5
DS6 DS8 DS9 (0,1) (1,1) DS7 DS4 DS3
DS1 (1,1)
v
(0,0) u
(1,0)
(0,0)
u
(1,0)
TYPE = QUADRATIC
TYPE = LINEAR (0,1) [NPOINT, 1]
(1,1) [NPOINT, MPOINT]
(0,0) [1,1]
v u
(1,0) [1,MPOINT]
TYPE = TABULAR
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SURFACE-FUNCTION
Sec. 6.7 Spatial functions
NAME Label number of the surface-function. TYPE [LINEAR] Selects the type of data variation – see Figure. This controls the actual parameters used. LINEAR
A bilinear variation from surface vertex values DS1, DS2, DS3, DS4.
QUADRATIC
A biquadratic variation from surface vertex values DS1 to DS4, and mid-side/internal surface point values DS5 to DS9.
TABULAR
The function values are given at a grid of regularly spaced points on the surface. The function is bilinearly interpolated between the input values.
DS1 Value at the (u = 1, v = 1) vertex point of the surface, see Figure. DS2 Value at the (u = 0, v = 1) vertex point of the surface, see Figure.
[DS1]
DS3 Value at the (u = 0, v = 0) vertex point of the surface, see Figure.
[DS1]
DS4 Value at the (u = 1, v = 0) vertex point of the surface, see Figure.
[DS1]
DS5 Value at the (u = 0.5, v = 1) mid-side point of the surface, see Figure.
[DS1]
DS6 Value at the (u = 0, v = 0.5) mid-side point of the surface, see Figure.
[DS1]
DS7 Value at the (u = 0.5, v = 0) mid-side point of the surface, see Figure.
[DS1]
DS8 Value at the (u = 1, v = 0.5) mid-side point of the surface, see Figure.
[DS1]
DS9 Value at the (u = 0.5, v = 0.5) internal point of the surface, see Figure.
[DS1]
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SURFACE-FUNCTION
Chap. 6 Geometry definition
MPOINT [3] The number of input points in the u-parametric direction of the surface, used when TYPE = TABULAR. The function values are assigned for a grid of points on the surface, with bilinear interpolation used to determine values on the surface. MPOINT defines the number of “columns” for the input grid. NPOINT [3] The number of input points in the v-parametric direction of the surface, used when TYPE = TABULAR. The function values are assigned for a grid of points on the surface, with bilinear interpolation used to determine values on the surface. NPOINT defines the number of “rows” for the input grid. row Row index of the input function point, which can take a value from 1 to NPOINT. {1 ≤ row ≤ NPOINT} col Column index of the input function point, which can take a value from 1 to MPOINT. {1 ≤ col ≤ MPOINT} fvalij Value of the function at index point (i = row, j = col).
[1.0]
Auxiliary commands LIST SURFACE-FUNCTION DELETE SURFACE-FUNCTION
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VOLUME-FUNCTION
VOLUME-FUNCTION
Sec. 6.7 Spatial functions
NAME TYPE DV1 DV2 DV3 DV4 DV5 DV6 DV7 DV8 ... DV27
VOLUME-FUNCTION describes the variation of a quantity within a volume. It may be used, for instance, to indicate how a load is distributed within some geometry volume of the model. Note that the variation is spatial; variation of a quantity in time is described by TIMEFUNCTION. NAME Label number of the volume-function. TYPE Selects the type of data variation. This controls the actual parameters used.
[LINEAR]
LINEAR
A trilinear variation from volume vertex values DV1 to DV8.
QUADRATIC
A triquadratic variation from volume vertex values DV1 to DV8, and mid-side/internal volume point values DV9 to DV27.
DV1...DV27 [DVi = DV1 (i = 2...27)] Values at the vertex, mid-side, and internal points of the volume, see table below. Auxiliary commands LIST VOLUME-FUNCTION DELETE VOLUME-FUNCTION
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TRANSFORMATION COMBINED
Sec. 6.8 Transformations
TRANSFORMATION COMBINED
NAME
positioni transformi TRANSFORMATION COMBINED defines a general transformation as an ordered sequence of existing transformations defined by command TRANSFORMATION. The associated transformation matrix is calculated by concatenating the matrices of the sequence of transformations. NAME [(current highest transformation label number) + 1] Label number of transformation being defined. positioni Index for the transformation, indicating its position in the order of transformation application. In the concatenation the transformation associated with “positioni” = 1 is applied first, then that for “positioni” = 2, and so on. If a transformation is not defined for a given index then the identity transformation is assumed. The index may also be used to delete a transformation from the concatenating sequence. transformi [0] Label number of an existing transformation defined by command TRANSFORMATION (provided that no recursion is implied). A zero value indicates the identity transformation. Example TRANSFORMATION TRANSLATION TRANSFORMATION ROTATION TRANSFORMATION TRANSLATION
TRANSFORMATION DIRECT defines a general 3-D transformation by directly specifying the transformation matrix. NAME [(current highest transformation label number) + 1] Label number of the transformation. Tij Components of the 3-D transformation matrix:
T11 T12 T T 22 21 T31 T32 0 0
T13 T23 T33 0
T14 T24 T34 1
Auxiliary commands LIST TRANSFORMATION DELETE TRANSFORMATION
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TRANSFORMATION POINTS
Chap. 6 Geometry definition
TRANSFORMATION POINTS
NAME P1 P2 P3 Q1 Q2 Q3
TRANSFORMATION POINTS defines a rigid-body 3-D transformation by the specification of 6 geometry points – 3 “initial” points P1, P2, P3, and 3 “target” points Q1, Q2, Q3. The transformation is such that point P1 is transformed into point Q1, the direction from P1 to P2 is transformed into the direction from Q1 to Q2, and the plane defined by the 3 initial points is transformed into the plane defined by the 3 target points. NAME [(current highest transformation label number) + 1] Label number of the transformation. P1, P2, P3 Label numbers of three non-coincident, non-collinear, initial geometry points. Q1, Q2, Q3 Label numbers of three target points, which must also be non-coincident and non-collinear. Auxiliary commands LIST TRANSFORMATION DELETE TRANSFORMATION
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TRANSFORMATION REFLECTION
TRANSFORMATION REFLECTION
Sec. 6.8 Transformations
NAME MODE SYSTEM PLANE P1 P2 P3
TRANSFORMATION REFLECTION defines a 3-D reflection (mirror) transformation about a plane. NAME [(current highest transformation label number) + 1] Label number of the transformation. MODE [SYSTEM] Selects the method of defining the plane of the transformation. This controls which parameters actually define the transformation, other parameters are ignored. SYSTEM
The reflection is defined to be relative to one of the base coordinate planes of a given local coordinate system. (SYSTEM, PLANE)
POINTS
The reflection plane is defined via three (non-collinear) points. (P1, P2, P3)
SYSTEM [currently active coordinate system] Local coordinate system label number. The reflection is made relative to one of the base coordinate planes of this system. PLANE [XZ] Selects a coordinate plane with respect to the base coordinate directions (XL, YL, ZL) of the coordinate system “SYSTEM”. XY
XL-YL plane of coordinate system SYSTEM.
XZ
XL-ZL plane of coordinate system SYSTEM.
YZ
YL-ZL plane of coordinate system SYSTEM.
P1, P2, P3 Label numbers of geometry points which define the plane of reflection for the trans-formation. The points must be distinct, non-coincident, and non-collinear (in order to define a plane). Auxiliary commands LIST TRANSFORMATION DELETE TRANSFORMATION
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TRANSFORMATION ROTATION
TRANSFORMATION ROTATION
NAME MODE SYSTEM AXIS LINE P1 P2 ANGLE X0 Y0 Z0 XA YA ZA
TRANSFORMATION ROTATION defines a 3-D rotation transformation, about an axis.
AXIS
T ANGLE
NAME [(current highest transformation label number) + 1] Label number of the transformation. MODE [AXIS] Selects the method of defining the axis of rotation. This controls which parameters actually define the rotation – other parameters are ignored. AXIS
The axis of rotation is taken as one of the basic axes (XL, YL, ZL) of the local coordinate system given by SYSTEM. (SYSTEM, AXIS, ANGLE)
LINE
The axis of rotation is aligned with the straight line between the end points of a geometry line. Note that the geometry line is not necessarily straight. (LINE, ANGLE)
POINTS
The axis of rotation is taken to be the straight line between two geometry points. (P1, P2, ANGLE)
VECTORS
The axis of rotation is defined by a position vector (lying on the axis), and a direction vector. (X0, Y0, Z0, XA, YA, ZA, ANGLE)
SYSTEM [currently active coordinate system] Local coordinate system label number. The rotation is relative to one of the base axes of this coordinate system.
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TRANSFORMATION ROTATION
Sec. 6.8 Transformations
AXIS [XL] Selects which of the base axes (XL, YL, ZL) of the local coordinate system given by SYSTEM, is used as the axis of rotation. {XL/YL/ZL} LINE Label number of a geometry line. The axis of rotation is given by the straight line between the starting point and ending point of the geometry line LINE. P1 P2 Label numbers of two geometry points. The axis of rotation is the straight line between geometry points P1 and P2. ANGLE The angle of rotation, measured in degrees.
[0.0]
X0 [0.0] Y0 [0.0] Z0 [0.0] Global components of a position vector indicating a point lying on the axis of rotation. XA YA ZA Global components of a vector indicating the direction of the axis of rotation.
[0.0] [0.0] [0.0]
Auxiliary commands LIST TRANSFORMATION DELETE TRANSFORMATION
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TRANSFORMATION SCALE
Chap. 6 Geometry definition
TRANSFORMATION SCALE
NAME MODE SYSTEM POINT SX SY SZ
TRANSFORMATION SCALE defines a 3-D scaling transformation. NAME [(current highest transformation label number) + 1] Label number of the transformation. MODE Selects the method of defining the transformation. This controls which parameters actually define the transformation, other parameters are ignored. SYSTEM
The scaling transformation is defined by scale factors which are relative to the origin of a given local coordinate system and which scale parallel to its base axes (XL, YL, ZL). (SYSTEM, SX, SY, SZ)
POINT
The scaling transformation is defined with the origin at a given geometry point, and by scale factors which scale parallel to the global Cartesian axes. (POINT, SX, SY, SZ)
SYSTEM [currently active coordinate system] Coordinate system label number. The scaling is relative to this coordinate system. POINT Geometry point label number. The origin of the scaling transformation is taken as this point. SX SY SZ Scaling factors.
[1.0] [1.0] [1.0]
Auxiliary commands LIST TRANSFORMATION DELETE TRANSFORMATION
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TRANSFORMATION TRANSLATION
TRANSFORMATION TRANSLATION
Sec. 6.8 Transformations
NAME MODE SYSTEM DX DY DZ LINE P1 P2
TRANSFORMATION TRANSLATION defines a 3-D translation transformation. NAME [(current highest transformation label number) + 1] Label number of the transformation. MODE [SYSTEM] Selects the method of defining the translation. This controls which parameters actually define the translation, other parameters are ignored. SYSTEM
The translation is defined by increments parallel to the base axes (XL, YL, ZL) of local coordinate system SYSTEM. (SYSTEM, DX, DY, DZ)
LINE
The translation is defined as that which would translate the starting point of a geometry line to the ending point of the same geometry line. (LINE)
POINTS
The translation is defined as that which would translate one geometry point to another. (P1, P2)
SYSTEM [currently active coordinate system] Local coordinate system label number. For MODE = SYSTEM the translation is relative to this coordinate system. DX [0.0] DY [0.0] DZ [0.0] Translations parallel to the base Cartesian system (XL,YL,ZL) associated with local coordinate system SYSTEM. LINE Label number of a geometry line. The translation is that which would translate the starting point of geometry line LINE to its ending point. P1 P2 Label numbers of two geometry points. The translation is that which would translate geometry point P1 to geometry point P2. Auxiliary commands LIST TRANSFORMATION DELETE TRANSFORMATION ADINA R & D, Inc.
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TRANSFORMATION INVERSE
Chap. 6 Geometry definition
TRANSFORMATION INVERSE
NAME TINVERT
Defines a 3-D geometry transformation as the inverse of another transformation. NAME [(current highest transformation label number) + 1] Label number of the transformation to be defined. TINVERT Label number of the transformation to be inverted to give the transformation being defined. Auxiliary commands LIST TRANSFORMATION DELETE TRANSFORMATION
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DOMAIN
Sec. 6.9 Miscellaneous
DOMAIN typei
NAME namei
bodyi
Defines a geometry “domain”, which is a collection of geometry entities. A domain may be referenced, for example, by parameter NCDOMAIN of the mesh generation commands (e.g. GSURFACE) to restrict nodal coincidence checking to within a set of geometry entities thereby facilitating partitioning of the finite element model into topologically distinct but geometrically adjacent regions. NAME [(current highest domain label number) + 1] Label number of the domain to be defined. typei Geometry entity type for entry ‘i’ in the list of geometry entities which comprise the domain. {‘POINT’/‘LINE’/‘SURFACE’/‘VOLUME’/‘EDGE’/‘FACE’/‘BODY’} namei Label number of the geometry entity of type typei bodyi Label number of a solid body, used to identify the entity when typei = EDGE or FACE.
[0]
Auxiliary commands LIST DOMAIN DELETE DOMAIN
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Chap. 6 Geometry definition
MEASURE
MEASURE
GTYPE P1 P2 P3 BODY EDGE LINE N1 N2 N3 SUBSTRUCTURE REUSE RESPONSE PROGRAM FACE
Measures the distance between 2 points or 2 nodes, the length of an edge or a line, or the angle formed by 3 points or 3 nodes. GTYPE [POINTS] Options for measurement. {POINTS/EDGE/LINE/POINT-ANGLE/NODES/NODEANGLE/FACE/BODY} POINTS
Distance between two points.
EDGE
Length of an edge of a body.
LINE
Length of a line.
POINT-ANGLE
Angle between three points.
NODES
Distance between two nodes.
NODE-ANGLE
Angle between three nodes.
FACE
Area of a face of a body
BODY
Volume of a body
P1, P2, P3 Label numbers of existing geometry points. P3 is only used when GTYPE=POINT-ANGLE. BODY Body label number. EDGE Edge label number. LINE Line label number. N1, N2, N3 Label numbers of existing nodes. N1 and N2 are only used when GTYPE=NODES or NODEANGLE. N3 is only used when GTYPE=NODE-ANGLE. SUBSTRUCTURE [current substructure label number] The substructure number of the node in the model. Not applicable to ADINA- T/-F. 6-96
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MEASURE
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REUSE [current reuse label number] The reuse number of the node in the model. Not applicable to ADINA-T/-F. RESPONSE Specifies the response for which the node is evaluated.
[DEFAULT]
PROGRAM [current finite element program] The current finite element program, used only if GTYPE=NODES or NODE-ANGLE. FACE Face label number.
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Chap. 6 Geometry definition
GET-EDGE-FACES
NAME BODY
GET-EDGE-POINTS
NAME BODY
GET-EDGE-FACES
GET-EDGE-FACES lists the body faces connected to a body edge. GET-EDGE-POINTS lists theAUI points bounding a body edge. NAME Edge label. {1, 2, ...} BODY Label of body the edge belongs to. {1, 2, ...}
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GET-FACE-EDGES
GET-FACE-EDGES
Sec. 6.9 Miscellaneous
NAME BODY
Lists the body edges bounding a body face. NAME Face label. {1, 2, ...} BODY Label of body the face belongs to. {1, 2, ...}
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REM-EDGE
REM-EDGE
NAME BODY POINT
Removes a body edge by collapsing one end point onto the other. The remaining point is given as POINT. If POINT is set to 0, the remaining point is chosen by the command. NAME Body edge label. {1, 2, ...} BODY Label of body the edge belongs to. {1, 2, ...} POINT Label of point that will remain. {0, 1, 2, ...}
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REM-FACE
REM-FACE
Sec. 6.9 Miscellaneous
NAME BODY EDGE
Removes a body face (bounded by exactly 2 edges) by collapsing one bounding edge onto the other. The remaining edge is given as EDGE. If EDGE is set to 0, the remaining edge is chosen by the command. NAME Body face label. {1, 2, ...} BODY Label of body the face belongs to. {1, 2, ...} EDGE Label of edge that will remain. {0, 1, 2, ...}
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BODY BLEND
Chap. 6 Geometry definition
BODY BLEND
NAME OPTION R1 R2 EDGE POINT
(OPTION=CONSTANT, LINEAR)
edgei or facei
(OPTION=FACE)
The command BODY BLEND takes an existing solid geometry body and modifies specified edges to have a ‘radius’ blend. Two options allow for a constant or variable ‘radius’ blend. This command is only active when ADINA-M has been licensed.
Specified edge
R1
Specified edge
Specified point
R2
R1
Before blend
After blend
Before blend
Constant blend OPTION=CONSTANT
After blend
Linear blend OPTION=LINEAR
NAME Label number of the body to be blended. An existing body label number must be specified. OPTION This parameter offers basic options for blending the edges.
[CONSTANT]
CONSTANT
Multiple edges are blended by a constant radius.
LINEAR
A single edge of the body is blended by two radii - one at each end (vertex) of the edge.
FACE
Multiple faces are blended by a constant radius.
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BODY BLEND
Sec. 6.10 ADINA - M
R1 The first radius of the blend. R1 must be input with a positive value (no default is assumed). R2 The second radius of the blend. R2 is only used when OPTION=LINEAR,and must be input with a non-negative value (no default is assumed). EDGE Label number of the edge to be blended. This parameter is only used when OPTION=LINEAR, in whch case an existing edge label number ust be specified (no default is assumed). POINT Label number of a point at which the blend radius is R1. This parameter is only used when OPTION=LINEAR, in which case an existing point label number must be specified (no default is assumed). edgei Label numbers of body edges to be blended with (constant) radius R1. This data is only used when OPTION=CONSTANT. facei Label numbers of body faces to be blended with (constatnt) radius R1. This data is only used when OPTION=FACE.
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BODY BLOCK
Chap. 6 Geometry definition
BODY BLOCK
NAME OPTION POSITION ORIENTATION CX1 CX2 CX3 CENTER SYSTEM AX AY AZ BX BY BZ DX1 DX2 DX3 P1 P2
The command BODY BLOCK defines a solid geometry block or “brick” shape. A number of options allow for the position, orientation, and dimensions of the block shape. The block body may be used in conjunction with other body shapes to form more complex geometries using the Boolean operation commands BODY MERGE, BODY SUBTRACT, BODY INTERSECT. A body may be meshed directly via the GBODY command (in which case free-form meshing is necessarily used - there is no intrinsic parametric description of the body to support mapped meshing). This command is only active when ADINA-M has been licensed.
Local coordinate system P2
z y x Center
DX3
P1 DX2 DX1
NAME Label number of the body to be defined.
[(highest body label number) + 1]
OPTION This parameter offers basic options for defining the block:
[CENTERED]
CENTERED
The block is defined by its center, orientation and dimensions.
DIAGONAL
The block is defined by two diagonally opposite geometry points and its orientation.
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BODY BLOCK
Sec. 6.10 ADINA - M
POSITION Specifies how the block center is located. (This parameter is only used when OPTION=CENTERED).
[VECTOR]
VECTOR
The center of the block is specified by a position vector (CX1,CX2,CX3) with components in terms of a given coordinate system (SYSTEM).
POINT
The center of the block is specified by an existing geometry point (CENTERED), possibly a vertex of another body.
ORIENTATION Specifies how the edges of the block are aligned:
[SYSTEM]
SYSTEM
The block is aligned with the base Cartesian axes of a local coordinate system (possibly the global coordinate system).
VECTORS
The X,Y,Z directions of the block edges are input in terms of two non-parallel direction vectors (AX,AY,AZ), (BX,BY,BZ). These vectors are used to form a right-handed system as described below.
CX1 [0.0] CX2 [0.0] CX3 [0.0] The position vector of the center of the block, given in terms of curvilinear components of the local coordinate system specified by SYSTEM. Note that these parameters are only used when POSITION=VECTOR and OPTION=CENTERED. CENTER The center of the block - the label number of an existing geometry point. This parameter is only used when POSITION=POINT and OPTION=CENTERED, in which case an existing geometry point must be specified (no default is assumed). SYSTEM [0] Label number of a local coordinate system which may be used to position the center of the block and/or provide the orientation of the block. The center of the block may be given in terms of the curvilinear coordinates (CX1,CX2,CX3) of this local system, when POSITION=VECTOR and OPTION=CENTERED. The local directions of the block are aligned with the base Cartesian system (XL,YL,ZL) of this system, see command SYSTEM, when ORIENTATION=SYSTEM. This parameter is only used when POSITION=VECTOR (and OPTION=CENTERED), or when ORIENTATION=SYSTEM. Note that the default is chosen as the global Cartesian coordinate system.
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BODY BLOCK
AX [1.0] AY [0.0] AZ [0.0] Global Cartesian components of a direction vector specifying the local x-direction of the block. If OPTION= CENTERED, then the component DX1 will be associated with this direction. Note that this vector need not be of unit length, and is only used if ORIENTATION=VECTOR. BX [0.0] BY [1.0] BZ [0.0] Global Cartesian components of a direction vector, which specifies, in conjunction with vector (AX,AY,AZ), the local x-y plane of the block orientation. The vector product, or “cross” product, of (AX,AY,AZ) with (BX,BY,BZ) gives the local z-direction, and the y-direction is then given by the right hand rule. If OPTION=CENTERED the components DX2, DX3 will be associated with the local y-direction and z-directions respectively. Note that this vector need not be of unit length, and is only used if ORIENTATION=VECTOR. DX1 DX2 DX3 The dimensions of the block, aligned with the local x, y and z-directions of the block, respectively. These lengths are only used if OPTION=CENTERED, in which case they must be input with positive values (no defaults are assumed). P1 P2 Label numbers of two existing geometry points which define the opposite corners of a diagonal of the block. These parameters are only used when OPTION= DIAGONAL, and in that case two distinct and non-coincident points must be specified (no defaults are assumed).
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BODY CHAMFER
Sec. 6.10 ADINA - M
BODY CHAMFER edgei facei
NAME R1 R2 OPTION (OPTION=EDGE)
or facei
(OPTION=FACE)
The command BODY CHAMFER applies chamfers to edges or faces of a solid geometry body. This command is only active when ADINA-M has been licensed.
Specified edge
Range 2 Range 1
Specified face
Before chamfer applied
After chamfer applied
NAME Label number of the body to be chamfered. (No default - an existing body name must be given.) R1 The first range (depth) of the chamfer. R1 must be input with a positive value (no default is assumed). R2 [R1] The second range (depth) of the chamfer. If R2 is input, it cannot be negative. If R2 = 0.0, then it is assumed that R2 = R1.
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OPTION This parameter offers basic options for chamfering the edges or faces: EDGE
Multiple edges are chamfered.
FACE
Multiple faces are chamfered.
BODY CHAMFER
[EDGE]
edgei Label numbers of edges to be chamfered. This parameters is used only when OPTION=EDGE. facei Label numbers of faces to be chamfered with range R1. This data is only used when R2 is not equal to R1. (OPTION=EDGE) facei Label numbers of faces to be chamfered. (OPTION=FACE)
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BODY CONE
Sec. 6.10 ADINA - M
BODY CONE
NAME OPTION POSITION ORIENTATION X1 X2 X3 APEX BASE SYSTEM AXIS AX AY AZ SANGLE RADIUS LENGTH
The command BODY CONE defines a solid geometry cone shape. A number of options allow for the position, orientation, and dimensions of the cone shape. The cone body may be used in conjunction with other body shapes to form more complex geometries using the Boolean operation commands BODY MERGE, BODY SUBTRACT, BODY INTERSECT. A body may be meshed directly via the GBODY command (in which case free-form meshing is necessarily used - there is no intrinsic parametric description of the body to support mapped meshing). This command is only active when ADINA-M has been licensed. Axis Apex
Semi-angle Length
Base center
NAME Label number of the body to be defined.
Radius
[(highest body label number) + 1]
OPTION This parameter offers basic options for defining the cone:
[APEX]
APEX
The cone is defined by its apex, semi-angle, orientation, and length.
BASE
The cone is defined by its base center, orientation, radius and length.
ENDPOINTS
The cone is defined by two end points (APEX, BASE) and its base radius.
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BODY CONE
POSITION [VECTOR] Specifies how the apex or base of the cone is located. (This parameter is only used when OPTION=APEX or BASE.) VECTOR
The apex or base of the cone is specified by a position vector (X1,X2,X3) - with components in terms of a given coordinate system (SYSTEM).
POINT
The apex or base of the cone is specified by an existing geometry point (APEX or BASE), possibly a vertex of another body.
ORIENTATION [SYSTEM] Specifies how the direction of the cone axis is defined. (This parameter is only used when OPTION=APEX or BASE.) SYSTEM
The cone axis is aligned with one of the base Cartesian axes (AXIS) of a local coordinate system (SYSTEM) (possibly the global coordinate system).
VECTOR
The cone axis is defined via a direction vector (AX,AY,AZ) in the global coordinate system.
X1 [0.0] X2 [0.0] X3 [0.0] The position vector of the apex or base of the cone, given in terms of curvilinear components of the local coordinate system specified by SYSTEM. Note that these parameters are only used when POSITION=VECTOR, and OPTION=APEX or BASE. APEX The label number of an existing geometry point indicating the apex of the cone. This parameter is only used when POSITION=POINT and OPTION=APEX, or when OPTION=ENDPOINTS; in either case an existing geometry point must be specified (no default is assumed). BASE The label number of an existing geometry point indicating the base center of the cone. This parameter is only used when POSITION=POINT and OPTION=BASE, or when OPTION=ENDPOINTS; in either case an existing geometry point must be specified (no default is assumed). SYSTEM [0] Label number of a local coordinate system which may be used to position the apex or base of the cone and/or define the cone axis direction. The apex or base of the cone may be given in
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BODY CONE
Sec. 6.10 ADINA - M
terms of the curvilinear coordinates (X1,X2,X3) of this local system, when POSITION=VECTOR. For ORIENTATION=SYSTEM the cone axis direction is aligned with one of the base Cartesian system axes of this system (AXIS), see command SYSTEM . This parameter is only used when OPTION=APEX or BASE, and when POSITION= VECTOR or ORIENTATION=SYSTEM. Note that the default is chosen as the global Cartesian coordinate system. AXIS [XL] Indicates which of the base Cartesian axes of the local coordinate system (SYSTEM) is to be used for the direction of the cone axis. Note that both positive and negative coordinate system axial directions may be requested. This parameter is used only when ORIENTATION=SYSTEM and OPTION=APEX or BASE. {XL/YL/ZL/XL-/YL-/ZL-}
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BODY CYLINDER
Chap. 6 Geometry definition
BODY CYLINDER
NAME OPTION POSITION ORIENTATION CX1 CX2 CX3 CENTER SYSTEM AXIS AX AY AZ RADIUS LENGTH P1 P2 SHEET
The command BODY CYLINDER defines a solid geometry cylinder shape. A number of options allow for the position, orientation, and dimensions of the cylinder shape. The cylinder body may be used in conjunction with other body shapes to form more complex geometries using the Boolean operation commands BODY MERGE, BODY SUBTRACT, BODY INTERSECT. A body may be meshed directly via the GBODY command (in which case free-form meshing is necessarily used - there is no intrinsic parametric description of the body to support mapped meshing). This command is only active when ADINA-M has been licensed.
Radius
P1
Center
P2
Axis
Length
NAME Label number of the body to be defined.
[(highest body label number) + 1]
OPTION This parameter offers basic options for defining the cylinder:
[CENTERED]
CENTERED
The cylinder is defined by its center, orientation and dimensions.
ENDPOINTS
The cylinder is defined by two end points and its radius.
POSITION [VECTOR] Specifies how the center of the cylinder is located. This parameter is only used when OPTION=CENTERED.
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BODY CYLINDER
Sec. 6.10 ADINA - M
VECTOR
The center of the cylinder is specified by a position vector (CX1,CX2,CX3) - with components in terms of a given coordinate system (SYSTEM).
POINT
The center of the cylinder is specified by an existing geometry point (CENTER), possibly a vertex of another body.
ORIENTATION [SYSTEM] Specifies how the direction of the cylinder axis is defined. This parameter is only used when OPTION=CENTERED. SYSTEM
The cylinder axis is aligned with one of the base Cartesian axes (AXIS) of a local coordinate system (SYSTEM) (possibly the global coordinate system).
VECTOR
The cylinder axis is defined via a direction vector (AX,AY,AZ) in the global coordinate system.
CX1 [0.0] CX2 [0.0] CX3 [0.0] The position vector of the center of the cylinder, given in terms of curvilinear components of the local coordinate system specified by SYSTEM. Note that these parameters are only used when POSITION=VECTOR and OPTION=CENTERED. CENTER The label number of an existing geometry point indicating the center of the cylinder . This parameter is only used when POSITION=POINT and OPTION=CENTERED, and in that case an existing geometry point must be specified (no default is assumed). SYSTEM [0] The number of a local coordinate system which may be used to position the center of the cylinder and/or define the cylinder axis direction. The center of the cylinder may be given in terms of the curvilinear coordinates (CX1,CX2,CX3) of this local system, when POSITION=VECTOR. For ORIENTATION= SYSTEM the cylinder axis direction is aligned with one of the base Cartesian system axes of this system (AXIS), see command SYSTEM. This parameter is only used when OPTION=CENTERED and POSITION=VECTOR or ORIENTATION= SYSTEM. Note that the default is chosen as the global Cartesian coordinate system. AXIS [XL] Indicates which of the base Cartesian axes of the local coordinate system (SYSTEM) is to be used for the direction of the cylinder axis. This parameter is used only when ORIENTATION=SYSTEM and OPTION=CENTERED. {XL/YL/ZL} ADINA R & D, Inc.
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BODY CYLINDER
AX [1.0] AY [0.0] AZ [0.0] Global Cartesian components of a direction vector specifying the cylinder axis direction. This vector is only used when ORIENTATION=VECTOR and OPTION=CENTERED. RADIUS The radius of the cylinder, which must be input with a positive value (no default is assumed). LENGTH The axial length of the cylinder. This parameter is used only when OPTION=CENTERED, in which case it must be input with a positive value (no default is assumed). P1 P2 Label numbers of two existing geometry points which implicitly define the location, orientation, and length of the cylinder - the only other required data to complete the cylinder definition is the radius (RADIUS). These parameters are only used when OPTION=ENDPOINTS, in which case they must be distinct and non-coincident (also, no defaults are assumed). SHEET Create cylindrical sheet body instead of solid body. {NO, YES}
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BODY HOLLOW
BODY HOLLOW
Sec. 6.10 ADINA - M
NAME THICKNESS
facei thicknessi The command BODY HOLLOW hollows a solid geometry body with thickness THICKNESS. This command is only active when ADINA-M has been licensed. NAME Label number of the body to be hollowed. An existing body name must be given. THICKNESS The thickness of all the faces except the faces listed in the table input. facei Label numbers of faces. thicknessi Thickness for the given face label number. Note:
if thicknessi = 0.0, then facei is removed.
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BODY INTERSECT
Chap. 6 Geometry definition
BODY INTERSECT
NAME KEEP-TOOL
bodyi The command BODY INTERSECT takes an existing solid body (the “target”) and modifies it by taking the intersection of it with a set of other (overlapping) solid bodies (tools). This definition corresponds to a Boolean “intersection” of several bodies. This command is only active when ADINA-M has been licensed. NAME Label number of the (target) body to be modified. (No default - an existing body name must be given.) KEEP-TOOL [NO] Indicates whether or not the tools are to be kept after applying the command BODY INTERSECT. {NO/YES} bodyi Label numbers of other bodies which are to be intersected with the target body. Note that bodyi cannot be the same as that specified for parameter NAME, and repeated body names are only counted once. Also, each body must overlap some part of each of the other bodies, including the target body - i.e. a solid body must result from the intersection operations - an “empty” body cannot be defined.
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BODY LOFTED
BODY LOFTED
Sec. 6.10 ADINA - M
NAME ENTITY DELETE-ENTITIES
entityi bodyi pointi reversei Creates a sheet body by lofting through a set of lines or edges, a solid body by lofting through a set of surfaces, faces, and sheet bodies. NAME Label number of the body to be defined.
[(highest body label number)+1]
ENTITY The set of entities used in the lofting process. {LINE/EDGE/SURFACE/FACE/SHEET} LINE
To define a sheet body by lofting a set of lines.
EDGE
To define a sheet body by lofting a set of edges.
SURFACE
To define a solid body by lofting two surfaces.
FACE
To define a solid body by lofting two faces.
SHEET
To define a solid body by lofting two sheet bodies.
DELETE-ENTITIES [YES] Indicates whether the entities are to be deleted after applying the command.{YES/NO} Entities are lines, surfaces or sheets if ENTITY=LINE, SURFACE or SHEET respectively. This parameter is only used when ENTITY=LINE, SURFACE, or SHEET. entityi Label of entities used to create the lofted body. Entity type depends on the ENTITY parameter. bodyi Label of parent body of edge or face entity when ENTITY = EDGE or FACE. bodyi is not i used if ENTITY = LINE, SURFACE or SHEET. pointi Point label numbers of the start points on each entity. reversei [NO] Indicates whether or not the orientation of the entities needs to be reversed. {NO/YES} Please note that the normals of the surfaces/faces/sheets must be oriented in the same direction as the loft direction. Parameter reversal can be used to reverse the direction if necessary. ADINA R & D, Inc.
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BODY MERGE
Chap. 6 Geometry definition
BODY MERGE
NAME KEEP-TOOL
bodyi The command BODY MERGE takes an existing solid body (the “target”) and modifies it by joining it together with a set of other solid bodies (tools). This definition corresponds to a Boolean “union” of several bodies. This command is only active when ADINA-M has been licensed. NAME Label number of the (target) body to be modified. (No default - an existing body name must be given.) KEEP-TOOL [NO] Indicates whether or not the tools are to be kept after applying the command BODY MERGE. {NO/YES} bodyi Label numbers of other bodies which are to be merged with the target body. Note that bodyi cannot be the same as that specified for parameter NAME, and repeated body names are only counted once.
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Sec. 6.10 ADINA - M
BODY MID-SURFACE
BODY MID-SURFACE
NAME BODY SEW THICKNESS DELETE-BODY REDUNDANT SEWGAP
The command BODY MID-SURFACE creates sheet bodies from a thin-walled solid body. Each thin wall must have two faces and at least one of the following conditions must be met: 1. Both faces are planar. 2. The two faces are offsets of each other. NAME [(current highest body label number)+1] Body label number to be created. BODY Body label number of the thin-walled body that will be used to create sheet bodies. SEW Indicates whether sheet bodies are to be sewn together.{NO/YES}
[NO]
THICKNESS A sheet body will be created if the thickness of the thin wall is less than THICKNESS. DELETE-BODY [NO] Indicates whether the thin-walled body is to be deleted when sheet bodies are created. {NO/ YES} REDUNDANT Indicates whether the redundant topology is to be removed.{KEEP/REMOVE}
[KEEP]
SEWGAP [0.01] Factor used to determine the sewing gap value. The gap value used to sew the sheet bodies is SEWGAP*(the largest of the maximum coordinate differences in each global coordinate direction considering all the sheet bodies that are being sewn together). This parameter is used only when SEW=YES.
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BODY OPTION
BODY OPTION CHECK This command provides the options for ADINA-M bodies. CHECK Geometry checking for bodies in ADINA-M commands. {YES/NO}
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BODY PARTITION
Sec. 6.10 ADINA - M
BODY PARTITION
NAME EXTEND
facei The command BODY PARTITION takes an existing solid body and partition it with a set of faces of the body, resulting in two or more bodies. This command is only active when ADINA-M has been licensed.
Body 2
Face 1 Body 1
Body 1 before partition
Body 1
Body 1 and 2 after partition by face 1
NAME Label number of the body to be partitioned. (No default - an existing body name must be given.) EXTEND Indicates whether or not the faces are extended. {NO/YES}
[NO]
facei Label numbers of faces used to partition the body. Note that repeated face names will only be counted once. Also, when EXTEND=YES and more than one face is used to partition the body, these extended faces should not intersect.
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BODY PIPE
Chap. 6 Geometry definition
BODY PIPE
NAME OPTION POSITION ORIENTATION CX1 CX2 CX3 CENTER SYSTEM AXIS AX AY AZ RADIUS LENGTH P1 P2 THICKNESS
The command BODY PIPE defines a solid geometry pipe shape. A number of options allow for the position, orientation, and dimensions of the pipe shape. The pipe body may be used in conjunction with other body shapes to form more complex geometries using the Boolean operation commands BODY MERGE, BODY SUBTRACT, BODY INTERSECT. A body can be meshed directly via the GBODY command (in which case free-form meshing is necessarily used - there is no intrinsic parametric description of the body to support mapped meshing). This command is only active when ADINA-M has been licensed. NAME
[(highest body label number)+1] Radius
P1
Center
Length
P2
Axis
Thickness
Label number of the body to be defined. OPTION This parameter offers basic options for defining the pipe:
[CENTERED]
CENTERED
The pipe is defined by its center, orientation and dimensions.
ENDPOINTS
The pipe is defined by two end points and dimensions.
POSITION [VECTOR] Specifies how the center of the pipe is located. This parameter is only used when OPTION=CENTERED. VECTOR
The center of the pipe is specified by a position vector (CX1,CX2,CX3) - with components in terms of a given coordinate system (SYSTEM).
POINT
The center of the pipe is specified by an existing geometry point
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(CENTER), possibly a vertex of another body. ORIENTATION [SYSTEM] Specifies how the direction of the pipe axis is defined. This parameter is only used when OPTION=CENTERED. SYSTEM
The pipe axis is aligned with one of the base Cartesian axes (AXIS) of a local coordinate system (SYSTEM), possibly the global coordinate system.
VECTORS
The pipe axis is defined via a direction vector (AX,AY,AZ) in the global coordinate system.
CX1 [0.0] CX2 [0.0] CX3 [0.0] The position vector of the center of the pipe, given in terms of curvilinear components of the local coordinate system specified by SYSTEM. Note that these parameters are only used when POSITION=VECTOR and OPTION=CENTERED. CENTER The label number of an existing geometry point indicating the center of the pipe . This parameter is only used when POSITION=POINT and OPTION=CENTERED, and in that case an existing geometry point must be specified (no default is assumed). SYSTEM [0] Label number of a local coordinate system which may be used to position the center of the pipe and/or define the pipe axis direction. The center of the pipe can be given in terms of the curvilinear coordinates (CX1,CX2,CX3) of this local system, when POSITION=VECTOR. For ORIENTATION= SYSTEM the pipe axis direction is aligned with one of the base Cartesian system axes of this system (AXIS), see command SYSTEM. This parameter is only used when OPTION=CENTERED and POSITION=VECTOR or ORIENTATION=SYSTEM. Note that the default is chosen as the global Cartesian coordinate system. AXIS [XL] Indicates which of the base Cartesian axes of the local coordinate system (SYSTEM) is to be used for the direction of the pipe axis. This parameter is used only when ORIENTATION=SYSTEM and OPTION=CENTERED. {XL/YL/ZL} AX [1.0] AY [0.0] AZ [0.0] Global Cartesian components of a direction vector specifying the pipe axis direction. This vector is only used when ORIENTATION=VECTOR and OPTION=CENTERED. ADINA R & D, Inc.
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BODY PIPE
RADIUS The outer radius of the pipe, which must be input with a positive value (no default is assumed). LENGTH The axial length of the pipe. This parameter is used only when OPTION=CENTERED, in which case it must be input with a positive value (no default is assumed). P1 P2 Label numbers of two existing geometry points which implicitly define the location, orientation, and length of the pipe - the only other required data to complete the pipe definition is the radius and thickness (RADIUS, THICKNESS). P1 and P2 are only used when OPTION=ENDPOINTS, in which case they must be distinct and non-coincident (also, no defaults are assumed). THICKNESS The thickness of the pipe, which must be input with a positive value less than RADIUS (no default is assumed).
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BODY PRISM
Sec. 6.10 ADINA - M
BODY PRISM
NAME OPTION POSITION ORIENTATION CX1 CX2 CX3 CENTER SYSTEM AXIS POLE AX AY AZ BX BY BZ RADIUS LENGTH P1 P2 P3 NSIDES SHEET
The command BODY PRISM defines a prismatic solid geometry shape, which is a cylinder with a regular polygonal cross-section. A number of options allow for the position, orientation, and dimensions of the prism shape. The prism body may be used in conjunction with other body shapes to form more complex geometries using the Boolean operation commands BODY MERGE, BODY SUBTRACT, BODY INTERSECT. A body may be meshed directly via the GBODY command (in which case free-form meshing is necessarily used - there is no intrinsic parametric description of the body to support mapped meshing). This command is only active when ADINA-M has been licensed. P3 (the pole)
P1
Center
P2 Axis Radius
Length
NAME Label number of the body to be defined.
[(highest body label number) + 1]
OPTION This parameter offers basic options for defining the prism:
[CENTERED]
CENTERED
The prism is defined by its center, orientation, dimensions and number of sides.
POINTS
The prism is defined by two end points, a point giving the pole direction, its radius and number of sides.
POSITION [VECTOR] Specifies how the center of the prism is located. This parameter is only used when OPTION=CENTERED.
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BODY PRISM
VECTOR
The center of the prism is specified by a position vector (CX1,CX2,CX3) - with components in terms of a given coordinate system (SYSTEM).
POINT
The center of the prism is specified by an existing geometry point (CENTER), possibly a vertex of another body.
ORIENTATION [SYSTEM] Specifies how both the axial and pole directions of the prism are defined (the pole direction passes through a vertex of the polygonal cross-section). (This parameter is only used when OPTION=CENTERED. SYSTEM
The prism axis is aligned with one of the base Cartesian axes (AXIS), and the pole with another axis (POLE), of a local coordinate system (SYSTEM), possibly the global coordinate system.
VECTORS
The prism axis and pole directions are defined via direction vectors (AX,AY,AZ), (BX, BY, BZ) in the global coordinate system.
CX1 [0.0] CX2 [0.0] CX3 [0.0] The position vector of the center of the prism, given in terms of curvilinear components of the local coordinate system specified by SYSTEM. Note that these parameters are only used when POSITION=VECTOR and OPTION=CENTERED. CENTER The label number of an existing geometry point indicating the center of the prism . This parameter is only used when POSITION=POINT and OPTION=CENTERED, and in that case an existing geometry point must be specified (no default is assumed). SYSTEM [0] Label number of a local coordinate system which may be used to position the center of the prism and/or define both the axis and pole directions of the prism. The center of the prism can be given in terms of the curvilinear coordinates (CX1,CX2,CX3) of this local system, when POSITION=VECTOR. For ORIENTATION=SYSTEM the prism axis and pole directions are aligned with two of the base Cartesian system axes of this system (AXIS, POLE), see command SYSTEM. This parameter is only used when OPTION=CENTERED and POSITION=VECTOR or ORIENTATION=SYSTEM. Note that the default is chosen as the global Cartesian coordinate system. AXIS [XL] Indicates which of the base Cartesian axes of the local coordinate system (SYSTEM) is to be used for the direction of the prism axis. This parameter is used only when 6-126
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ORIENTATION=SYSTEM and OPTION=CENTERED. {XL/YL/ZL} POLE [YL] Indicates which of the base Cartesian axes of the local coordinate system (SYSTEM) is to be used for the pole direction of the prism. This parameter is used only when ORIENTATION=SYSTEM and OPTION=CENTERED. {XL/YL/ZL} AX [1.0] AY [0.0] AZ [0.0] Global Cartesian components of a direction vector specifying the prism axis direction. Note that this vector need not be of unit length, and is only used when ORIENTATION=VECTOR and OPTION=CENTERED. BX [0.0] BY [1.0] BZ [0.0] Global Cartesian components of a direction vector, which specifies, in conjunction with vector (AX,AY,AZ), the local axis-pole plane of the block orientation. The vector product, or “cross” product, of (AX,AY,AZ) with (BX,BY,BZ) gives the local z-direction, and the pole direction is then given by the right hand rule. Note that this vector need not be of unit length, and is only used when ORIENTATION=VECTOR and OPTION=CENTERED. RADIUS The radius of the prism, i.e. the distance of the points of the polygonal cross-section from the prism axis. This value must be input with a positive value (no default is assumed). LENGTH The axial length of the prism. This parameter is used only when OPTION=CENTERED, in which case it must be input with a positive value (no default is assumed). P1, P2, P3 Label numbers of three non-collinear existing geometry points which implicitly define the location, orientation, and length of the prism - the only other required data to complete the prism definition is the radius (RADIUS). The points P1, P2 are taken to lie at the end points on the axis of the prism, whilst point P3 determines the pole direction of the prism. These parameters are only used when OPTION=POINTS, in which case they must be distinct, non-coincident and non-collinear (also, no defaults are assumed). NSIDES [3] The number of sides of the polygonal cross-section of the prism. NSIDES must be at least 3. SHEET Create cylindrical sheet body instead of solid body. {NO, YES}
[NO]
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BODY PROJECT
BODY PROJECT
NAME FACE DIRECTION VECTOR P1 P2 DX DY DZ DELETE-LINE
linei Projects lines onto a face of the body. NAME Label number of the body to be projected onto. An existing body name must be given. FACE Label number of the face to be projected onto. DIRECTION Specifies the direction of projection. {NORMAL/VECTOR} NORMAL VECTOR
[NORMAL]
Lines project to the face in the direction of the face normal. Lines project to the face along the given vector direction.
VECTOR [VALUES] Specifies how the vector is defined. (This parameter is only used when OPTION=VECTOR.) {COMPONENTS/POINTS} COMPONENTS The vector is defined by DX, DY, and DZ. POINTS The vector is defined by two points (P1 and P2). P1 P2 Label numbers of geometry points to define the projection vector. (These two parameters are only used when VECTOR=POINTS.) DX DY DZ Components of vector to define the projection vector. (These three parameters are only used when VECTOR=COMPONENTS.) DELETE-LINE [YES] Indicates whether or not the lines are to be deleted after projection is done. {YES/NO} linei Label numbers of geometry lines used to project to the face.
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BODY REVOLVED
BODY REVOLVED
Sec. 6.10 ADINA - M
NAME MODE BODY FACE ANGLE SYSTEM AXIS ALINE AP1 AP2 X0 Y0 Z0 XA YA ZA MESH NODES SUBSTRUCTURE 2D-EGROUP 3D-EGROUP NDIV NCOINCIDE NCTOLERANCE DELETE-FACE-ELEMENT
Face 1
Body 1 before revolution
Body 1 after revolution Face 1 is revolved
Creates a revolved body on an existing body by rotating a face of the body about an axis. NAME Label number of the body to be defined.
[(highest body label number) + 1]
MODE [AXIS] Selects the method of defining the axis of revolution used to create the body. This controls which parameters actually define the revolved body — other parameters are ignored. AXIS
The axis of revolution is taken as a given coordinate axis of a coordinate system (FACE, ANGLE, SYSTEM, AXIS).
LINE
The axis of revolution is taken as the straight line between the end points of a given geometry line (which is not necessarily straight, but must be open , i.e., have non-coincident end points) (FACE, ANGLE, ALINE).
POINTS
The axis of revolution is taken as the straight line between two given (noncoincident) geometry points (FACE,ANGLE,AP1,AP2).
VECTORS
The axis of revolution is defined by an position vector and a direction vector (FACE, ANGLE, X0, Y0, Z0, XA, YA, ZA).
BODY Label number of the body to be revolved. FACE Label number of the face to be revolved.
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BODY REVOLVED
Chap. 6 Geometry definition
ANGLE Angle of rotation (in degrees). The sign of the angle is given by the right hand rule — i.e., if you curl your fingers around the axis of revolution, with the thumb pointing along the axis, then a positive angle is in the direction of the curl of the fingers. {-360 ≤ ANGLE ≤ 360} SYSTEM [current active coordinate system] Label number of a coordinate system. One of the axes of this cartesian coordinate system may be used to define the axis of revolution, via parameter AXIS, when MODE=AXIS. AXIS [XL] Selects which of the basic axes (XL,YL,ZL) of the local cartesian coordinate system, given by parameter SYSTEM, is used as the axis of revolution {XL/YL/ZL}. ALINE Label number of a geometry line which defines the axis of revolution. The direction of the axis is taken from the start point of the line to the end point of the line. AP1, AP2 Label numbers of geometry points which define the axis of revolution. The direction of the axis is taken from point AP1 topoint AP2. X0, Y0, Z0 Global coordinates of the position vector defining the axis of rotation when MODE=VECTORS.
[0.0]
XA [1.0] YA, ZA [0.0] Components (with respect to the global coordinate system) of the axis of rotation when MODE=VECTORS. MESH [NO] Indicates whether or not the mesh is generated while a swept body is created. If MESH = YES, 3-D elements can be created if 2-D elements exist on the face. NODES [0] The number of nodes per element of the mesh. {0/8/20/27} For the default 0, the program assigns the number of nodes per element in the resulting 3-D mesh based on the corresponding number of nodes of the 2-D mesh on the face, as follows: 2-D 4 8 9
3-D 8 20 27
SUBSTRUCTURE [current substructure label number] The label number of the substructure (ADINA) in which the elements and nodes are created. 6-130
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2D-EGROUP [largest element group of the revolved face] The element group label of the elements on the revolved face. 3D-EGROUP [current group label number] The element group label of the elements on the revolved body. NDIV Number of elements created along the sweeping direction.
[1]
NCOINCIDE Selects the method of nodal coincidence checking. ALL
[BOUNDARIES]
The global coordinates of all generated nodes are compared against those of existing nodes of the substructure (ADINA) or model (ADINA-T/-F). If there is coincidence to within NCTOLERANCE * (max. difference in global coordinates between all previous nodes of the substructure or model), then no new node is created at that location, i.e., the previous node label number is assumed.
BOUNDARIES Coincidence checking is carried out for the nodes generated at vertices, edges, and faces of the geometry bodies. NO
No nodal coincidence checking is carried out.
NCTOLERANCE Tolerance used to determine nodal coincidence.
[TOLERANCES GEOMETRIC]
DELETE-FACE-ELEMENT Indicates whether elements on the 2-D mesh are deleted.
[ALL]
ALL
Delete elements on 2-D mesh and also the element group if it does not contain any elements.
ELEMENT
Delete elements on 2-D mesh but do not delete the element group.
NO
Do not delete any elements.
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Chap. 6 Geometry definition
BODY SECTION
BODY SECTION
NAME KEEP-SHEET KEEP-IMPRINT OPTION
namei bodyi The command BODY SECTION partitions an existing solid body using a set of sheets (defined using SHEET PLANE) or faces of other bodies, resulting in two or more bodies. This command is only active when ADINA-M has been licensed. NAME Label number of the body to be partitioned. An existing body name must be given. KEEP-SHEET [NO] Indicates whether sheets are to be kept after partitioning. This parameter is used only when OPTION = SHEET. {NO/YES} KEEP-IMPRINT [NO] Indicates whether imprinted edges created by the section operation are to be kept. {NO/ YES} OPTION [SHEET] Specifies whether sheets or faces are used to partition the body. {SHEET/FACE} SHEET
Use sheets to section the body.
FACE
Use faces of bodies to section the body.
namei Label number of a sheet (OPTION=SHEET) or face (OPTION=FACE). Note:
The following remarks apply to faces also. - orientation of two adjacent sheets should be the same. - each sheet (or set of connected sheets) must divide the body into completely separate bodies; - each sheet (or set of connected sheets) cannot have its boundary within the body to be sectioned; - the sheets cannot intersect; - three or more sheets cannot meet at a common edge.
bodyi Label number of a solid body. Used when OPTION=FACE.
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BODY SEW
BODY SEW
Sec. 6.10 ADINA - M
NAME SOLID DELETE-BODY HEAL SEWGAP
bodyi The command BODY SEW sews a set of sheet bodies into a sewn body. NAME Label number of the body to be defined.
[(highest body label number) + 1]
SOLID [YES] Indicates whether a solid body is to be created. If SOLID=NO, the created sewn body is a sheet body.{YES/NO} DELETE-BODY [YES] Indicates whether the sheet bodies are deleted after the sewn body is created.{YES/NO} HEAL [NO] If the resulting sewn body does not have a complete boundary, then any holes are treated as wounds which are healed as specified by HEAL. Only used when SOLID=YES. {NO/CAP/EXTEND} NO
Do not heal wounds. Any holes (gaps) will only be closed if they are smaller than the sewing gap.
CAP
Create a face formed by all edges of the hole to cover up (cap) the hole.
EXTEND
Faces around the hole are extended until they cover the hole.
SEWGAP [0.01] Factor used to determine the sewing gap value. The gap value used to sew the body is SEWGAP * (the largest of the maximum coordinate differences in each global coordinate direction considering all the bodies that are being sewn together). bodyi Label numbers of sheet bodies which are used to create the sewn body.
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BODY SHEET
Chap. 6 Geometry definition
BODY SHEET
NAME LINE DELETE-LINE
linei The command BODY SHEET defines a sheet body by a set of geometry lines. NAME Label number of the body to be defined.
[(highest body label number) + 1]
LINE Label number of geometry line comprising the external loop of the sheet body. DELETE-LINE [YES] Indicates whether or not the lines are to be deleted after applying the command BODY SHEET. {YES/NO} linei Label numbers of geometry lines comprising the internal loops of the sheet body.
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BODY SPHERE
Sec. 6.10 ADINA - M
BODY SPHERE
NAME POSITION DIMENSION CX1 CX2 CX3 SYSTEM CENTER RADIUS POINT
The command BODY SPHERE defines a solid geometry sphere shape. The sphere body may be used in conjunction with other body shapes to form more complex geometries using the Boolean operation commands BODY MERGE, BODY SUBTRACT, BODY INTERSECT. A body may be meshed directly via the GBODY command (in which case free-form meshing is necessarily used - there is no intrinsic parametric description of the body to support mapped meshing). This command is only active when ADINA-M has been licensed.
Radius
NAME Label number of the body to be defined. POSITION Specifies how the sphere center is located:
Center
Point
[(highest body label number) + 1] [VECTOR]
VECTOR
The center of the sphere is specified by a position vector (CX1,CX2,CX3) - with components in terms of a given coordinate system (SYSTEM).
POINT
The center of the sphere is specified by an existing geometry point (CENTER), possibly a vertex of another body.
DIMENSION Specifies the size of the sphere:
[RADIUS]
RADIUS
The radius of the sphere is input via parameter RADIUS.
POINT
An existing geometry point lying on the surface of the sphere is used to determine its radius.
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BODY SPHERE
CX1 [0.0] CX2 [0.0] CX3 [0.0] The position vector of the center of the sphere, given in terms of curvilinear components of the local coordinate system specified by SYSTEM. Note that these parameters are only used when POSITION=VECTOR. SYSTEM [0] Label number of a local coordinate system which may be used to position the center of the sphere, in terms of the curvilinear coordinates (CX1,CX2,CX3) of this local system, when POSITION=VECTOR. This parameter is only used when POSITION=VECTOR. Note that the default is chosen as the global Cartesian coordinate system. CENTER The center of the sphere - the label number of an existing geometry point. This parameter is only used when POSITION=POINT, and in that case an existing geometry point must be specified (no default is assumed). RADIUS The radius of the sphere, used only when DIMENSION=RADIUS, in which case it must be input with a positive value (no default is assumed). POINT Label number of an existing geometry point which implicitly defines the radius of the sphere (the point is assumed to be on the surface of the sphere). This parameter is only used when DIMENSION=POINT, in which case it must be non-coincident with the sphere center (also, no default is assumed).
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BODY SUBTRACT
BODY SUBTRACT
Sec. 6.10 ADINA - M
NAME KEEP-TOOL KEEP-IMPRINT
bodyi The command BODY SUBTRACT takes an existing solid body (the “target”) and modifies it by removing from it a set of other solid bodies (tools). This definition corresponds to a Boolean subtraction of one or more bodies from a given solid body. E.g. to “drill” a hole through a body you could subtract a cylindrical body from it. This command is only active when ADINA-M has been licensed. NAME Label number of the (target) body to be modified. (No default - an existing body name must be given.) KEEP-TOOL [NO] Indicates whether or not the tools are to be kept after applying the command BODY SUBTRACT. {NO/YES} KEEP-IMPRINT [NO] Indicates whether or not the imprinted edges created by the Boolean operation are to be merged with the target body. {NO/YES} bodyi Label numbers of other bodies which are to be subtracted from the target body. Note that bodyi cannot be the same as that specified for parameter NAME, and repeated body names are only counted once.
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BODY SWEEP
Chap. 6 Geometry definition
BODY SWEEP NAME BODY FACE OPTION DX DY DZ SYSTEM LINE DELETE-LINE ALIGNMENT MESH NODES SUBSTRUCTURE 2D-EGROUP 3D-EGROUP NDIV NCOINCIDE NCTOLERANCE DELETE-FACE-ELEMENT TWIST-ANGLE
Line 1 Face 1
Body before sweep
Body after sweep Face 1 is swept along line 1
Creates a swept body on an existing body by sweeping a face of the body in a given direction or along a line. NAME Label number of the body to be defined.
[(highest body label number) + 1]
BODY Label number of the body containing face to be swept. FACE Label number of the face to be swept. OPTION This parameter offers the options of body sweep.
[VECTOR]
VECTOR
swept body is created by sweeping a geometry face in a given direction.
LINE
swept body is created by sweeping a geometry face along a line.
DX [1.0] DY [0.0] DZ [0.0] Components of displacement vector with reference to coordinate system SYSTEM. Note that this is the actual displacement vector, i.e. it specifies both magnitude as well as direction. (This parameter is only used when OPTION=VECTOR) 6-138
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SYSTEM [current active coordinate system] Label number of a coordinate system which is referenced by the displacement vector (DX, DY, DZ). (This parameter is only used when OPTION=VECTOR) LINE The geometry line label. (This parameter is only used when OPTION=LINE) DELETE-LINE [YES] Indicates whether or not the lines are to be deleted after applying the command BODY SWEEP. (This parameter is only used when OPTION=LINE). {YES/NO} ALIGNMENT This parameter specifies the direction of the face during sweeping. NORMAL
Face normal is at fixed angle to line tangent.
PARALLEL
Face normal always points to the same direction.
[NORMAL]
MESH [NO] Indicates whether or not the mesh is generated while a swept body is created. If MESH = YES, 3-D elements can be created if 2-D elements exist on the face. NODES [0] The number of nodes per element of the mesh. {0/8/20/27} For the default 0, the program assigns the number of nodes per element in the resulting 3-D mesh based on the corresponding number of nodes of the 2-D mesh on the face, as follows: 2-D 4 8 9
3-D 8 20 27
SUBSTRUCTURE [current substructure label number] The label number of the substructure (ADINA) in which the elements and nodes are created. 2D-EGROUP [largest element group of the swept face] The element group label of the elements on the swept face. 3D-EGROUP [current group label number] The element group label of the elements on the swept body. NDIV Number of elements created along the sweeping direction.
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BODY SWEEP
Chap. 6 Geometry definition
NCOINCIDE Selects the method of nodal coincidence checking. ALL
[BOUNDARIES]
The global coordinates of all generated nodes are compared against those of existing nodes of the substructure (ADINA) or model (ADINA-T/-F). If there is coincidence to within NCTOLERANCE * (max. difference in global coordinates between all previous nodes of the substructure or model), then no new node is created at that location, i.e., the previous node label number is assumed.
BOUNDARIES Coincidence checking is carried out for the nodes generated at vertices, edges, and faces of the geometry bodies. NO
No nodal coincidence checking is carried out.
NCTOLERANCE Tolerance used to determine nodal coincidence.
[TOLERANCES GEOMETRIC]
DELETE-FACE-ELEMENT Indicates whether elements on the 2-D mesh are deleted.
[ALL]
ALL
Delete elements on 2-D mesh and also the element group if it does not contain any elements.
ELEMENT
Delete elements on 2-D mesh but do not delete the element group.
NO
Do not delete any elements.
TWIST-ANGLE [0.0] Indicates the twisted angle when the swept body is twisted along the swept line. This parameter is only used when OPTION=LINE.
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BODY TORUS
Sec. 6.10 ADINA - M
BODY TORUS NAME POSITION ORIENTATION CX1 CX2 CX3 CENTER SYSTEM AXIS AX AY AZ RMAJOR RMINOR BODY TORUS defines a solid geometry torus shape. The torus body may be used in conjunction with other body shapes to form more complex geometries using the Boolean operation commands BODY MERGE, BODY SUBTRACT, BODY INTERSECT. A body may be meshed directly via the GBODY command (in which case free-form meshing is necessarily used - there is no intrinsic parametric description of the body to support mapped meshing). This command is only active when ADINA-M has been licensed. NAME Label number of the body to be defined.
[(highest body label number) + 1]
Major radius
Top view
Center
Axis
Minor radius
Side view POSITION Specifies how the center of the torus is located:
[VECTOR]
VECTOR
The center of the torus is specified by a position vector (CX1,CX2, CX3) with components in terms of a given coordinate system (SYSTEM).
POINT
The center of the torus is specified by an existing geometry point (CENTER), possibly a vertex of another body.
ORIENTATION Specifies how the direction of the major torus axis is defined: SYSTEM
[SYSTEM]
The torus axis is aligned with one of the base Cartesian axes (AXIS) of a local coordinate system (SYSTEM), possibly the global coordinate system.
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VECTOR
BODY TORUS
The torus axis is defined via a direction vector (AX,AY,AZ) in the global coordinate system.
CX1 [0.0] CX2 [0.0] CX3 [0.0] The position vector of the center of the torus, given in terms of curvilinear components of the local coordinate system specified by SYSTEM. Note that these parameters are only used when POSITION=VECTOR. CENTER The label number of an existing geometry point indicating the center of the torus. This parameter is only used when POSITION=POINT, and in that case an existing geometry point must be specified (no default is assumed). SYSTEM [0] Label number of a local coordinate system which may be used to position the center of the torus and/or define the major torus axis direction. The center of the torus may be given in terms of the curvilinear coordinates (CX1,CX2,CX3) of this local system, when POSITION=VECTOR. For ORIENTATION= SYSTEM the torus axis direction is aligned with one of the base Cartesian system axes of this system (AXIS), see command SYSTEM. This parameter is only used when POSITION=VECTOR or ORIENTATION=SYSTEM. Note that the default is chosen as the global Cartesian coordinate system. AXIS [XL] Indicates which of the base Cartesian axes of the local coordinate system (SYSTEM) is to be used for the direction of the major torus axis. This parameter is used only when ORIENTATION=SYSTEM. {XL/YL/ZL} AX [1.0] AY [0.0] AZ [0.0] Global Cartesian components of a direction vector specifying the major torus axis direction. This vector is only used when ORIENTATION=VECTOR. RMAJOR The major radius of the torus, which must be input with a positive value (no default is assumed). RMINOR The minor radius of the torus, which must be input with a positive value (no default is assumed).
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BODY TORUS
Sec. 6.10 ADINA - M
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BODY TRANSFORMED
Chap. 6 Geometry definition
BODY TRANSFORMED
NAME OPTION PARENT TRANSFORMATION NCOPY
bodyi The command BODY TRANSFORMED defines a solid geometry by copying or moving an existing Parasolid body. The transformed body may be used in conjunction with other body shapes to form more complex geometries using the Boolean operation commands BODY MERGE, BODY SUBTRACT, BODY INTERSECT. A body may be meshed directly via the GBODY command (in which case free-form meshing is necessarily used - there is no intrinsic parametric description of the body to support mapped meshing). The transformed body is identified by its label number NAME. If NCOPY is greater than 1, the other newly defined transformed bodies are identified by the current highest body label number + 1. This command is only active when ADINA-M has been licensed. NAME Label number of the body to be defined.
[(highest body label number) + 1]
OPTION This parameter offers two options for defining the body: COPY
The body is defined by coping an existing body.
MOVE
The body is defined by moving an existing body.
[COPY]
PARENT The label of the body to be copied (used only when OPTION=COPY). This parameter must be entered when copying a body. TRANSFORMATION Label number of a geometrical transformation defined by one of the TRANSFORMATION commands. This parameter must be entered. NCOPY [1] Parameter defines number of bodies to be generated by the transformation - transformation is repeated NCOPY times. bodyi Label numbers of body to be transformed.
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SHEET PLANE
SHEET PLANE
Sec. 6.10 ADINA - M
NAME OPTION POSITION OFFSET X Y Z POINT NX NY NZ P1 P2 P3 SYSTEM
positioni pointi The command SHEET PLANE defines a planar sheet. A number of options allow for the position, orientation and dimensions of the planar sheet. The planar sheet may be used to partition a body into one or more bodies using the command BODY SECTION. This command is only active when ADINA-M has been licensed. NAME The sheet label number.
[(current highest sheet label number)+1]
OPTION Selects the method for the planar sheet definition:
[POLYGON]
POLYGON
Sheet defined by a set of co-planar points.
XPLANE
Sheet defined by normal vector in X direction.
YPLANE
Sheet defined by normal vector in Y direction.
ZPLANE
Sheet defined by normal vector in Z direction.
POINT-NORMAL
Sheet defined by a point and a normal vector.
THREE-POINT
Sheet defined by three points.
POSITION [VECTOR] Selects the method to define origin point (only for OPTION=POINT-NORMAL): VECTOR
Origin is defined by a position vector (X,Y,Z).
POINT
Origin is defined by an existing geometry point (POINT).
OFFSET Defines position of the planar sheet along the normal vector. This parameter is only used when OPTION= XPLANE, YPLANE, or ZPLANE. X [0.0] Y [0.0] Z [0.0] Defines origin of the vector normal to the sheet plane. These parameters are only used when
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Chap. 6 Geometry definition
SHEET PLANE
POSITION=VECTOR and OPTION=POINT-NORMAL. POINT Defines geometry point - origin of the planar sheet. This parameter is only used when POSITION=POINT and OPTION=POINT-NORMAL. NX NY NZ Defines vector normal to the planar sheet. These parameters are only used when OPTION=POINT-NORMAL.
[1.0] [0.0] [0.0]
P1 P2 P3 Label numbers of three existing geometry points which define planar sheet. This parameters are only used when OPTION=THREE-POINT (no defaults are assumed). SYSTEM [0] Label number of a local coordinate system. This parameter is used only when OPTION=XPLANE, YPLANE, ZPLANE, or POINT-NORMAL. Only the Cartesian coordinate system is allowed. positioni Position numbers of geometry points. pointi Label numbers of geometry points. Note:
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AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
VOLUME BODY
VOLUME BODY
Sec. 6.10 ADINA - M
NAME BODY DELETE-BODY DEG-EDGE NPTS LINE-TYPE
Converts a body into a geometry volume. Only body of the following geometries can be converted into volume: tetrahedron, hexahedron, prism and pyramid. If more than one body will be converted into volumes and the bodies are from command LOADSOLID, in order not to create duplicated surfaces between connected volumes, make sure PCOINCIDE=YES in command LOADSOLID. This command is only active when ADINA-M has been licensed. NAME [(current highest geometry volume label number) + 1] Label number of the geometry volume. BODY Label number of solid geometry body to be converted into a geometry volume. If BODY=ALL, all the bodies will be converted into volumes. DELETE-BODY [YES] Indicates whether or not the body are to be deleted after applying the command VOLUME BODY. {YES/NO} DEG-EDGE [0] That parameter is used to degenerate edge of the body and body is a prism shape. Parameter can not be used when BODY= ALL. NPTS The number of intermediate points of non-straight and non-arc edges.
[3]
LINE-TYPE [BIARC-SEGMENT] This parameter specifies the line type when volume is created. {BIARC-SEGMENT / SPLINE} BIARC-SEGMENT
If line type is neither straight nor arc, polyline bi-arc is used when all the control points are co-planar and polyline segmented is used when the control points are not co-planar.
SPLINE
If line type is neither straight nor arc, polyline spline is used.
Auxiliary commands LIST VOLUME FIRST LAST DELETE VOLUME FIRST LAST Note that no geometry volume is deleted which has nodes and/or elements associated with it. ADINA R & D, Inc.
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Chap. 6 Geometry definition
SURFACE FACE
SURFACE FACE
NAME BODY FACE DELETE-BODY DEG-POINT NPTS REVERSE LINE-TYPE
Converts a face of a body into a geometry surface. NAME [(current highest geometry surface label number) + 1] Label number of the geometry surface to be created. BODY Label number of the body that contains the face to be converted. If BODY=ALL, faces of all sheet bodies will be converted into surfaces. FACE Label number of the face to be converted to a surface. If BODY=ALL or the specified body is a sheet body, then FACE=1 by default. Otherwise, a face label number has to be input. DELETE-BODY [YES] Indicates whether the body will be deleted after executing this command. {YES/NO} DEG-POINT [0] If the face is a triangle, this parameter indicates which point will be the degenerate vertex of the created triangular surface. Otherwise, this parameter is ignored. If BODY=ALL is specified, this parameter is also ignored and the degenerate vertex is set by the program. NPTS [3] The number of intermediate points used for interpolating edges that are not straight or not arcs. REVERSE Reverses the orientation of the surface. {YES/NO}
[NO]
LINE-TYPE [BIARC-SEGMENT] This parameter specifies the line type when surface is created. {BIARC-SEGMENT / SPLINE} BIARC-SEGMENT
If line type is neither straight nor arc, polyline bi-arc is used when all the control points are co-planar and polyline segmented is used when the control points are not co-planar.
SPLINE
If line type is neither straight nor arc, polyline spline is used.
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SURFACE FACE
Sec. 6.9 Miscellaneous
Auxiliary commands LIST SURFACE DELETE SURFACE
FIRST LAST FIRST LAST OPTION
When deleting surfaces, OPTION=ALL will delete any vertex points or edge lines which have no other dependent geometry; otherwise (OPTION=SURFACE), only the surface itself will be deleted.
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Chapter 7 Model definition
MATERIAL ANAND
MATERIAL ANAND
Chap. 7
Model definition
NAME E NU DENSITY A1 QDR XSI M N H0 A2 S0 ALPHA
SHAT
Defines an Anand material model. This material model may be used with 2-D (plane strain and axisymmetric) and 3-D solid elements. NAME [ (current highest material label number) + 1] Label number of the material to be defined. E Young’s modulus. {>0.0} NU Poisson’s ratio. {-1.0 < NU < 0.5}
[0.0]
DENSITY Mass density. {≥0.0}
[0.0]
A1 Pre-exponential factor. {>0.0} QDR Activation energy normalized by the universal gas constant. {≥0.0} XSI Stress multiplier. {>0.0} M Strain rate sensitivity of stress. {>0.0} SHAT Coefficient for the saturation value of the deformation resistance. {>0.0, only checked if H0>0} N Strain rate sensitivity of the deformation resistance. {≥0.0} H0 Hardening / softening constant. {≥0.0} A2 Strain rate sensitivity of hardening or softening. {>0.0}
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MATERIAL ANAND
S0 Initial value of deformation resistance. {>0.0} ALPHA [0.0] Mean coefficient of thermal expansion. ALPHA is only considered if thermal loading is modeled.
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MATERIAL ARRUDA-BOYCE
MATERIAL ARRUDA-BOYCE
Sec. 7.1 Material models
NAME MU LAMDA KAPPA DENSITY FITTING-CURVE VISCOELASTIC-CONSTANTS TEMPERATURE-DEPENDENCE TREF RUBBER-TABLE RUBBER-VISCOELASTIC RUBBER-MULLINS RUBBER-ORTHOTROPIC
Defines an Arruda-Boyce material model, which is a hyperelastic material model for rubber materials. This material model may be used with 2-D solid and 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. If the label number of an existing material is given, then the previous material definition is overwritten. MU Initial shear modulus. MU > 0.
[12.6008]
LAMDA Locking stretch. LAMDA > 0.
[1.0]
KAPPA Bulk modulus. KAPPA > 0.
[63000.0]
DENSITY Mass density.
[0]
FITTING-CURVE [0] Fitting-curve label. The fitting curve is used to calculate the parameters MU and LAMDA. If FITTING-CURVE > 0 is specified, any values specified for MU and LAMDA will be ignored. VISCOELASTIC-CONSTANTS [0] Viscoelastic-constants label. This parameter is superseded by the RUBBER-VISCOELASTIC parameter. However, this parameter is still supported for backwards compatibility. TEMPERATURE-DEPENDENCE Specifies the temperature dependence of the material properties. {NO/TRS/FULL}
[NO]
NO
The material properties are not temperature dependent; thermal effects are not included.
TRS
The material properties are not temperature dependent, but the material is assumed to be TRS (thermorheologically simple). Thermal effects are included.
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Chap. 7 Model definition
FULL
MATERIAL ARRUDA-BOYCE
The material properties are temperature dependent. Parameters C1 to KAPPA, and RUBBER-VISCOELASTIC to RUBBER-ORTHOTROPIC of this command are ignored.
The only parameters used when TEMPERATURE-DEPENDENCE = FULL are NAME, TEMPERATURE-DEPENDENCE, TREF and RUBBER-TABLE. TREF [0.0] The material reference temperature, required if TEMPERATURE-DEPENDENCE = TRS or FULL. RUBBER-TABLE The label number of a rubber-table data set. The type of rubber-table depends upon TEMPERATURE-DEPENDENCE, as follows:
[0]
TEMPERATURE-DEPENDENCE = NO : Do not enter a rubber-table. TEMPERATURE-DEPENDENCE = TRS : A rubber-table of type TRS must be entered. This rubber-table is a table of temperatures and corresponding coefficients of thermal expansion. TEMPERATURE-DEPENDENCE = FULL : A rubber-table of type Arruda-Boyce must be entered. This rubber-table is a table of temperatures and corresponding material properties. RUBBER-VISCOELASTIC [0] If RUBBER-VISCOELASTIC is zero, no viscoelastic effects are included. If RUBBER-VISCOELASTIC is non-zero, viscoelastic effects are included, using the data set from the corresponding RUBBER-VISCOELASTIC command. This parameter is not used when TEMPERATURE-DEPENDENCE = FULL. RUBBER-MULLINS [0] If RUBBER-MULLINS is zero, no Mullins effects are included. If RUBBER-MULLINS is nonzero, Mullins effects are included, using the data set from the corresponding RUBBER-MULLINS command. This parameter is not used when TEMPERATURE-DEPENDENCE = FULL. RUBBER-ORTHOTROPIC [0] If RUBBER-ORTHOTROPIC is zero, no orthotropic effects are included. If RUBBERORTHOTROPIC is non-zero, orthotropic effects are included, using the data set from the corresponding RUBBER-ORTHOTROPIC command. This parameter is not used when TEMPERATURE-DEPENDENCE = FULL.
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MATERIAL ARRUDA-BOYCE
Sec. 7.1 Material models
Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL CAM-CLAY
Chap. 7 Model definition
MATERIAL CAM-CLAY
NAME E NU LAMDA KAPPA GAMMA PNULL MIU OCR KNULL DENSITY SINITIAL
Defines a nonlinear Cam-Clay material model This material model may be used with 2-D solid and 3-D solid elements. NAME
[(current highest material label number)+1]
E Initial Young's modulus E. {> 0.0} NU Poisson's Ratio. {-1.0 < NU < 0.5}
[0.0]
LAMDA Isotropic normal consolidation slope. {> 0.0} KAPPA Unloading-reloading slope. {> 0.0} GAMMA Critical state constant [1]. {> 0.0} PNULL Initial size of yield surface. {≥ 0.0}
thetai E0i nui alphai sigmati sigmaci epsci sigmaui epsui sigmatpi xsii gfi Defines a nonlinear concrete material. This material model may be used with 2-D solid and 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. OPTION [KUPFER] Selects triaxial failure curve input method. INPUT requires the specification of 24 values, SP11 to SP363, to represent the failure curves. {KUPFER/SANDIA/INPUT} OPTION = KUPFER corresponds to: BETA = 0.75 SP11 = 0.0 SP14 = 0.75 SP311 = 1.0 SP341 = 2.2 SP312 = 1.3 SP342 = 2.3 SP313 = 1.25 SP343 = 2.25
E0 Tangent modulus at zero strain. NU Poisson’s ratio. SIGMAT Uniaxial cut-off tensile stress. {> 0.0} SIGMATP Post-cracking uniaxial cut-off tensile stress. {> 0.0} If SIGMATP=0, program sets SIGMATP=SIGMAT. SIGMAC Uniaxial maximum compressive stress. {SIGMAC
[0.75 (OPTION = KUPFER, INPUT)] [0.5 (OPTION = SANDIA)] Principal stress ratio used for failure surface input. {0.0 < BETA < 1.0} C1 C2 Critical strain constants.
[1.4] [-0.4]
XSI [8.0] Constant used to define the tensile strain corresponding to zero stress in tensile failure. STIFAC Normal stiffness reduction factor.
[0.0001]
SHEFAC Shear stiffness reduction factor.
[0.5]
ALPHA Mean coefficient of thermal expansion.
[0.0]
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MATERIAL CONCRETE
Sec. 7.1 Material models
TREF [0.0] Reference temperature for thermal expansion calculation. See the Theory and Modeling Guide. INDNU Selects one of the following options for Poisson’s ratio:
[CONSTANT]
CONSTANT
Poisson’s ratio remains constant.
VARIABLE
Poisson’s ratio is allowed to vary (see Theory and Modeling Guide).
GF Fracture energy.
[0.0]
DENSITY Mass density.
[0.0]
SP11 ... SP363 Principal stress ratios used to define compression failure envelope. Only used when OPTION = INPUT. See the Theory and Modeling Guide. TEMPERATURE-DEPENDENT [NO] Indicates whether material is temperature dependent. If YES then material property variation with temperature follows in the command data lines. Note that the maximum allowed number of temperature points is 16. {YES/ NO} thetai Temperature at data point “i”. E0i Tangent modulus at zero strain at temperature “thetai”. nui Poisson’s ratio at temperature “thetai”. alphai Mean coefficient of thermal expansion at temperature “thetai”. sigmati Uniaxial cut-off tensile stress at temperature “thetai”. sigmaci Uniaxial maximum compressive stress at temperature “thetai”.
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MATERIAL CONCRETE
Chap. 7 Model definition
epsci Uniaxial compressive strain for stress sigmaci, at temperature “thetai”. sigmaui Uniaxial ultimate compressive stress at temperature “thetai”. epsui Uniaxial ultimate compressive strain at temperature “thetai”. sigmatpi Post-cracking tensile stress at temperature “thetai”. Note:
The material properties are automatically sorted in order of increasing temperature. If the same temperature is given several times, only the last given values are used.
xsii Constant for the tensile strain failure at temperature “i” gfi Fracture energy at temperature “i” Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL CREEP
MATERIAL CREEP
Sec. 7.1 Material models
NAME CREEP-LAW TEMP-UNIT E NU A0 A1 A2 A3 A4 A5 A6 A7 ALPHA TOLIL DENSITY NRUPT1 NRUPT2 TIME-HARDENING A8 A9 A10 A11 A12 A13 A14 A15
Defines a nonlinear creep material model. This model falls under the category of the more general thermo-elastic-plastic and creep material model, which requires nodal temperature input. (A uniform zero nodal temperature is assumed otherwise). This model also assumes that the effective stress remains below 104×(Young’s modulus) during the analysis. It may be used with truss, 2-D solid, 3-D solid, isobeam, shell and pipe elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. CREEP-LAW Selects type of the creep law. For details, please refer to the Theory and Modeling Guide,Section 3.6.3. {1/2/3/LUBBY2/BLACKBURN}
[1]
TEMP-UNIT [CELSIUS] Creep law 3 may refer to temperatures in degrees Celsius (the centigrade scale) or degrees Kelvin (the absolute scale). {CELSIUS/KELVIN} E Young’s modulus. {> 0.0} NU Poisson’s ratio. {-1.0 < NU < 0.5}
[0.0]
A0 ... A15 [0.0] Creep law constants, ai. A8 ... A15 are applicable only when CREEP-LAW = BLACKBURN. ALPHA Parameter for creep rate equation time integration. The limiting values are: 0.0 Euler forward method (explicit). 1.0 Euler backward method (implicit). Note: ALPHA = 1.0 must be used with large strain analyses.
[1.0]
TOLIL [1.0E-10] Solution tolerance for effective stress calculation. See the Theory and Modeling Guide for further details. DENSITY Mass density.
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MATERIAL CREEP
NRUPT1 [0] NRUPT2 [0] Label numbers of rupture criteria, defined by command RUPTURE. Two rupture criteria can be used simultaneously provided they are not of the same type. A zero value indicates that no rupture criteria are to be used with the material definition. TIME-HARDENING [NO] Indicates whether strain hardening (NO) or time hardening (YES) is used. {YES/NO} Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL CREEP-IRRADIATION
MATERIAL CREEP-IRRADIATION
Sec. 7.1 Material models
NAME IRRADC NF TEMP-UNIT E NU A1 A2 A3 A4 A5 ALPHA TOLIL DENSITY NRUPT1 NRUPT2 TIME-HARDENING TREF
Defines a irradiation creep material model with temperature and neutron fluence dependent properties. This material model may be used with 2-D solid and 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. IRRADC Label number of the irradiation creep table used. The number refers to a definition made by the command IRRADIATION_CREEP-TABLE. NF Label number of the fast neutron dose rate TEMP-UNIT [CELSIUS] Creep law may refer to temperatures in degrees Celsius (the centigrade scale) or degrees Kelvin (the absolute scale) CELSIUS KELVIN
Celsius degrees Kelvin degrees
E Initial Youngs modulus. (E must be > 0.0) NU Poisson’s ratio. (-1.0 < NU < 0.5).
[0.0]
A1 ... A5 Creep law constants. ALPHA Parameter for creep rate equation time integration. The limiting values are: 0.0
Euler forward method (explicit)
1.0
Euler backward method (implicit)
[1.0]
Note: ALPHA = 1.0 must be used with large strain analyses.
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MATERIAL CREEP-IRRADIATION
TOLIL [1.0E-10] Solution tolerance for effective stress calculation. See the Theory and Modeling Guide for further details. DENSITY Mass density.
[0.0]
NRUPT1, NRUPT2 Label numbers of rupture criteria used. The numbers refer to definitions made by the command RUPTURE. Two rupture criteria can be used at the same time provided their types are not the same. TIME-HARDENING
[NO]
NO
The usual strain hardening method will be used in ADINA.
YES
The time hardening method will be used in ADINA.
TREF The reference temperature for thermal expansion coefficient Auxiliary commands LIST MATERIALCREEP-IRRADIATION
FIRST LAST
DELETE MATERIALCREEP-IRRADIATION
FIRST LAST
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MATERIAL CREEP-VARIABLE
MATERIAL CREEP-VARIABLE
Sec. 7.1 Material models
NAME NCOEF TEMP-UNIT E NU ALPHA TOLIL DENSITY NRUPT1 NRUPT2 TIME-HARDENING CREEP-LAW
Defines a nonlinear creep material model with temperature and/or effective-stress dependent coefficients, see command CREEP-COEFFICIENTS . This model falls under the category of the more general thermo-elastic-plastic and creep material model, which requires nodal temperature input. (A uniform zero nodal temperature is assumed otherwise). It may be used with truss, 2-D solid, 3-D solid, isobeam, shell and pipe elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. NCOEF Label number of the creep coefficient dependence function, defined by command CREEP-COEFFICIENTS. TEMP-UNIT [CELSIUS] Indicates the temperature unit for the creep model; degrees Celsius (the centigrade scale) or degrees Kelvin (the absolute scale). {CELSIUS/KELVIN} E Young’s modulus. {> 0.0} NU Poisson’s ratio. {-1.0 < NU < 0.5}
[0.0]
ALPHA Parameter for creep rate equation time integration. The limiting values are:
[1.0]
0.0
Euler forward method (explicit).
1.0
Euler backward method (implicit).
Note:
ALPHA = 1.0 must be used with large strain analyses.
TOLIL [1.0E-10] Solution tolerance for effective stress calculation. See the Theory and Modeling Guide for further details. DENSITY Mass density.
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MATERIAL CREEP-VARIABLE
Chap. 7 Model definition
NRUPT1 [0] NRUPT2 [0] Label numbers of rupture criteria, defined by command RUPTURE. Two rupture criteria can be used simultaneously, provided they are not of the same type. A zero value indicates that no rupture criteria are to be used with the material definition. TIME-HARDENING [NO] Indicates whether strain hardening (NO) or time hardening (YES) is used. {YES/NO} CREEP-LAW Specifies creep law to be used. {NONE/LAW3/LUBBY2} NONE
No creep.
LAW3
ec = S ⋅ T ⋅ e − H
LUBBY2
Lubby2 creep law.
Note:
[LAW3]
If CREEP-LAW=LAW3, the parameter NCOEF reference a creep-coefficient function defined by command CREEP-COEFFICIENTS TEMPERATURE-ONLY or CREEP-COEFFICIENTS MULTILINEAR. If CREEP-LAW=LUBBY2, the parameter NCOEF reference a creep-coefficient function defined by command CREEP-COEFFICIENTS LUBBY2.
Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL CURVE-DESCRIPTION
MATERIAL CURVE-DESCRIPTION
strainvi kloadi kunloadi gloadi
Sec. 7.1 Material models
NAME OPTION GAMMA STIFAC SHEFAC DENSITY (i = 1…6)
Defines a nonlinear geological material, with the option of tension cut-off or cracking. Moduli at 6 volume strain values must be provided. This material model may be used with 2-D plane strain, axisymmetric and 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. OPTION Selects special options.
[NONE]
NONE
No special options.
TENSION-CUT-OFF
Tension cut-off is modeled.
CRACKING
Material cracking is modeled.
GAMMA The material density used to calculate the in-situ gravity pressure.
[0.0]
STIFAC Normal stiffness reduction factor. {< 1.0}
[0.0]
SHEFAC Shear stiffness reduction factor. {< 1.0}
[0.0]
DENSITY Mass density.
[0.0]
strainvi Volume strain at data point “i”. kloadi Loading bulk modulus at strain “strainvi”. kunloadi Unloading bulk modulus at strain “strainvi”. gloadi Loading shear modulus at strain “strainvi”. ADINA R & D, Inc.
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MATERIAL CURVE-DESCRIPTION
Chap. 7 Model definition
Note: strainv1 = 0.0 strainvj > strainv(j-1) kunloadj ≥ kloadj; gloadj < 1.5 × kloadj The unloading shear modulus is calculated as (kunload/kload) × gload Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL DRUCKER-PRAGER
MATERIAL DRUCKER-PRAGER
Sec. 7.1 Material models
NAME E NU ALPHA KYIELD WCAP DCAP TCUT ICPOS RCAP DENSITY BETA POTENTIAL
Defines a nonlinear Drucker-Prager material model with a hardening cap and tension cut-off. This material model may be used with 2-D solid and 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. E Young’s modulus. {> 0.0} NU Poisson’s ratio. {0.0 ≤ NU < 0.5}
[0.0]
ALPHA Yield function parameter α. {≥ 10-5}
[0.0]
KYIELD Yield function parameter, k. {> 0.0} WCAP Cap hardening parameter, W. {< 0.0} DCAP Cap hardening parameter, D. {< 0.0} TCUT Tension cut-off limit. {≥ 0.0}
[0.0]
ICPOS Initial cap position. {≤ 0.0}
[0.0]
RCAP [0.0] Cap ratio. This is the ratio of the major/minor axes of the elliptical cap. RCAP = 0.0 corresponds to a planar cap. {≥ 0.0} DENSITY Mass density.
[0.0]
BETA Potential function parameter β. {≥ 0.0}
[0.0]
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MATERIAL DRUCKER-PRAGER
POTENTIAL Indicates whether to use or ignore the specified BETA. {YES/NO} If NO is specified, then BETA = ALPHA.
[NO]
Auxiliary commands LIST MATERIAL FIRST LAST DELETEMATERIAL FIRST LAST
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MATERIAL DRUCKER-PRAGER
Sec. 7.1 Material models
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MATERIAL ELASTIC
Chap. 7 Model definition
MATERIAL ELASTIC
NAME E NU DENSITY ALPHA
Defines an isotropic linear elastic material. This material model may be used with all elements except fluid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. E Young’s modulus. {> 0.0} NU Poisson’s ratio. {-1.0 < NU < 0.5}
[0.0]
DENSITY Mass density.
[0.0]
ALPHA Coefficient of thermal expansion.
[0.0]
Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL FLUID
MATERIAL FLUID
Sec. 7.1 Material models
NAME K DENSITY GRAVITY X0 Y0 Z0
Defines a linear fluid material. This material model may be used with 2-D and 3-D fluid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. K Bulk modulus. DENSITY Mass density.
[0.0]
GRAVITY The gravity constant used in calculating free surface effects.
[0.0]
Note:
This parameter is used only when MASTER FLUIDPOTENTIAL=YES. specify gravity loads when MASTER FLUIDPOTENTIAL=AUTOMATIC use commands: APPLY-LOAD and LOAD MASSPROPORTIONAL INTERPRETATION=BODY-FORCE.
To
X0 [0.0] Y0 [0.0] Z0 [0.0] X's, Y’s and Z’s datum value for body force potential. See Theory and Modeling Guide. Note:
These parameters are used only when MASTER FLUIDPOTENTIAL=AUTOMATIC and when there are gravity loads entered using command LOAD MASSPROPORTIONAL INTERPRETATION=BODY-FORCE. See the ADINA Theory and Modeling Guide, Equation 2.11-35.
Auxiliary Commands LIST MATERIAL DELETE MATERIAL
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MATERIAL GASKET
Chap. 7 Model definition
MATERIAL GASKET
NAME TREF DENSITY YIELD-CURVE G-G E-G ALPHA-G LEAKAGE-PRESSURE E-INPLANE NU-INPLANE ALPHA-INPLANE NPOINTS
lcurvei Defines a gasket material model. This material model may be used with low-order elements of 2-D solid and 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. If the label number of an existing material is given, then the previous material definition is overwritten. TREF Reference temperature for thermal expansion coefficient.
[0.0]
DENSITY Mass density.
[0.0]
YIELD-CURVE Label of yield (loading) curve. This curve is defined using the LCURVE command.
[1]
G-G Transverse shear modulus. {G-G>=0.0}
[0.0]
E-G Tensile Young's modulus in normal direction.{E-G>=0.0}
[0.0]
ALPHA-G Mean coefficient of thermal expansion in normal direction. {ALPHA-G>=0.0}
ALPHA-INPLANE Inplane mean coefficient of thermal expansion. {ALPHA-INPLANE>=0.0}
[0.0]
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Sec. 7.1 Material models
NPOINTS [2] The point number on the yield curve which corresponds to the initial yield point. All previous points are nonlinear elastic loading/unloading data. lcurvei Label numbers of loading-unloading curves. The curves are defined using the LCURVE command. Note: All loading-unloading curves must have same number of points (=NPOINT) and their first point must have Pressure = 0.0 and their last point must coincide with a yield point.
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Chap. 7 Model definition
MATERIAL GURSON-PLASTIC
MATERIAL GURSON-PLASTIC
NAME E NU YIELD Q1 Q2 Q3 F0 N FN SN EN TOL DENSITY ALPHA TREF FC FF
Command MATERIAL GURSON-PLASTIC defines a Gurson plastic material. This material model may be used with 2-D solid and 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. If the label number of an existing material is given, then the previous material definition is overwritten. E Young=s modulus. {> 0.0} NU Poisson=s ratio. {-1.0 < NU < 0.5}
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
MATERIAL GURSON-PLASTIC
Sec. 7.1 Material models
DENSITY Mass density.
[0.0]
ALPHA [0.0] Mean coefficient of thermal expansion. ALPHA is only considered if thermal loading is modeled. TREF [0.0] The reference temperature for thermal expansion coefficient. See the Theory and Modeling Guide. Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL HYPERELASTIC
Chap. 7 Model definition
MATERIAL HYPERELASTIC
NAME MODEL TENSION-CURVE SHEAR-CURVE EQUIBIAXIAL-CURVE ORDER WEIGHTING CURVE-TYPE ALPHA1 ALPHA2 ALPHA3 ALPHA4 ALPHA5 ALPHA6 ALPHA7 ALPHA8 ALPHA9 KAPPA DENSITY METHOD NSINGULAR MAX-SINGV MIN-SINGV ECHO
This material model will not be supported from ADINA version 8.0 onwards, but is retained for the convenience of users of previous versions. Defines a hyperelastic material model, which is an incompressible nonlinear elastic material model for rubber materials. A least squares curve fitting technique is employed to determine the parameters for a generalized Mooney-Rivlin or an Ogden material model from experimental stress versus strain (or stretch) data. The data can be input for any of three test cases: (i) simple tension, (ii) pure shear, or (iii) equibiaxial tension. A single test or combination of any two, or all three, can be supplied. The accuracy of the model curve thus fitted depends on the number of data points, and the desired approximation order of the model. The total number of data points, from all three test cases, is subject to a minimum (equal to the input order for an Ogden model, and 2, 5, 9 for a generalized Mooney-Rivlin model of input order 1, 2, 3 respectively). See the Theory and Modeling Guide for details. NAME [(current highest material label number) + 1] Label number of the material to be defined. MODEL Specifies which type of material model is to be used.
[OGDEN]
OGDEN
The Ogden constants µi are determined, from the input data curves and αi values.
MOONEY-RIVLIN
The Mooney-Rivlin constants Ci are determined.
TENSION-CURVE [0] Indicates the label number of a (stress, strain) data curve, defined by command SCURVE, which provides data for the simple tension test case. A value of 0 indicates no simple tension data is supplied. The abscissae may be interpreted as strain or stretch as indicated by parameter CURVE-TYPE. SHEAR-CURVE [0] Indicates the label number of a (stress, strain) data curve, defined by command SCURVE,
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MATERIAL HYPERELASTIC
Sec. 7.1 Material models
which provides data for the pure shear test case. A value of 0 indicates no pure shear data is supplied. The abscissae may be interpreted as strain or stretch as indicated by parameter CURVE-TYPE. EQUIBIAXIAL-CURVE [0] Indicates the label number of a (stress, strain) data curve, defined by command SCURVE, which provides data for the equibiaxial tension test case. A value of 0 indicates no equibiaxial tension data is supplied. The abscissae may be interpreted as strain or stretch as indicated by parameter CURVE-TYPE. ORDER Approximation order. Allowed values are: 1 ≤ ORDER ≤ 3
(MODEL = MOONEY-RIVLIN)
1 ≤ ORDER ≤ 9
(MODEL = OGDEN)
Note:
[3]
If MODEL=MOONEY-RIVLIN, then the material constants derivied are as follows: ORDER 1 2 3
Constants C1 ÷ C2 C1 ÷ C5 C1 ÷ C9
WEIGHTING [NO] Specifies whether or not the least squares fitting scheme utilizes weighted data intervals. Their use may provide a better fit for data with very irregular spacing of the strain (or stretch) abscissae. {YES/NO} CURVE-TYPE [STRAIN] Indicates the type of input curve data given by parameters TENSION-CURVE, SHEARCURVE, and EQUIBIAXIAL-CURVE. The option is given for the data abscissae to be either principal (engineering) strain, or principal stretch (= deformed length / undeformed length). The ordinate values in either case are values of nominal stress (= force / unit undeformed area). STRAIN
Input principal engineering strain data.
STRETCH
Input principal stretch data.
ALPHAi Ogden constants αi.
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[i (1
≤ i
≤ 9)]
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Chap. 7 Model definition
KAPPA
MATERIAL HYPERELASTIC
[determined from the initial shear modulus, assuming near incompressibility ( ν=0.499)]
Bulk modulus. DENSITY Mass density.
[0.0]
METHOD [SVD] Specifies the least squares matrix equation solution method. Use of Gaussian elimination may well result in model constants which alternate in sign and have very high magnitude. This is due to the presence of near-singular terms in the least squares system. The “singular value decomposition” method attempts to remove these terms during solution, yielding more reasonable model constants without affecting the overall quality of the least squares fit. The number of near-singular terms to be removed may be controlled by parameters MAX-SINGV, MIN-SINGV. Near-singular terms are removed by default until a monotone increasing solution is obtained for all test cases. SVD
The singular value decomposition method.
GAUSS
Standard Gaussian elimination technique.
NSINGULAR [AUTOMATIC] Indicates whether the number of near-singular terms to be removed in the singular value decomposition solution method is controlled automatically by the program, or is to be specified by you via parameters MAX-SINGV, MIN-SINGV. This parameter is only applicable when METHOD = SVD. AUTOMATIC
The program controls the number of near-singular terms to be removed by the singular value decomposition solution method.
CUSTOM
You indicate the maximum and minimum number of near-singular terms to be removed.
MAX-SINGV
[ORDER (MODEL=OGDEN)] [2 (ORDER=1, MODEL=MOONEY-RIVLIN)] [5 (ORDER=2, MODEL=MOONEY-RIVLIN)] [9 (ORDER=3, MODEL=MOONEY-RIVLIN)] If NSINGULAR = CUSTOM, this parameter indicates the maximum number of near-singular terms which are permitted to be removed during the search for a monotone increasing set of result curves. MAX-SINGV may range from 0 (for which the resulting solution is identical to that obtained by Gaussian elimination) to the total desired number of model constants, as indicated by parameter ORDER. MIN-SINGV [0] If NSINGULAR = CUSTOM, this parameter indicates the minimum number of near-singular
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MATERIAL HYPERELASTIC
Sec. 7.1 Material models
terms which will be removed by the singular value decomposition method, i.e., the SVD algorithm will remove at least MIN-SINGV terms even if a monotone solution set was obtained with fewer terms removed. ECHO Specifies the level of information reported by the command.
[ALL]
NONE
The command behaves silently, except for a completion message.
MODEL
The resulting Ogden / Mooney-Rivlin model constants are reported.
ALL
As well as model constants, curve fitting statistics and comparison tables of input and fitted stress values for the input strain/stretch points is reported.
Note:
It is required that the initial shear modulus be positive, i.e., µi ⋅ α i > 0.0
for an Ogden model.
C1 + C2 > 0.0
for a Mooney-Rivlin model.
or
Note:
KAPPA is used in plane strain, axisymmetric and three-dimensional analyses.
Note:
For a discussion on the singular value decomposition method and its application to the least squares curve fitting algorithm, please consult the Theory and Modeling Guide.
Note:
It is unwise to apply this command to a small set of data within a narrow range of strains (stretches). If possible, some values of strain (stretch) should be input for compression, and it is recommended that the resulting material behavior always be checked graphically with the MATERIALSHOW command.
Note:
The generalized Mooney-Rivlin parameters C1 through C9 may be evaluated by this command; the parameters D1, D2 are, however, set to zero by this command.
Defines a hyper-foam material model, which is a hyperelastic material model for rubber materials. This material model may be used with 2-D solid and 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. If the label number of an existing material is given, then the previous material definition is overwritten. NPOINTS This parameter is not used in this version of the AUI.
[1]
MUi [1.85 (i=1); 9.2 (i=2); 0.0 (i=3,4,5,...,9)] ALPHAi [4.5 (i=1); -4.5 (i=2); 0.0 (i=3,4,5,...,9)] BETAi [9.2 (i=1); 9.2 (i=2); 0.0 (i=3,4,5,...,9)] Non-viscoelastic constants µi, αi, βi (i=1,2,3,...,9). DENSITY Mass density.
[0.0]
FITTING-CURVE [0.0] Fitting-curve label. The fitting curve is used to calculate the parameters MUi, ALPHAi and BETAi. If FITTING-CURVE > 0 is specified, any values specified for MUi, ALPHAi and BETAi will be ignored. ISO-VISCOELASTIC-CONSTANTS [0] Viscoelastic-constants label (isochoric) . This parameter is superseded by the RUBBERVISCOELASTIC parameter. However, this parameter is still supported for backwards compatibility. VOL-VISCOELASTIC-CONSTANTS [0] Viscoelastic-constants label (volumetric) . This parameter is superseded by the RUBBERVISCOELASTIC parameter. However, this parameter is still supported for backwards compatibility.
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Sec. 7.1 Material models
Notes: 1 µi * αi must be greater than zero. 2 βi must be greater than -1/3. TEMPERATURE-DEPENDENCE Specifies the temperature dependence of the material properties. {NO/TRS/FULL}
[NO]
NO
The material properties are not temperature dependent; thermal effects are not included.
TRS
The material properties are not temperature dependent, but the material is assumed to be TRS (thermorheologically simple). Thermal effects are included.
FULL
The material properties are temperature dependent. Parameters C1 to KAPPA, and RUBBER-VISCOELASTIC to RUBBER-ORTHOTROPIC of this command are ignored.
The only parameters used when TEMPERATURE-DEPENDENCE = FULL are NAME, TEMPERATURE-DEPENDENCE, TREF and RUBBER-TABLE. TREF [0.0] The material reference temperature, required if TEMPERATURE-DEPENDENCE = TRS or FULL. RUBBER-TABLE The label number of a rubber-table data set. The type of rubber-table depends upon TEMPERATURE-DEPENDENCE, as follows:
[0]
TEMPERATURE-DEPENDENCE = NO : Do not enter a rubber-table. TEMPERATURE-DEPENDENCE = TRS : A rubber-table of type TRS must be entered. This rubber-table is a table of temperatures and corresponding coefficients of thermal expansion. TEMPERATURE-DEPENDENCE = FULL : A rubber-table of type Hyper-Foam must be entered. This rubber-table is a table of temperatures and corresponding material properties. RUBBER-VISCOELASTIC [0] If RUBBER-VISCOELASTIC is zero, no viscoelastic effects are included. If RUBBER-VISCOELASTIC is non-zero, viscoelastic effects are included, using the data set from the corresponding RUBBER-VISCOELASTIC command. This parameter is not used when
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MATERIAL HYPER-FOAM
Chap. 7 Model definition
TEMPERATURE-DEPENDENCE = FULL. RUBBER-MULLINS [0] If RUBBER-MULLINS is zero, no Mullins effects are included. If RUBBER-MULLINS is nonzero, Mullins effects are included, using the data set from the corresponding RUBBER-MULLINS command. This parameter is not used when TEMPERATURE-DEPENDENCE = FULL. RUBBER-ORTHOTROPIC [0] If RUBBER-ORTHOTROPIC is zero, no orthotropic effects are included. If RUBBERORTHOTROPIC is non-zero, orthotropic effects are included, using the data set from the corresponding RUBBER-ORTHOTROPIC command. This parameter is not used when TEMPERATURE-DEPENDENCE = FULL. Auxiliary commands LIST MATERIAL DELETE MATERIAL
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Sec. 7.1 Material models
MATERIAL ILYUSHIN
MATERIAL ILYUSHIN
NAME E NU YIELD ET GAMMA DENSITY
Defines a nonlinear elastic-plastic material with the Ilyushin yield condition and isotropic hardening. This material model may be used with plate elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. E Young’s modulus. {> 0.0} NU Poisson’s ratio. {-1.0 < NU < 0.5}
[0.0]
YIELD Yield stress in simple tension. ET Strain hardening modulus.
[0.0]
GAMMA Ilyushin factor.
[0.0]
DENSITY Mass density.
[0.0]
Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL MOHR-COULOMB
MATERIAL MOHR-COULOMB
NAME E NU PHI PSI COH TCUT DENSITY DILATATION TEMPEFFECTS ECC ALPHA
Defines a nonlinear Mohr-Coulomb material model that may include temperature effects. This material model may be used with 2-D solid and 3-D solid elements NAME [(current highest material label number) + 1] Label number of the material to be defined. E Young’s modulus. {> 0.0} NU Poisson’s ratio. {0.0 ≤ NU < 0.5}
[0.0]
PHI Friction angle in degrees. {> 0.0} PSI Dilatation angle in degrees. {0.0 ≤ PSI ≤ PHI}
[0.0]
COH Cohesion. {≥ 0.0}
[0.0]
TCUT Tension cut-off limit. {≥ 0.0}
[1.0E10]
DENSITY Mass density.
[0.0]
DILATATION Indicates whether to use or ignore the specified dilatation angle. {YES/NO}
[YES]
TEMPEFFECTS [NO] Indicates whether or not to apply temperature effects. Note that if temperature effects are included, then a different potential function will be used (see the Theory and Modeling Guide for details). {YES/NO} ECC [0.1] Eccentricity parameter at the apex of the Mohr-Coulomb yield surface. Applicable only when temperature effects are included. {0.0 < ECC < 1.0}
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Sec. 7.1 Material models
ALPHA [0.0] Mean coefficient of thermal expansion. Applicable only when temperature effects are included. {≥ 0.0} Auxiliary commands LIST MATERIAL DELETE MATERIAL
Defines a Mooney-Rivlin material model, which is an incompressible nonlinear elastic material model for rubber materials. This material model may be used with 2-D solid and 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. Ci [0.0 (1 ≤ i ≤ 9)] Dj [0.0 (1 ≤ j ≤ 2)] Generalized Mooney-Rivlin constants Ci, Dj. See the Theory and Modeling Guide for details. KAPPA
[determined from the initial shear modulus, assuming near incompressibility ( ν=0.499)]
Bulk modulus. Note:
It is required that the initial shear modulus be positive, i.e., C1 + C2 + D1⋅D2 > 0.0 KAPPA is used in plane strain, axisymmetric and three-dimensional analyses.
DENSITY Mass density.
[0.0]
FITTING-CURVE Fitting-curve label. The fitting curve is used to calculate the parameters Ci and Di. If FITTING-CURVE > 0 is specified, any values specified for Ci and Di will be ignored.
[0]
VISCOELASTIC-CONSTANTS [0] Viscoelastic-constants label. This parameter is superseded by the RUBBER-VISCOELASTIC parameter. However, this parameter is still supported for backwards compatibility. TEMPERATURE-DEPENDENCE Specifies the temperature dependence of the material properties. {NO/TRS/FULL} NO
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[NO]
The material properties are not temperature dependent; thermal effects are not
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
MATERIAL MOONEY-RIVLIN
Sec. 7.1 Material models
included. TRS
The material properties are not temperature dependent, but the material is assumed to be TRS (thermorheologically simple). Thermal effects are included.
FULL
The material properties are temperature dependent. Parameters C1 to KAPPA, and RUBBER-VISCOELASTIC to RUBBER-ORTHOTROPIC of this command are ignored.
The only parameters used when TEMPERATURE-DEPENDENCE = FULL are NAME, TEMPERATURE-DEPENDENCE, TREF and RUBBER-TABLE. TREF [0.0] The material reference temperature, required if TEMPERATURE-DEPENDENCE = TRS or FULL. RUBBER-TABLE The label number of a rubber-table data set. The type of rubber-table depends upon TEMPERATURE-DEPENDENCE, as follows:
[0]
TEMPERATURE-DEPENDENCE = NO : Do not enter a rubber-table. TEMPERATURE-DEPENDENCE = TRS : A rubber-table of type TRS must be entered. This rubber-table is a table of temperatures and corresponding coefficients of thermal expansion. TEMPERATURE-DEPENDENCE = FULL : A rubber-table of type Mooney-Rivlin must be entered. This rubber-table is a table of temperatures and corresponding material properties. RUBBER-VISCOELASTIC [0] If RUBBER-VISCOELASTIC is zero, no viscoelastic effects are included. If RUBBER-VISCOELASTIC is non-zero, viscoelastic effects are included, using the data set from the corresponding RUBBER-VISCOELASTIC command. This parameter is not used when TEMPERATURE-DEPENDENCE = FULL. RUBBER-MULLINS [0] If RUBBER-MULLINS is zero, no Mullins effects are included. If RUBBER-MULLINS is nonzero, Mullins effects are included, using the data set from the corresponding RUBBER-MULLINS command. This parameter is not used when TEMPERATURE-DEPENDENCE = FULL.
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MATERIAL MOONEY-RIVLIN
Chap. 7 Model definition
RUBBER-ORTHOTROPIC [0] If RUBBER-ORTHOTROPIC is zero, no orthotropic effects are included. If RUBBERORTHOTROPIC is non-zero, orthotropic effects are included, using the data set from the corresponding RUBBER-ORTHOTROPIC command. This parameter is not used when TEMPERATURE-DEPENDENCE = FULL. Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL MROZ-BILINEAR
Sec. 7.1 Material models
MATERIAL MROZ-BILINEAR
NAME E NU YIELD BOUND ET ETB EPA DENSITY ALPHA TREF
Defines an elastic-plastic material with the Mroz yield criteria and bilinear hardening. This material model may be used with 2-D solid and 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. E Young’s modulus. {> 0.0} NU Poisson’s ratio. {-1.0 < NU < 0.5}
[0.0]
YIELD Initial yield stress in simple tension. BOUND Bounding stress. ET Strain hardening modulus. ETB Hardening modulus of the bounding surface. EPA [0.0] The maximum allowable effective plastic strain, which enables the modeling of rupture. The stresses are set to zero when the effective plastic strain is greater than the rupture strain EPA. EPA = 0.0 corresponds to no rupture condition. DENSITY Mass density.
[0.0]
ALPHA The mean coefficient of thermal expansion.
[0.0]
TREF [0.0] Reference temperature for calculation of ALPHA. See the Theory and Modeling Guide. Auxiliary commands LIST MATERIAL DELETE MATERIAL ADINA R & D, Inc.
thetai Ei nui alphai dcurvei Defines a nonlinear thermo-elastic-plastic-multilinear and creep material, with von Mises yield condition and isotropic or kinematic strain hardening. This material model may be used with truss, 2-D solid, 3-D solid, isobeam, shell and pipe elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. HARDENING Selects the type of strain hardening used by the material. ISOTROPIC
Linear isotropic strain hardening.
KINEMATIC
Linear kinematic strain hardening.
[ISOTROPIC]
CREEP-LAW [0] Indicates type of the creep law. For details of the creep laws, please refer to Section 3.6.3 of the Theory and Modeling Guide. {0/1/2/3/LUBBY2/BLACKBURN} TEMP-UNIT [CELSIUS] Creep law 3 may refer to temperatures in degrees Celsius (the centigrade scale) or degrees Kelvin (the absolute scale). {CELSIUS/KELVIN} A0 ... A15 [0.0] Creep law constants, ai. A8 ... A15 are applicable only when CREEP-LAW = BLACKBURN. TREF [0.0] The reference temperature for thermal expansion calculation. See the Theory and Modeling Guide. ALPHA [1.0] Time integration parameter {0.0 ≤ ALPHA ≤ 1.0}, used in the integration of the thermoplastic and creep rate equations. The limiting values are:
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MATERIAL MULTILINEAR-PLASTIC-CREEP
0.0
Euler forward method (explicit).
1.0
Euler backward method (implicit).
TOLIL Solution tolerance. See the Theory and Modeling Guide. DENSITY Mass density.
Sec. 7.1 Material models
[1.0E-10] [0.0]
NRUPT1 [0] NRUPT2 [0] Label numbers of rupture criteria, defined by command RUPTURE. Two rupture criteria can be used simultaneously provided that they are not of the same type. A zero value indicates that no rupture criteria are to be used with the material definition. TIME-HARDENING [NO] Indicates whether strain hardening (NO) or time hardening (YES) is used. {YES/NO} thetai Temperature at data point “i”. Ei Young’s Modulus at temperature “thetai”. nui Poisson’s ratio at temperature “thetai”. alphai Mean coefficient of thermal expansion at temperature “thetai”. dcurvei Stress vs. strain curve at temperature “thetai”. This data entry is the label number of a stressstrain curve defined via the SCURVE command. When MASTER CONVERT-SSVAL=NO, stressi and straini are interpreted as true stresses and strains. Stresses and strains entered in the SCURVE command are also intrepreted as true stresses and strains. When MASTER CONVERT-SSVAL=YES, stressi and straini are interpreted as engineering stresses and strains. Stresses and strains entered in the SCURVE command are also intrepreted as engineering stresses and strains.
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Chap. 7 Model definition
Note:
MATERIAL MULTILINEAR-PLASTIC-CREEP
The material properties are automatically sorted in order of increasing temperature. If the same temperature is given several times, only the last given values are used.
Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLE
Sec. 7.1 Material models
MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLE NAME HARDENING NCOEF TEMP-UNIT TREF ALPHA TOLIL DENSITY NRUPT1 NRUPT2 TIME-HARDENING CREEP-LAW thetai Ei nui alphai dcurvei Defines a nonlinear thermo-elastic-plastic-multilinear and creep material, with temperature and/or effective-stress dependent coefficients (see command CREEP-COEFFICIENTS ), von Mises yield condition, and isotropic or kinematic strain hardening. This material model may be used with truss, 2-D solid, 3-D solid, isobeam, shell and pipe elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. HARDENING Selects the type of strain hardening rule: ISOTROPIC
Linear isotropic strain hardening.
KINEMATIC
Linear kinematic strain hardening.
[ISOTROPIC]
NCOEF Label number of the creep coefficient dependence function, defined by command CREEP-COEFFICIENTS. TEMP-UNIT [CELSIUS] Indicates the temperature unit for the creep model; degrees Celsius (the centigrade scale) or degrees Kelvin (the absolute scale). {CELSIUS/KELVIN} TREF [0.0] The reference temperature for thermal expansion calculation. See the Theory and Modeling Guide. ALPHA [1.0] Time integration parameter {0.0 ≤ ALPHA ≤ 1.0}, used in the integration of the thermoplastic and creep rate equations. The limiting values are: 0.0
Euler forward method (explicit).
1.0
Euler backward method (implicit).
Note:
ALPHA = 1.0 must be used with large strain analyses.
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MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLE
TOLIL Solution tolerance. See the Theory and Modeling Guide for further details.
[1.0E-10]
DENSITY Mass density.
[0.0]
NRUPT1 [0] NRUPT2 [0] Label numbers of rupture criteria, as defined by command RUPTURE. Two rupture criteria can be used simultaneously, provided they are not of the same type. A zero value indicates that no rupture criteria are to be used with the material definition. TIME-HARDENING [NO] Indicates whether strain hardening (NO) or time hardening (YES) is used. {YES/NO} CREEP-LAW Specifies creep law to be used. {NONE/LAW3/LUBBY2} NONE
No creep.
LAW3
ec = S ⋅ T ⋅ e − H
LUBBY2
Lubby2 creep law.
Note:
[LAW3]
If CREEP-LAW=LAW3, the parameter NCOEF reference a creep-coefficient function defined by command CREEP-COEFFICIENTS TEMPERATURE-ONLY or CREEP-COEFFICIENTS MULTILINEAR. If CREEP-LAW=LUBBY2, the parameter NCOEF reference a creep-coefficient function defined by command CREEP-COEFFICIENTS LUBBY2.
thetai Temperature at data point “i”. Ei Young’s Modulus at temperature “thetai”. nui Poisson’s ratio at temperature “thetai”. alphai Mean coefficient of thermal expansion at temperature “thetai”.
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MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLE
Sec. 7.1 Material models
dcurvei Stress v strain curve at temperature “thetai”. This data entry is the label number of a stressstrain curve defined via SCURVE. When MASTER CONVERT-SSVAL=NO, stressi and straini are interpreted as true stresses and strains. Stresses and strains entered in the SCURVE command are also intrepreted as true stresses and strains. When MASTER CONVERT-SSVAL=YES, stressi and straini are interpreted as engineering stresses and strains. Stresses and strains entered in the SCURVE command are also intrepreted as engineering stresses and strains. Note:
The material properties are automatically sorted in order of increasing temperature. If the same temperature is given several times, only the last given values are used.
Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL NONLINEAR-ELASTIC
Chap. 7 Model definition
MATERIAL NONLINEAR-ELASTIC
NAME DENSITY DCURVE NU MATRIX
straini stressi Defines a nonlinear elastic material. The model is uniaxial and the stress-strain curve is defined as piecewise linear through the data points (straini, stressi) which can be entered as data lines following the command or can be referenced via the DCURVE parameter (see SCURVE ). For a given strain, the total stress and tangent modulus are interpolated from the input curve. This material model may be used with truss elements, 2-D solid and 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. DENSITY Mass density.
[0.0]
DCURVE [0] Label number of a stress-strain curve defined by command SCURVE. This defines the stressstrain data points associated with this material model. If DCURVE is input as 0, then the data lines following the command define the stress-strain data points. Conversely, if DCURVE is greater than zero then no data lines are expected. NU Poisson's ratio. Not applicable to truss element. {-1.0 < NU < 0.5}
[0.0]
MATRIX [TANGENT] This flag indicates whether the tangent or secant stress-strain matrix is used when the stressstrain curve enters into a softening region. Not applicable to truss element.{TANGENT/ SECANT} TANGENT SECANT
Use tangent stress-strain matrix Use secant stress-strain matrix
straini Strain at data point “i”. stress i Stress at strain “straini”. Auxiliary commands LIST MATERIAL DELETE MATERIAL 7-50
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Defines an Ogden material model, which is an incompressible nonlinear elastic material model for rubber materials. This material model may be used with 2-D solid and 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. MUi [0.0 (1 ≤ i ≤ 9)] ALPHAi [0.0 (1 ≤ i ≤ 9)] Ogden constants µi, αi. See the Theory and Modeling Guide for details. Note that if ALPHAi = 0.0 and curve fitting is used (i.e., FITTING-CURVE > 0), ALPHAi = i will be assigned. KAPPA
[determined from the initial shear modulus, assuming near incompressibility ( ν=0.499)]
Bulk modulus. DENSITY Mass density. Note:
[0.0]
It is required that the initial shear modulus be positive, i.e., µi .νi > 0.0 . KAPPA is used in plane strain, axisymmetric and three-dimensional analyses.
FITTING-CURVE [0] Fitting-curve label. The fitting curve is used to calculate the parameters MUi and ALPHAi. If FITTING-CURVE > 0 is specified, any values specified for MUi and ALPHAi will be ignored. VISCOELASTIC-CONSTANTS [0] Viscoelastic-constants label. This parameter is superseded by the RUBBER-VISCOELASTIC parameter. However, this parameter is still supported for backwards compatibility. TEMPERATURE-DEPENDENCE Specifies the temperature dependence of the material properties. {NO/TRS/FULL}
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[NO]
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
MATERIAL OGDEN
Sec. 7.1 Material models
NO
The material properties are not temperature dependent; thermal effects are not included.
TRS
The material properties are not temperature dependent, but the material is assumed to be TRS (thermorheologically simple). Thermal effects are included.
FULL
The material properties are temperature dependent. Parameters C1 to KAPPA, and RUBBER-VISCOELASTIC to RUBBER-ORTHOTROPIC of this command are ignored.
The only parameters used when TEMPERATURE-DEPENDENCE = FULL are NAME, TEMPERATURE-DEPENDENCE, TREF and RUBBER-TABLE. TREF [0.0] The material reference temperature, required if TEMPERATURE-DEPENDENCE = TRS or FULL. RUBBER-TABLE The label number of a rubber-table data set. The type of rubber-table depends upon TEMPERATURE-DEPENDENCE, as follows:
[0]
TEMPERATURE-DEPENDENCE = NO : Do not enter a rubber-table. TEMPERATURE-DEPENDENCE = TRS : A rubber-table of type TRS must be entered. This rubber-table is a table of temperatures and corresponding coefficients of thermal expansion. TEMPERATURE-DEPENDENCE = FULL : A rubber-table of type Ogden must be entered. This rubber-table is a table of temperatures and corresponding material properties. RUBBER-VISCOELASTIC [0] If RUBBER-VISCOELASTIC is zero, no viscoelastic effects are included. If RUBBER-VISCOELASTIC is non-zero, viscoelastic effects are included, using the data set from the corresponding RUBBER-VISCOELASTIC command. This parameter is not used when TEMPERATURE-DEPENDENCE = FULL. RUBBER-MULLINS [0] If RUBBER-MULLINS is zero, no Mullins effects are included. If RUBBER-MULLINS is nonzero, Mullins effects are included, using the data set from the corresponding RUBBER-MULLINS command. This parameter is not used when TEMPERATURE-DEPENDENCE = FULL.
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MATERIAL OGDEN
Chap. 7 Model definition
RUBBER-ORTHOTROPIC [0] If RUBBER-ORTHOTROPIC is zero, no orthotropic effects are included. If RUBBERORTHOTROPIC is non-zero, orthotropic effects are included, using the data set from the corresponding RUBBER-ORTHOTROPIC command. This parameter is not used when TEMPERATURE-DEPENDENCE = FULL. Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL ORTHOTROPIC
MATERIAL ORTHOTROPIC
Sec. 7.1 Material models
NAME EA EB EC NUAB NUAC NUBC GAB GAC GBC DENSITY WRINKLE W-TIME ALPHA1 ALPHA2 ALPHA3
Defines an orthotropic linear elastic material. This material model may be used with 2-D solid, 3-D solid, shell and plate elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. EA a-direction modulus. {> 0.0} EB b-direction modulus. {> 0.0} EC [0.0] c-direction modulus. EC=0 is admissible only for PLATE elements ( EGROUP PLATE ). {≥ 0.0} NUAB a-b strain ratio.
[0.0]
NUAC a-c strain ratio.
[0.0]
NUBC b-c strain ratio.
[0.0]
GAB a-b shear modulus. {> 0.0} GAC a-c shear modulus. GAC=0 is admissible only for PLATE and 2D solid elements ( EGROUP PLATE and EGROUP TWODSOLID ). {≥ 0.0}
[0.0]
GBC b-c shear modulus. GBC=0 is admissible only for PLATE and 2D solid elements ( EGROUP PLATE and EGROUP TWODSOLID ). {≥ 0.0}
[0.0]
DENSITY Mass density.
[0.0]
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Chap. 7 Model definition
MATERIAL ORTHOTROPIC
WRINKLE Indicates whether wrinkling is to be modeled (e.g., for fabrics). {YES/NO} Note:
[NO]
Modeling of wrinkling is only allowed for TWODSOLID plane stress elements.
W-TIME Wrinkling time, i.e., the time at which wrinkling of the material is activated.
[0.0]
ALPHA1 The coefficient. of thermal expansion for the a direction.
[0.0]
ALPHA2 The coefficient. of thermal expansion for the b direction.
[0.0]
ALPHA3 The coefficient. of thermal expansion for the c direction.
[0.0]
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MATERIAL PLASTIC-BILINEAR
Sec. 7.1 Material models
MATERIAL PLASTIC-BILINEAR NAME HARDENING E NU YIELD ET EPA STRAINRATEFUNCTION DENSITY ALPHA TREF DEPENDENCY TRANSITION-STRAINRATE EP-STRAINRATE BCURVE BVALUE XM-INF XM0 ETA STRAINRATE-FIT Defines a bilinear elastic-plastic material model with von Mises yield condition. This material model may be used with truss, 2-D solid, 3-D solid, beam, iso-beam, shell and pipe elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. HARDENING [ISOTROPIC] Selects the type of strain hardening used by the material. {ISOTROPIC/KINEMATIC/ MIXED} Linear isotropic strain hardening. Linear kinematic strain hardening. Mixed hardening. See Theory and Modeling Guide, Section 3.4.1
ISOTROPIC KINEMATIC MIXED E Young’s modulus.
{> 0.0}
NU Poisson’s ratio. {-1.0 < NU < 0.5}
[0.0]
YIELD Initial yield stress in simple tension. ET Strain hardening modulus.
[0.0]
EPA [0.0] Maximum allowable effective plastic strain. This allows for the modeling of material rupture, whereby the stresses are set to zero whenever the effective plastic strain is greater than the rupture strain EPA. If EPA is input as 0.0, the rupture condition is not used. EPA is not applicable to beam elements. STRAINRATEFUNCTION The parameter is currently not used. Replaced by STRAINRATE-FIT. DENSITY Mass density.
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[0] [0.0]
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Chap. 7 Model definition
MATERIAL PLASTIC-BILINEAR
ALPHA [0.0] Mean coefficient of thermal expansion. ALPHA is only considered if thermal loading is modeled. TREF [0.0] Reference temperature for calculations of ALPHA. See the Theory and Modeling Guide. Note:
The parameters ALPHA, TREF are not applicable to TRUSS elements.
EP-STRAINRATE [0.0] Non-zero strainrate, used only if STRAINRATE-FIT = 0 and BCURVE > 0. This parameter is obsolete, but kept for backwards compatibility. BCURVE Label number of a stress-strain curve defined by command SCURVE. This parameter is obsolete, but kept for backwards compatibility.
[0]
BVALUE Strain rate hardening parameter.
[0.0]
XM-INF Hardening parameter M∞ , used only for mixed hardening.{0 ≤ XM-INF ≤ 1}
[0.0]
XM0 Hardening parameter M0 , used only for mixed hardening.{0 ≤ XM0 ≤ 1}
[0.0]
ETA Hardening parameter η , used only for mixed hardening. {ETA ≥ 0} If ETA >0, then 0< XM-INF < 1 and 0< XM0 <1.
[0.0]
STRAINRATE-FIT [0] The label number of a strainrate-fit describing the strain rate dependence of the yield stress. The function must have been defined using the STRAINRATE-FIT command. A zero value indicates no strain rate dependence. Notes on the STRAINRATE-FIT, TRANSITION-STRAINRATE, EP-STRAINRATE, BCURVE and BVALUE parameters:
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MATERIAL PLASTIC-BILINEAR
Sec. 7.1 Material models
These parameters are used only if DEPENDENCY=YES. 1) STRAINRATE-FIT = 0 and BCURVE = 0. The strainrate material parameters are TRANSITION-STRAINRATE and BVALUE. No curve-fitting is performed. 2) STRAINRATE-FIT = 0 and BCURVE > 0. The AUI uses the stress-strain curve entered in BCURVE, and the associated strainrate EP-STRAINRATE, to determine the overstress ratio at strainrate EP-STRAINRATE. Then the AUI uses the input material parameter TRANSITION-STRAINRATE and the overstress ratio in a curve-fitting procedure to determine material parameter BVALUE. Note that the BCURVE>0 option is obsolete and kept only for backwards compatibility. 3) STRAINRATE-FIT > 0. There are two possibilities, depending upon how many strainrates are entered in the strainrate-fit. a) One strainrate (strainrate1) and stress-strain curve (scurve1) in the strainrate-fit. The AUI determines the overstress ratio at strainrate1 using scurve1. Then the AUI uses the input material parameter TRANSITION-STRAINRATE and the overstress ratio in a curve-fitting procedure to determine material parameter BVALUE. b) More than one strainrate (strainratei) and stress-strain curve (scurvei)in the strainrate-fit. The AUI determines the overstress ratio at each strainratei using scurvei. Then the AUI uses these strainrates and overstress ratios in a curve-fitting procedure to determine both material parameters TRANSITION-STRAINRATE and BVALUE. Auxiliary commands LIST MATERIAL DELETE MATERIAL
thetai Ei nui yieldi ETi alphai EPAi Defines a nonlinear thermo-elastic-plastic and creep material, with von Mises yield condition and isotropic or kinematic strain hardening. This material model may be used with truss, 2-D solid, 3-D solid, beam, iso-beam, shell and pipe elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. HARDENING Selects the type of strain hardening used by the material. ISOTROPIC KINEMATIC
[ISOTROPIC]
Linear isotropic strain hardening. Linear kinematic strain hardening.
CREEP-LAW [0] Indicates type of the creep law. Please refer to the Theory and Modeling Guide, Section 3.6.3 for details of the formulation of these creep laws. {0/1/2/3/LUBBY2/BLACKBURN} TEMP-UNIT [CELSIUS] Creep law 3 may refer to temperatures in degrees Celsius (the centigrade scale) or degrees Kelvin (the absolute scale). {CELSIUS/KELVIN} A0 ... A15 Creep law constants, ai.
[0.0]
TREF [0.0] The reference temperature for thermal expansion calculation. See the Theory and Modeling Guide. ALPHA [1.0] Time integration parameter { 0.0 ≤ ALPHA ≤ 1.0}, used in the integration of the thermoplastic and creep rate equations. The limiting values are: 0.0 1.0 TOLIL
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
MATERIAL PLASTIC-CREEP
Sec. 7.1 Material models
Solution tolerance. See the Theory and Modeling Guide. DENSITY Mass density.
[0.0]
NRUPT1 [0] NRUPT2 [0] Label numbers of rupture criteria, defined by command RUPTURE. Two rupture criteria can be used simultaneously provided that they are not of the same type. A zero value indicates that no rupture criteria are to be used with the material definition. TIME-HARDENING [NO] Indicates whether strain hardening (NO) or time hardening (YES) is used. {YES/NO} thetai Temperature at data point “i”. Ei Young’s Modulus at temperature “thetai”. nui Poisson’s ratio at temperature “thetai”. yieldi Yield stress in simple tension at temperature “thetai”. ETi Strain hardening modulus at temperature “thetai”. alphai Mean coefficient of thermal expansion at temperature “thetai”. EPAi Maximum allowable effective plastic strain at temperature “thetai” enabling the modeling of rupture. If EPAi = 0.0 the rupture condition is not used at temperature “thetai”. Note:
The material properties are automatically sorted in order of increasing temperature. If the same temperature is given several times, only the last given values are used.
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MATERIAL PLASTIC-CREEP-VARIABLE
Chap. 7 Model definition
MATERIAL PLASTIC-CREEP-VARIABLE
NAME HARDENING NCOEF, TEMP-UNIT TREF ALPHA TOLIL DENSITY NRUPT1 NRUPT2 TIME-HARDENING CREEP-LAW
thetai Ei nui yieldi ETi alphai EPAi Defines a nonlinear thermo-elastic-plastic and creep material, with temperature and/or effective-stress dependent coefficients (see command CREEP-COEFFICIENTS ), von Mises yield condition, and isotropic or kinematic strain hardening. This material model may be used with truss, 2-D solid, 3-D solid, beam, iso-beam, shell and pipe elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. HARDENING Selects the type of strain hardening rule: ISOTROPIC
Linear isotropic strain hardening.
KINEMATIC
Linear kinematic strain hardening.
[ISOTROPIC]
NCOEF Label number of the creep coefficient dependence function, defined by command CREEP-COEFFICIENTS. TEMP-UNIT [CELSIUS] Indicates the temperature unit for the creep model; degrees Celsius (the centigrade scale) or degrees Kelvin (the absolute scale). {CELSIUS/KELVIN} TREF [0.0] The reference temperature for thermal expansion calculation. See the Theory and Modeling Guide. ALPHA [1.0] Time integration parameter {0.0 ≤ ALPHA ≤ 1.0}, used in the integration of the thermoplastic and creep rate equations. The limiting values are: 0.0
Euler forward method (explicit).
1.0
Euler backward method (implicit).
Note:
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MATERIAL PLASTIC-CREEP-VARIABLE
Sec. 7.1 Material models
TOLIL Solution tolerance. See the Theory and Modeling Guide for further details. DENSITY Mass density.
[1.0E-10] [0.0]
NRUPT1 [0] NRUPT2 [0] Label numbers of rupture criteria, as defined by command RUPTURE. Two rupture criteria can be used simultaneously, provided they are not of the same type. A zero value indicates that no rupture criteria are to be used with the material definition. TIME-HARDENING [NO] Indicates whether strain hardening (NO) or time hardening (YES) is used. {YES/NO} thetai Temperature at data point “i”. Ei Young’s Modulus at temperature “thetai”. nui Poisson’s ratio at temperature “thetai”. yieldi Yield stress in simple tension at temperature “thetai”. ETi Strain hardening modulus at temperature “thetai”. alphai Mean coefficient of thermal expansion at temperature “thetai”. EPAi Maximum allowable effective plastic strain at temperature “thetai” enabling the modeling of rupture. If EPAi = 0.0 the rupture condition is not used at temperature “thetai”. Note:
The material properties are automatically sorted in order of increasing temperature. If the same temperature is given several times, only the last given values are used.
CREEP-LAW Specifies creep law to be used. {NONE/LAW3/LUBBY2}
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[LAW3]
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MATERIAL PLASTIC-CREEP-VARIABLE
Chap. 7 Model definition
NONE
No creep.
LAW3
ec = S ⋅ T ⋅ e − H
LUBBY2
Lubby2 creep law.
Note:
If CREEP-LAW=LAW3, the parameter NCOEF reference a creep-coefficient function defined by command CREEP-COEFFICIENTS TEMPERATURE-ONLY or CREEP-COEFFICIENTS MULTILINEAR. If CREEP-LAW=LUBBY2, the parameter NCOEF reference a creep-coefficient function defined by command CREEP-COEFFICIENTS LUBBY2.
Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL PLASTIC-CYCLIC
MATERIALPLASTIC-CYCLIC
Sec. 7.1 Material models
NAME E NU DENSITY ALPHA PLCYCL-ISOTROPIC PLCYCL-KINEMATIC PLCYCL-RUPTURE BETA MAXITE RTOL
Defines a plastic-cyclic material, that is, a material model used to model cyclic plasticity. This material model can be used with 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. E Young’s modulus. {> 0.0} NU Poisson’s ratio. {-1.0 < NU < 0.5}
[0.0]
DENSITY Mass density.
[0.0]
ALPHA [0.0] Mean coefficient of thermal expansion. ALPHA is only considered if thermal loading is modeled. PLCYCL-ISOTROPIC The number of a PLCYCL-ISOTROPIC definition. This definition specifies the dependence of the radius of the yield surface on the plastic strains. This parameter must be specified. PLCYCL-KINEMATIC [0] The number of a PLCYCL-KINEMATIC definition. This definition specifies the dependence of the back stresses on the plastic strains. This parameter can be set to 0 to specify no kinematic hardening. PLCYCL-RUPTURE [0] The number of a PLCYCL-RUPTURE definition. This definition specifies the rupture criterion. This parameter can be set to 0 to specify no rupture. BETA [AUTOMATIC] A factor used in the stress integration (0 ≤ BETA ≤ 1). If BETA=AUTOMATIC, ADINA automatically sets BETA based on the time integration method (=1 for static or implicit dynamics, =0 for explicit dynamics). MAXITE The maximum number of stress integration iterations allowed per integration point.
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MATERIAL PLASTIC-CYCLIC
RTOL [1E-12] A tolerance used to assess convergence of stress integration iterations. This is a relative tolerance, i.e., dimensionless values are tested against RTOL. Notes: 1) The simplest material that can be defined using this command is given by a command sequence such as PLCYCL-ISOTROPIC 1 BILINEAR YIELD=2E8 MATERIAL PLASTIC-CYCLIC 1 E=2.07E11 NU=0.3 DENSITY=7800 PLCYCL-ISOTROPIC=1 This material is perfectly plastic. This material description is equivalent to MATERIAL PLASTIC-BILINEAR 1 E=2.07E11 NU=0.3 DENSITY=7800 YIELD=2E8 2) The PLASTIC-CYCLIC material can be used to model bilinear isotropic hardening using a command sequence such as PLCYCL-ISOTROPIC 1 BILINEAR YIELD=2E8 EP=2.090909E09 MATERIAL PLASTIC-CYCLIC 1 E=2.07E11 NU=0.3 DENSITY=7800 PLCYCL-ISOTROPIC=1 and this material description is equivalent to MATERIAL PLASTIC-BILINEAR 1 E=2.07E11 NU=0.3 DENSITY=7800 YIELD=2E8 ET=2.07E09 3) The plastic-cyclic material can be used to model multilinear isotropic hardening using a command sequence such as PLCYCL-ISOTROPIC 1 MULTILINEAR 0 2E8 1E-3 2.5E8 2E-3 2.7E8 MATERIAL PLASTIC-CYCLIC 1 E=2.07E11 NU=0.3 DENSITY=7800 PLCYCL-ISOTROPIC=1 and this material description is equivalent to MATERIAL PLASTIC-MULTILINEAR 1 E=2.07E11 NU=0.3 9.6618E-4 2E8 2.2077E-3 2.5E8 3.3043E-3 2.7E8
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MATERIAL PLASTIC-CYCLIC
Sec. 7.1 Material models
4) The plastic-cyclic material can be used to model bilinear kinematic hardening using a command sequence such as PLCYCL-ISOTROPIC 1 BILINEAR YIELD=2E8 PLCYCL-KINEMATIC 1 ARMSTRONG-FREDRICK 2.090909E9 MATERIAL PLASTIC-CYCLIC 1 E=2.07E11 NU=0.3 DENSITY=7800 PLCYCL-ISOTROPIC=1, PLCYCL-KINEMATIC=1 and this material description is equivalent to MATERIAL PLASTIC-BILINEAR 1 E=2.07E11 NU=0.3 DENSITY=7800 YIELD=2E8 ET=2.07E09, HARDENING=KINEMATIC Auxiliary commands LIST MATERIAL FIRST LAST DELETE MATERIAL FIRST LAST
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MATERIAL PLASTIC-MULTILINEAR
Chap. 7 Model definition
MATERIAL PLASTIC-MULTILINEAR NAME HARDENING E NU STRAINRATEFUNCTION DENSITY ALPHA TREF DCURVE DEPENDENCY TRANSITION-STRAINRATE EP-STRAINRATE BCURVE BVALUE STRAINRATE-FIT strain1 stress1 ... straini stressi
(stress1 = initial yield stress)
Defines a multilinear elastic-plastic material model with von Mises yield condition. The stress-strain curve is defined as piecewise linear through the data points (straini, stressi) which can be entered as data lines following the command or can be referenced via the DCURVE parameter (see SCURVE ). This material model may be used with truss, 2-D solid, 3D solid, beam, iso-beam, shell and pipe elements. When MASTER CONVERT-SSVAL=NO, stressi and straini are interpreted as true stresses and strains. Stresses and strains entered in the SCURVE command are also intrepreted as true stresses and strains. When MASTER CONVERT-SSVAL=YES, stressi and straini are interpreted as engineering stresses and strains. Stresses and strains entered in the SCURVE command are also intrepreted as engineering stresses and strains. NAME [(current highest material label number) + 1] Label number of the material to be defined. HARDENING Selects the type of strain hardening used by the material.
ISOTROPIC
KINEMATIC
[ISOTROPIC]
Linear isotropic strain hardening. Linear kinematic strain hardening.
E Young’s modulus. {> 0.0}
[0.0]
NU Poisson’s ratio. {-1.0 < NU < 0.5}
[0.0]
STRAINRATEFUNCTION The parameter is currently not used. Replaced by STRAINRATE-FIT. DENSITY Mass density.
[0] [0.0]
ALPHA [0.0] Mean coefficient of thermal expansion. ALPHA is only considered if thermal loading is modeled. 7-68
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MATERIAL PLASTIC-MULTILINEAR
Sec. 7.1 Material models
TREF [0.0] Reference temperature to calculations of ALPHA. See the Theory and Modeling Guide. Note:
Parameters ALPHA, TREF are not applicable to TRUSS elements.
DCURVE [0] Label number of a stress-strain curve defined by command SCURVE. This defines the stressstrain data points associated with this material model. If DCURVE is input as 0, then the data lines following the command define the stress-strain data points. Conversely, if DCURVE is greater than zero then no data lines are expected. DEPENDENCY Flag indicating strain rate dependency. {YES/NO} TRANSITION-STRAINRATE Transition strain rate.
[NO] [0.0001]
EP-STRAINRATE [0.0] Non-zero strainrate, used only if STRAINRATE-FIT = 0 and BCURVE > 0. This parameter is obsolete, but kept for backwards compatibility. BCURVE Label number of a stress-strain curve defined by command SCURVE. This parameter is obsolete, but kept for backwards compatibility. BVALUE Strain rate hardening parameter.
[0]
[0.0]
strain1 Strain at data point 1. The input value here is overwritten by the calculated initial yield strain (stress1 / E). stress 1 Stress at strain1, equal to the initial yield stress. straini Strain at data point i (i > 1). stress i Stress at straini. Note:
The strain-stress data points can be input in any strain order (they will be automatically sorted in increasing strain order) but all input strains must be greater than or equal to strain1 = (stress1 / E).
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Chap. 7 Model definition
Note:
The stress is assumed to be zero when the effective plastic strain is greater than the maximum input strain value.
Note:
The slope of the stress-strain curve (the tangent modulus, ET) must satisfy (for all points in the nonlinear part of the curve): 0 ≤ ET < E 0.0001 × E ≤ ET < E
for isotropic hardening. for kinematic hardening.
STRAINRATE-FIT [0] The label number of a strainrate-fit describing the strain rate dependence of the yield stress. The function must have been defined using the STRAINRATE-FIT command. A zero value indicates no strain rate dependence. Notes on the STRAINRATE-FIT, TRANSITION-STRAINRATE, EP-STRAINRATE, BCURVE and BVALUE parameters: These parameters are used only if DEPENDENCY = YES. 1) STRAINRATE-FIT = 0 and BCURVE = 0. The strainrate material parameters are TRANSITION-STRAINRATE and BVALUE. No curve-fitting is performed. 2) STRAINRATE-FIT = 0 and BCURVE > 0. The AUI uses the stress-strain curve entered in BCURVE, and the associated strainrate EP-STRAINRATE, to determine the overstress ratio at strainrate EP-STRAINRATE. Then the AUI uses the input material parameter TRANSITION-STRAINRATE and the overstress ratio in a curve-fitting procedure to determine material parameter VALUE. Note that the BCURVE > 0 option is obsolete and kept only for backwards compatibility. 3) STRAINRATE-FIT > 0. There are two possibilities, depending upon how many strainrates are entered in the strainrate-fit. a) One strainrate (strainrate1) and stress-strain curve (scurve1) in the strainrate-fit. The AUI determines the overstress ratio at strainrate1 using scurve1. Then the AUI uses the input material parameter TRANSITION-STRAINRATE and the overstress ratio in a curve-fitting procedure to determine material parameter BVALUE. b) More than one strainrate (strainratei) and stress-strain curve (scurvei)in the strainrate-fit. The AUI determines the overstress ratio at each strainratei using scurvei. Then the AUI uses these strainrates and overstress ratios in a curve-fitting procedure to determine both material parameters TRANSITION-STRAINRATE and BVALUE. Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL PLASTIC-ORTHOTROPIC
Sec. 7.1 Material models
MATERIAL PLASTIC-ORTHOTROPIC NAME EA EB EC NUAB NUAC NUBC GAB GAC GBC YIELDAA YIELDBB YIELDCC YIELDAB YIELDAC YIELDBC ETAA ETBB ETCC ETAB ETAC ETBC EPLU EPA DENSITY ALPHAA ALPHAB ALPHAC TREF OPTION METHOD R0 R45 R90 F G H L M N C E0 NN Defines a nonlinear orthotropic plastic material. This material model may be used with shell, 2-D solid and 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. EA, EB, EC a-, b- and c-direction modulus, respectively. {> 0.0} NUAB a-b strain ratio.
[0.0]
NUAC a-c strain ratio.
[0.0]
NUBC b-c strain ratio.
[0.0]
GAB a-b shear modulus. {> 0.0} GAC [0.0] a-c shear modulus. GAC=0 is admissible only for 2D solid elements ( EGROUP TWODSOLID ). {≥ 0.0} GBC [0.0] b-c shear modulus. GBC=0 is admissible only for 2D solid elements ( EGROUP TWODSOLID ). {≥ 0.0} YIELDAA, YIELDBB, YIELDCC Initial yield stress for a-, b- and c-direction, respectively. See notes at end of command description. YIELDAB Initial yield stress for ab-plane. See notes at end of command description.
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YIELDAC Initial yield stress for ac-plane. See notes at end of command description.
[0.0]
YIELDBC Initial yield stress for bc-plane. See notes at end of command description.
[0.0]
ETAA Strain hardening modulus for a-direction. Used only for OPTION = 2.
[0.0]
ETBB Strain hardening modulus for b-direction. Used only for OPTION = 2.
[0.0]
ETCC Strain hardening modulus for c-direction. Used only for OPTION = 2.
[0.0]
ETAB Strain hardening modulus for ab-plane. Used only for OPTION = 2.
[0.0]
ETAC Strain hardening modulus for ac-plane. Used only for OPTION = 2.
[0.0]
ETBC Strain hardening modulus for bc-plane. Used only for OPTION = 2.
[0.0]
EPLU [0.0] Universal plastic modulus; ratio of effective plastic stress to effective plastic strain (Hill). Used only for OPTION = 1. EPA [0.0] Maximum allowable effective plastic strain. This allows for the modeling of material rupture, whereby the stresses are set to zero whenever the effective plastic strain is greater than the rupture strain EPA. If EPA is input as 0.0, the rupture condition is not used. DENSITY Mass density.
[0.0]
ALPHAA Mean coefficient of thermal expansion for a-direction.
[0.0]
ALPHAB Mean coefficient of thermal expansion for b-direction.
[0.0]
ALPHAC Mean coefficient of thermal expansion for c-direction.
[0.0]
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Sec. 7.1 Material models
TREF [0.0] Reference temperature for calculation of ALPHAA, ALPHAB and ALPHAC. See the Theory and Modeling Guide. OPTION Indicates method to determine plastic moduli:
[1]
1
The universal plastic modulus EPLU is used to determine the plastic moduli. Any input values for the strain hardening moduli ETAA, ETBB, ETCC, ETAB, ETAC, ETBC are ignored.
2
The moduli EA, EB, EC, GAB, GAC, GBC are used with the strain hardening moduli ETAA, ETBB, ETCC, ETAB, ETAC, ETBC to determine the plastic moduli. Any input value for the universal plastic modulus EPLU is ignored.
3
Constants C, E0 and NN are used to determine the plastic moduli. Any input values for the strain hardening moduli ETAA, ETBB, ETCC, ETAB, ETAC, ETBC, EPLU are ignored.
METHOD Indicates method to determine Hill’s anisotropy parameters f, g, h, l, m, n:
[1]
1
Anisotropy parameters are calculated by AUI based on yield stresses. Any input values for R0, R45, R90, f, g, h, l, m, n are ignored.
2
Anisotropy parameters are calculated based on Lankford coefficients R0, R45, R90. Any input values for f, g, h, l, m, n are ignored.
3
Anisotropy parameters are directly defined - f, g, h, l, m, n. Any input values for R0, R45, R90 are ignored.
R0 Lankford coefficient for 00 to rolling direction.
[1.0]
R45 Lankford coefficient for 450 to rolling direction.
[1.0]
R90 Lankford coefficient for 900 to rolling direction.
[1.0]
F Hill's anisotropy parameter f.
[0.5]
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G Hill's anisotropy parameter g.
[0.5]
H Hill's anisotropy parameter h.
[0.5]
L Hill's anisotropy parameter l.
[1.5]
M Hill's anisotropy parameter m.
[1.5]
N Hill's anisotropy parameter n.
[1.5]
C
[1.0] n
Constant C of analytical stress-strain curve σ = C ⋅ (ε 0 + ε p ) . E0
[0.001] n
Constant ε0 of analytical stress-strain curve σ = C ⋅ (ε 0 + ε p ) . NN
[0.1] n
Constant n of analytical stress-strain curve σ = C ⋅ (ε 0 + ε p ) . Note: The initial yield stresses YIELDAA, ..., YIELDBC are used as follows: If METHOD = 1, the initial yield stresses are directly used. If METHOD = 2 or 3, and OPTION = 1 or 2, the initial yield stresses are only used to calculate the quantity
σy = √[{(YIELDAA2 + YIELDBB2 + YIELDCC2 )/3 + YIELDAB2 + YIELDAC2 + YIELDBC2}/2] For other combinations of METHOD and OPTION, the initial yield stresses are not used. Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL SMA
MATERIAL SMA
Sec. 7.1 Material models
NAME EM EA NUM NUA ALPHAM ALPHAA CM CA MS MF AS AF SIGMAR CR ETMAX TOLIL DENSITY TREF VTM0
Defines a shape-memory alloy (SMA) material. An SMA material may be used with truss, 2-D solid, 3-D solid and isobeam elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. EM Elastic modulus for martensite. {> 0} EA Elastic modulus for austenite.{> 0} NUM Poisson’s ratio for martensite.{0 ≤ NUM < 0.5}
[0.0]
NUA Poission’s ratio for austenite.{0 ≤ NUA < 0.5}
[0.0]
ALPHAM Mean coefficient of thermal expansion for martensite. {≥ 0.0}
[0.0]
ALPHAA Mean coefficient of thermal expansion for austenite.{≥ 0.0}
[0.0]
CM Slope of the martensite transformation conditions. {> 0} CA Slope of the austenite transformation conditions. {> 0} MS Transformation temperature at the start of martensite. {real} MF Transformation temperature at the end of martensite. {real} AS Transformation temperature at the start of austenite. {real}
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MATERIAL SMA
AF Transformation temperature at the end of austenite. {real} SIGMAR [0.0] Martensite re-orientation yield property at temperature θ=0. If SIGMAR > 0.0, the martensite re-orientation calculation is performed.{≥ 0.0} CR Slope of the martensite re-orientation yield function.{≥ 0.0}
[0.0]
ETMAX Maximum residual transformation strain.{> 0.0} TOLIL Solution tolerance for effective stress calculation. {> 0.0} DENSITY Mass density.
[0.0]
TREF Reference temperature for thermal expansion calculation. VTM0 Initial twinned martensite fraction.{0.0 ≤ VTM0 ≤ 1.0}
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MATERIAL SUSSMAN-BATHE
Sec. 7.1 Material models
MATERIAL SUSSMAN-BATHE NAME SSCURVE SSTYPE RELERROR KAPPA DENSITY TEMPERATURE-DEPENDENCE TREF RUBBER-TABLE RUBBER-VISCOELASTIC RUBBER-MULLINS RUBBER-ORTHOTROPIC straini
stressi
Defines a Sussman-Bathe material model, which is an incompressible nonlinear elastic material model for rubber materials. This material model can be used with 2-D solid and 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. SSCURVE [0] Label number of a stress-strain curve defined by command SSCURVE. This defines the stressstrain data points associated with this material model. If SSCURVE is input as 0, then the data lines following the command define the stress-strain data points. Conversely, if SSCURVE is greater than zero then no data lines are expected. SSTYPE [ENGINEERING] The type of stress-strain data entered, either in the SSCURVE command or in the data input lines. {ENGINEERING/TRUE/STRETCH} ENGINEERING engineering strains, engineering stresses TRUE
true strains, true stresses
STRETCH
stretches, engineering stresses
RELERROR [0.01] The relative error used to determine the number of splines. This value must be greater than 0.0. KAPPA [0.0] The bulk modulus, used for 3-D, plane strain and axisymmetric elements. If the bulk modulus is 0.0, then the AUI computes the bulk modulus using a Poisson’s ratio of 0.499. DENSITY Mass density.
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TEMPERATURE-DEPENDENCE Specifies the temperature dependence of the material properties. {NO/TRS/FULL}
[NO]
NO
The material properties are not temperature dependent; thermal effects are not included.
TRS
The material properties are not temperature dependent, but the material is assumed to be TRS (thermorheologically simple). Thermal effects are included.
FULL
The material properties are temperature dependent. Parameters SSCURVE to KAPPA, and RUBBER-VISCOELASTIC to RUBBER-ORTHOTROPIC of this command are ignored. No data input lines are expected.
The only parameters used when TEMPERATURE-DEPENDENCE = FULL are NAME, TEMPERATURE-DEPENDENCE, TREF and RUBBER-TABLE. TREF [0.0] The material reference temperature, required if TEMPERATURE-DEPENDENCE = TRS or FULL. RUBBER-TABLE The label number of a rubber-table data set. The type of rubber-table depends upon TEMPERATURE-DEPENDENCE, as follows:
[0]
TEMPERATURE-DEPENDENCE = NO : Do not enter a rubber-table. TEMPERATURE-DEPENDENCE = TRS : A rubber-table of type TRS must be entered. This rubber-table is a table of temperatures and corresponding coefficients of thermal expansion. TEMPERATURE-DEPENDENCE = FULL : A rubber-table of type Sussman-Bathe must be entered. This rubber-table is a table of temperatures and corresponding material properties. RUBBER-VISCOELASTIC [0] If RUBBER-VISCOELASTIC is zero, no viscoelastic effects are included. If RUBBER-VISCOELASTIC is non-zero, viscoelastic effects are included, using the data set from the corresponding RUBBER-VISCOELASTIC command. This parameter is not used when TEMPERATURE-DEPENDENCE = FULL. RUBBER-MULLINS If RUBBER-MULLINS is zero, no Mullins effects are included.
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Sec. 7.1 Material models
If RUBBER-MULLINS is nonzero, Mullins effects are included, using the data set from the corresponding RUBBER-MULLINS command. This parameter is not used when TEMPERATURE-DEPENDENCE = FULL. RUBBER-ORTHOTROPIC [0] If RUBBER-ORTHOTROPIC is zero, no orthotropic effects are included. If RUBBER-ORTHOTROPIC is non-zero, orthotropic effects are included, using the data set from the corresponding RUBBER-ORTHOTROPIC command. This parameter is not used when TEMPERATURE-DEPENDENCE = FULL. straini, stressi The strain and stress at data point i. The strain and stress are interpreted according to the SSTYPE parameter. The (strain,stress) data points are assumed to correspond to a uniaxial tension/compression conditions. Auxiliary commands LIST MATERIAL FIRST LAST DELETE MATERIALFIRST LAST
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MATERIAL THERMO-ISOTROPIC
Sec. 7.1 Material models
MATERIALTHERMO-ISOTROPIC
NAME TREF DENSITY
thetai Ei nui alphai Defines a nonlinear isotropic thermo-elastic material model which considers the variation of material properties with temperature. Linear interpolation is performed to determine values at intermediate temperatures. This material model may be used with truss, 2-D solid, 3-D solid, isobeam, shell and pipe elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. TREF [0.0] The reference temperature for expansion coefficient calculation. See the Theory and Modeling Guide. DENSITY Mass density.
[0.0]
thetai Temperature at data point “i”. (i ≤ 16) Ei Young’s Modulus at temperature “thetai”. (i ≤ 16) nui Poisson’s ratio at temperature “thetai”. (i ≤ 16) alphai Mean coefficient of thermal expansion at temperature “thetai”. (i ≤ 16) Note: The material properties are automatically sorted in order of increasing temperature. If the same temperature is given several times, only the last given value is used. Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIALTHERMO-ORTHOTROPIC
MATERIAL THERMO-ORTHOTROPIC
NAME TREF DENSITY
thetai Eai Ebi Eci nuabi nuaci nubci Gabi Gaci Gbci alphaai alphabi alphaci Defines a nonlinear orthotropic thermo-elastic material model which considers the variation of material properties with temperature. Linear interpolation is performed to determine values at intermediate temperatures. This material model may be used with shell, 2-D solid and 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. TREF [0.0] The reference temperature for thermal expansion calculation. See the Theory and Modeling Guide. DENSITY Mass density.
[0.0]
thetai Temperature at data point “i”. (i ≤ 16) Eai a-direction modulus at temperature “thetai”. (i ≤ 16) Ebi b-direction modulus at temperature “thetai”. (i ≤ 16) Eci c-direction modulus at temperature “thetai”. (i ≤ 16) nuabi a-b strain ratio at temperature “thetai”. (i ≤ 16) nuaci a-c strain ratio at temperature “thetai”. (i ≤ 16) nubci b-c strain ratio at temperature “thetai”. (i ≤ 16) Gabi a-b shear modulus at temperature “thetai”. (i ≤ 16)
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Sec. 7.1 Material models
Gaci a-c shear modulus at temperature “thetai”. (i ≤ 16) Gbci b-c shear modulus at temperature “thetai”. (i ≤ 16) alphaai Mean coefficient of thermal expansion in a-direction at temperature “thetai”. alphabi Mean coefficient of thermal expansion in b-direction at temperature “thetai”. alphaci Mean coefficient of thermal expansion in c-direction at temperature “thetai”. Note: The material properties are automatically sorted in order of increasing temperature. If the same temperature is given several times, only the last given values are used. Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL THERMO-PLASTIC
Chap. 7 Model definition
MATERIALTHERMO-PLASTIC
NAME HARDENING TREF TOLIL DENSITY
thetai Ei nui yieldi ETi alphai EPAi Defines a nonlinear thermo-plastic material. This material model may be used with truss, 2-D solid, 3-D solid, isobeam, shell and pipe elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. HARDENING Selects the type of strain hardening used by the material. ISOTROPIC
Linear isotropic strain hardening.
KINEMATIC
Linear kinematic strain hardening.
[ISOTROPIC]
TREF [0.0] The reference temperature for thermal expansion calculation. See the Theory and Modeling Guide. TOLIL Solution tolerance. See Theory and Modeling Guide. DENSITY Mass density.
[1.0E-10] [0.0]
thetai Temperature at data point “i”. Ei Young’s Modulus at temperature “thetai”. nui Poisson’s ratio at temperature “thetai”. yieldi Yield stress in simple tension at temperature “thetai”. ETi Strain hardening modulus at temperature “thetai”.
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alphai Mean coefficient of thermal expansion at temperature “thetai”. EPAi Maximum allowable effective plastic strain at temperature “thetai” enabling the modeling of rupture. If EPAi = 0.0 the rupture condition is not used at temperature “thetai”. Note: The material properties are automatically sorted in order of increasing temperature. If the same temperature is given several times, only the last given values are used. Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL USER-SUPPLIED
Chap. 7 Model definition
MATERIAL USER-SUPPLIED
NAME INTEG NSUBD TREF DENSITY LENGTH1 LENGTH2 OPTION NCTI NSCP NCTD CTI1 ... CTI99 SCP1 ... SCP99 LENGTH3 LENGTH4 AUTOLEN NONSYM DENSITY
tempi alphai ctd1i ctd2i ... CtdNCTDi Defines a user-supplied material for use with ADINA, with options for piezoelectric or consolidation analyses (requiring interaction with ADINA-T). This material model may be used with 2-D solid and 3-D solid elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. INTEG Stress integration scheme. {FORWARD/BACKWARD} FORWARD
Forward integration scheme.
BACKWARD
Backward integration scheme.
[FORWARD]
NSUBD [10] Number of subdivisions of strain increments used in the integration of stresses. If INTEG = BACKWARD, NSUBD = 1 is always used regardless of this input. { > 0 } TREF [0.0] Reference temperature for thermal expansion calculation. See the Theory and Modeling Guide. DENSITY Mass density.
[0.0]
LENGTH1 [60] Length of working real array for storing/retrieving history dependent variables. See the Theory and Modeling Guide for details. LENGTH2 [2] Length of working integer array for storing/retrieving history dependent variables. See Theory and Modeling Guide for details. OPTION [NONE] Special analysis options. {NONE/PIEZOELECTRIC/CONSOLIDATION/LINEAR}
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Sec. 7.1 Material models
NONE
- No special analysis option
PIEZOELECTRIC
- Piezoelectric analysis (involving interaction with ADINA-T)
CONSOLIDATION
- Consolidation analysis.
LINEAR
- Linear material model option
NCTI Number of active material property constants. {0 ≤ NCTI ≤ 99} NSCP Number of active solution control parameters. {0 ≤ NSCP ≤ 99} NCTD Number of active temperature dependent material properties. {0 ≤ NCTD ≤ 98}
[0]
CTI1 ... CTI99 User defined material constants.
[0.0]
SCP1 ... SCP99 User defined solution control parameters.
[0.0]
LENGTH3 Number of parameters from the real working array to write to porthole file. {0 ≤ LENGTH3 ≤ LENGTH1}
[0]
LENGTH4 Number of parameters from the integer working array to write to porthole file. {0 ≤ LENGTH4 ≤ LENGTH2}
[0]
AUTOLEN Flag for setting the size of working and output arrays LENGTH1 - LENGTH4. {0 / 1}
[0]
0
Manually set via LENGTH1 - LENGTH4 variables
1
Automatically set by call to user coded material subroutine with KEY=0
NONSYM [NO] Flag for symmetry of stiffness matrix generated by this user-supplied material. {NO/YES} Note: Nonsymmetric stiffness matrix can only be activated when a non-symmetric solver is selected.
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DENSITY Mass density. {≥ 0.0}
[1.0]
tempi Temperature at data point “i”. alphai Mean coefficient of the thermal expansion at temperature “tempi”. ctdJi value of temperature-dependent material property “J” at temperature “tempi”. Note:
The material properties are automatically sorted in order of increasing temperature. If the same temperature is given several times, only the last given values are used.
Auxiliary commands LIST MATERIAL DELETE MATERIAL
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MATERIAL VISCOELASTIC
MATERIAL VISCOELASTIC
NAME NSUBD TREF C1 C2 ALPHA G-FUNCTION K-FUNCTION DENSITY SHIFT
thetai alphai Defines a viscoelastic material with time dependent and temperature dependent material properties. This material model may be used with truss, 2-D solid, 3-D solid and shell elements. NAME [(current highest material label number) + 1] Label number of the material to be defined. If the label number of an existing material is given, the existing material definition is overwritten. NSUBD Number of subdivisions of strain increments used in the integration of stresses.
[10]
TREF [0.0] Reference temperature used by the WLF (Williams-Landell-Ferry) equation for temperaturetime shift calculation. C1 [0.0] C2 [0.0] Material constants used by the WLF (Williams-Landell-Ferry) equation or the Arrhenius equation for temperature-time shift calculation. ALPHA [0.0] Constant mean coefficient of thermal expansion. If no temperature table is defined, alpha is assumed constant. G-FUNCTION Label number of a table, defined by command FTABLE, containing a series of shear moduli and decay coefficients to represent the shear modulus relaxation function. K-FUNCTION Label number of a table, defined by command FTABLE, containing a series of bulk moduli and decay coefficients to represent the bulk modulus relaxation function. DENSITY Mass density.
[0.0]
SHIFT Specifies the time-temperature superposition law. {WLF/ARRHENIUS}
[WLF]
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Sec. 7.1 Material models
WLF
Williams-Landell-Ferry equation
ARRHENIUS
Arrhenius equation
The following data lines are used only when the coefficient of thermal expansion is temperature-dependent: thetai Temperature at data point “i”. (i ≤ 16) alphai Mean coefficient of thermal expansion at temperature “thetai”. (i ≤ 16) Auxiliary commands LIST MATERIAL DELETE MATERIAL
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TMC-MATERIAL ISOTROPIC
Chap. 7 Model definition
TMC-MATERIAL ISOTROPIC NAME K C JOULE-HEAT ELECTRIC-K DENSITY Defines a constant, isotropic, conductivity and constant specific heat material. This command is used in ADINA thermal coupling for TRUSS, 2D/3D Solid, BEAM, ISOBEAM, PIPE elements only. NAME [(current highest material label number) + 1] Label number of the material to be defined. K Thermal conductivity. {≥ 0.0} C Heat capacity per unit volume.
[0.0]
{≥ 0.0}
JOULE-HEAT Indicates whether this material is used for Joule heat analysis. { YES/NO }
Auxiliary commands LIST TMC-MATERIAL FIRST LAST DELETE TMC-MATERIALFIRST LAST
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TMC-MATERIAL ORTHOTROPIC
TMC-MATERIAL ORTHOTROPIC
Sec. 7.1 Material models
NAME KA KB KC C JOULE-HEAT EKA EKB EKC DENSITY
Defines a constant, orthotropic, thermal conductivity and constant specific heat material. This command is used in ADINA thermal coupling for TRUSS, 2D/3D Solid, BEAM, ISOBEAM, PIPE elements only. NAME [(current highest material label number) + 1] Label number of the material to be defined. KA Thermal conductivity in a-direction. {≥ 0.0}
[0.0]
KB Thermal conductivity in b-direction. {≥ 0.0}
[0.0]
KC Thermal conductivity in c-direction. {≥ 0.0}
[0.0]
C Heat capacity per unit volume. {≥ 0.0}
[0.0]
JOULE-HEAT Indicates whether this material is used for Joule heat analysis. {YES/NO}
[NO]
EKA [0.0] EKB [0.0] EKC [0.0] Electrical conductivity in the a-, b- and c-directions. (units: electrical conductance/length, e.g., Siemens/m) {≥ 0.0} DENSITY Mass density. {≥ 0.0}
[1.0]
Auxiliary commands LIST TMC-MATERIAL FIRST LAST DELETE TMC-MATERIALFIRST LAST
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TMC-MATERIAL TEMPDEP-K
TMC-MATERIAL TEMPDEP-K NAME C JOULE-HEAT DENSITY thetai ki electric-ki Defines a material with temperature dependent thermal conductivity and constant specific heat. This command is used in ADINA thermal coupling for TRUSS, 2D/3D Solid, BEAM, ISOBEAM, PIPE elements only. NAME [(current highest material label number) + 1] Label number of the material to be defined. C Heat capacity per unit volume. {≥ 0.0} JOULE-HEAT Indicates whether this material is used for Joule heat analysis. { YES/NO } DENSITY Mass density. {≥ 0.0}
[0.0]
[NO] [1.0]
thetai Temperature at data point “i”. ki Thermal conductivity at temperature thetai. electric-ki Electrical conductivity at temperature thetai. Note: The input data is automatically sorted in order of increasing temperature. If the same temperature is given several times, only the last given value is used. Auxiliary commands LIST TMC-MATERIAL FIRST LAST DELETE TMC-MATERIALFIRST LAST
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TMC-MATERIAL TEMPDEP-C-ISOTROPIC
TMC-MATERIAL TEMPDEP-C-ISOTROPIC
Sec. 7.1 Material models
NAME K DENSITY
thetai ci Defines a material with temperature dependent specific heat and constant, isotropic, thermal conductivity. This command is used in ADINA thermal coupling for TRUSS, 2D/3D Solid, BEAM, ISOBEAM, PIPE elements only. NAME [(current highest material label number) + 1] Label number of the material to be defined. K Thermal conductivity. {≥ 0.0}
[0.0]
DENSITY Mass density. {≥ 0.0}
[1.0]
thetai Temperature at data point “i”. ci Heat capacity per unit volume at temperature thetai. Note: The input data is automatically sorted in order of increasing temperature. If the same temperature is given several times, only the last given value is used. Auxiliary commands LIST TMC-MATERIAL FIRST LAST DELETE TMC-MATERIALFIRST LAST
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TMC-MATERIAL TEMPDEP-C-ORTHOTROPIC
TMC-MATERIAL TEMPDEP-C-ORTHOTROPIC
NAME KA KB KC CONDUCTIVITY DENSITY
thetai ci kai kbi kci Defines a material with temperature dependent specific heat and constant, orthotropic thermal conductivity. This command is used in ADINA thermal coupling for TRUSS, 2D/3D Solid, BEAM, ISOBEAM, PIPE elements only. NAME [(current highest material label number) + 1] Label number of the material to be defined. KA Thermal conductivity in a-direction. {≥ 0.0}
[0.0]
KB Thermal conductivity in b-direction. {≥ 0.0}
[0.0]
KC Thermal conductivity in c-direction. {0.0}
[0.0]
CONDUCTIVITY [CONSTANT] Flags whether conductivity is constant or input in table. {CONSTANT/TABLE} DENSITY Mass density. {≥ 0.0}
[1.0]
thetai Temperature at data point “i”. ci Heat capacity per unit volume at temperature thetai. kai Thermal conductivity in a-direction {≥ 0.0}
[value of parameter KA]
kbi Thermal conductivity in b-direction {≥ 0.0}
[value of parameter KB]
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TMC-MATERIAL TEMPDEP-C-ORTHOTROPIC
kci Thermal conductivity in c-direction {≥ 0.0}
Sec. 7.1 Material models
[value of parameter KC]
Note: The input data is automatically sorted in order of increasing temperature. If the same temperature is given several times, only the last given value is used. Auxiliary commands LIST TMC-MATERIAL FIRST LAST DELETE TMC-MATERIALFIRST LAST
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TMC-MATERIAL TEMPDEP-C-K
TMC-MATERIAL TEMPDEP-C-K NAME JOULE-HEAT DENSITY thetai ki ci electric-ki Defines a material with temperature dependent specific heat and thermal conductivity. This command is used in ADINA thermal coupling for TRUSS, 2D/3D Solid, BEAM, ISOBEAM, PIPE elements only. NAME [(current highest material label number) + 1] Label number of the material to be defined. JOULE-HEAT Indicates whether this material is used for Joule heat analysis. { YES/NO } DENSITY Mass density. {≥ 0.0}
[NO] [1.0]
thetai Temperature at data point “i”. ki Thermal conductivity at temperature thetai. ci Heat capacity per unit volume at temperature thetai. electric-ki Electrical conductivity at temperature thetai. Note: The input data is automatically sorted in order of increasing temperature. If the same temperature is given several times, only the last given value is used. Auxiliary commands LIST TMC-MATERIAL FIRST LAST DELETE TMC-MATERIALFIRST LAST
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TMC-MATERIAL TIMEDEP-K
Sec. 7.1 Material models
TMC-MATERIAL TIMEDEP-K NAME C DENSITY timei ki Defines a material with time dependent thermal conductivity and constant specific heat. This command is used in ADINA thermal coupling for TRUSS, 2D/3D Solid, BEAM, ISOBEAM, PIPE elements only. NAME [(current highest material label number) + 1] Label number of the material to be defined. C Heat capacity per unit volume. {≥ 0.0}
[0.0]
DENSITY Mass density. {≥ 0.0}
[1.0]
timei Time at data point “i”. ki Conductivity at timei. Note: The input data is automatically sorted in order of increasing time. If the same time is given several times, only the last given value is used. Auxiliary commands LIST TMC-MATERIAL FIRST LAST DELETE TMC-MATERIALFIRST LAST
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CURVE-FITTING
Chap. 7 Model definition
CURVE-FITTING
NAME ORDER TENSION-CURVE SHEAR-CURVE EQUIBIAXIAL-CURVE WEIGHTING CURVE-TYPE METHOD NSINGULAR MAX-SINGV MIN-SINGV ECHO
Defines a fitting curve for hyperelastic material models. A least squares curve fitting technique is employed to determine the parameters for a Mooney-Rivlin, Ogden, Arruda-Boyce or hyper-foam material model from experimental stress versus strain (or stretch) data. The data can be input for any of three test cases: (i) simple tension, (ii) pure shear, or (iii) equibiaxial tension. A single test or combination of any two, or all three, can be supplied. The accuracy of the model curve thus fitted depends on the number of data points, and the desired approximation order of the model. The total number of data points, from all three test cases, is subject to a minimum, as follows: 2,5,9 for a Mooney-Rivlin model of input order 1, 2, 3 respectively; the input order for the Ogden material; 2 for the Arruda-Boyce material; and the input order for the hyper-foam material.
• • • •
NAME [(current highest curve-fitting label number) + 1] Label number of the curve-fitting to be defined. If the label number of an existing curve-fitting is given, then the previous curve-fitting definition is overwritten. This curve number can be assigned to the Mooney-Rivlin, Ogden, Arruda-Boyce or hyper-foam material model where material constants for the model are evaluated form the input curves (see Notes at the end of this command). ORDER Approximation order. Allowed values are: • Mooney-Rivlin material: 1 to 3 • Ogden material: 1 to 9 • Arruda-Boyce material: 2 • Hyper-foam material: 1 to 9
[3]
TENSION-CURVE [0] Indicates the label number of a (stress, strain) data curve, which provides data for the simple tension test case. This data curve is defined by command SSCURVE. A value of 0 indicates no simple tension data is supplied. The abscissae may be interpreted as strain or stretch as 7-100
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CURVE-FITTING
Sec. 7.1 Material models
indicated by parameter CURVE-TYPE. SHEAR-CURVE [0] Similar to TENSION-CURVE, except that this curve provides data for the pure shear test case. EQUIBIAXIAL-CURVE [0] Similar to TENSION-CURVE, except that this curve provides data for the equilbiaxial tension test case. WEIGHTING [NO] Specifies whether the least squares fitting scheme utilises weighted data intervals or not --their use may provide a better fit for data with very irregular spacing of the strain (or stretch) abscissae. See the Theory and Modeling Guide for further details. Input values are YES or NO. CURVE-TYPE [STRAIN] Indicates the type of input curve data given by parameters TENSION-CURVE, SHEARCURVE, and EQUIBIAXIAL-CURVE. The option is given for the data abscissae to be either principal (engineering) strain, or principal stretch (= deformed length /undeformed length). The ordinate values in either case are values of nominal stress (= force / unit undeformed area). {STRAIN/STRETCH} STRAIN STRETCH
-input principal engineering strain data - input principal stretch data
METHOD [SVD] Specifies the least squares matrix equation solution method. Use of Gaussian elimination may well result in model constants which alternate in sign and have very high magnitude. This is due to the presence of near-singular terms in the least squares system. The "singular value decomposition" method attempts to remove these terms during solution, yielding more reasonable model constants without affecting the overall quality of the least squares fit. The number of near-singular terms to be removed may be controlled by parameters MAX-SINGV, MIN-SINGV. Near-singular terms are removed by default until a monotone increasing solution is obtained for all test cases. This parameter is only used for the Mooney-Rivlin and Ogden material models. SVD - The singular value decomposition method GAUSS - Standard Gaussian elimination technique NSINGULAR [AUTOMATIC] Indicates whether the number of near-singular terms to be removed in the singular value decomposition solution method is controlled automatically by the program, or is to be
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CURVE-FITTING
user-specified via parameters MAX-SINGV, MIN-SINGV. This parameter is only applicable when METHOD=SVD. AUTOMATIC - the program controls the number of near-singular terms to be removed by the singular value decomposition solution method. CUSTOM - the user indicates the maximum and minimum number of near-singular terms to be removed. MAX-SINGV [0] If NSINGULAR=CUSTOM, this parameter indicates the maximum number of near-singular terms which are permitted to be removed during the search for a monotone increasing set of result curves. MAX-SINGV may range from 0 (for which the resulting solution is identical to that obtained by Gaussian elimination) to the total desired number of model constants, as indicated by parameter ORDER. This parameter is only applicable when METHOD=SVD. MIN-SINGV [0] If NSINGULAR=CUSTOM, this parameter indicates the minimum number of near-singular terms which will be removed by the singular value decomposition method, i.e. the SVD algorithm will remove at least MIN-SINGV terms even if a monotone solution set was obtained with fewer terms removed. This parameter is only applicable when METHOD=SVD. ECHO Specifies the level of information reported by the command: NONE MODEL ALL
[ALL]
- the command behaves silently, except for a completion message - the resulting material model constants are reported - as well as model constants, curve fitting statistics and comparison tables of input and fitted stress values for the input strain/stretch points is reported.
Notes: 1
For a discussion on the singular value decomposition method and its application to the least squares curve fitting algorithm, please consult the Theory and Modeling Guide.
2
It is unwise to apply this command to a small set of data within a narrow range of strains/ stretches. If possible, some values of strain/stretch should be input for compression, and
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CURVE-FITTING
Sec. 7.1 Material models
it is recommended that the resulting curve-fitting behavior always be checked with the MATERIALSHOW command. 3 The respective constants for each material model calculated from the input data curves are as follows (see Section 3.8.5 of the Theory and Modeling Guide Volume I for more details): Mooney-Rivlin: ORDER Constants 1 C1, C2 2 C1 - C5 3 C1 - C9 Ogden: The constants µi and αi are calculated from i = 1 to ORDER. Arruda-Boyce: ORDER = 2 only, with constants C1 to C5. Hyper-foam: The constants µi, αi and βi are calculated from i = 1 to ORDER.
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Defines viscoelastic contants for a viscoelastic material model. NAME
[(current highest viscoelastic-constants label number) + 1] Label number of the viscoelastic-contants to be defined. If the label number of an existing viscoelastic-contants is given, then the previous definition is overwritten. NPOINTS Number of constants. {1<=NPOINTS<=5}
[2]
BETA1 BETA2 BETA3 BETA4 BETA5 Free energy factors. {BETA>=0.0}
Auxiliary commands LIST VISCOELASTIC-CONSTANTS DELETE VISCOELASTIC-CONSTANTS
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PHI-MODEL-COMPLETION
PHI-MODEL-COMPLETION CLOSE-TOL XTOL YTOL ZTOL CLOSE-NODE PHI-ANGLE NORMAL-ANGLE This command controls certain parameters used during the phi model completion phase of constructing the data file. The phi model completion phase is performed only when there are potential-based fluid elements in the model. CLOSE-TOL [AUTOMATIC] This parameter controls which tolerances are used during when searching for structural nodes coincident with potential-based fluid nodes. AUTOMATIC
The tolerances from the TOLERANCES GEOMETRIC command are used. The coincidence checks are the same as are used during mesh generation.
CUSTOM
The tolerances XTOL, YTOL, ZTOL of this command are used.
XTOL [0.0] YTOL [0.0] ZTOL [0.0] Tolerances used for coincident node checking during phi model completion, used only when CLOSE-TOL = CUSTOM. Note that XTOL, YTOL, ZTOL are absolute tolerances. To be specific, a structural node with coordinates (XS,YS,ZS) are coincident with a fluid node with coordinates (XF,YF,ZF) when XF-XTOL ≤ XS ≤ XF+XTOL YF-YTOL ≤ YS ≤ YF+YTOL ZF-ZTOL ≤ ZS ≤ ZF+ZTOL CLOSE-NODE [CLOSEST] This parameter controls which node is taken if two or more nodes are coincident. HIGHEST
The node with the highest number is taken.
CLOSEST
The closest node is taken.
PHI-ANGLE [30] This parameter, in degrees, is used in constructing the boundary conditions for a node on a free surface that is adjacent to the structure. When the angle between two adjacent faces of the structural boundary is greater than PHI-ANGLE, the AUI treats the intersection of the faces as a sharp corner. When the angle between two adjacent faces of the structural boundary is less than or equal to PHI-ANGLE, the AUI considers the faces to approximate smooth boundary. NORMAL-ANGLE [80] This parameter, in degrees, is the maximum angle between the unmodified and modified free normals on a fluid free surface. 7-106
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PLCYCL-ISOTROPIC BILINEAR
PLCYCL-ISOTROPIC BILINEAR
Sec. 7.1 Material models
NAME YIELD EP
Sets up a PLCYCL-ISOTROPIC definition of type bilinear. This definition can be used in the MATERIAL PLASTIC-CYCLIC command. NAME [(current highest plcycl-isotropic label number) + 1] Label number of the plcycl-isotropic definition. If the label number of an existing plcyclisotropic data set is defined, then the previous definition is overwritten. YIELD Yield stress (radius of yield surface). EP [0.0] Hardening modulus, giving the change in yield stress with respect to the accumulated effective plastic strain. Auxiliary commands LIST PLCYCL-ISOTROPIC FIRST LAST DELETE PLCYCL-ISOTROPIC FIRST LAST
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PLCYCL-ISOTROPIC MULTILINEAR
PLCYCL-ISOTROPIC MULTILINEAR
NAME
aepsi stress-radiusi Sets up a PLCYCL-ISOTROPIC definition of type multilinear. This definition can be used in the MATERIAL PLASTIC-CYCLIC command. NAME [(current highest plcycl-isotropic label number) + 1] Label number of the plcycl-isotropic definition. If the label number of an existing plcyclisotropic data set is defined, then the previous definition is overwritten. aepsi Accumulated effective plastic strain, interpreted as a logarithmic strain in large strain analysis. stress-radiusi Associated radius of yield surface (yield stress). During the analysis, if the accumulated effective plastic strain exceeds the largest value of aepsi, then ADINA issues an error message and either stops or cuts back the time step (if the ATS method is used). Auxiliary commands LIST PLCYCL-ISOTROPIC FIRST LAST DELETE PLCYCL-ISOTROPIC FIRST LAST
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PLCYCL-ISOTROPIC EXPONENTIAL
PLCYCL-ISOTROPIC EXPONENTIAL
Sec. 7.1 Material models
NAME YIELD Q B
Sets up a PLCYCL-ISOTROPIC definition of type exponential. This definition can be used in the MATERIAL PLASTIC-CYCLIC command. NAME [(current highest plcycl-isotropic label number) + 1] Label number of the plcycl-isotropic definition. If the label number of an existing plcyclisotropic data set is defined, then the previous definition is overwritten. YIELD Yield stress (radius of yield surface). This parameter must be entered. Q [0.0] B [0.0] Parameters giving the change in yield stress with respect to the accumulated effective plastic strain, see the Theory and Modeling Guide. If Q is positive, the material cyclically hardens, if Q is negative, the material cyclically softens. Q and B default to 0.0. Auxiliary commands LIST PLCYCL-ISOTROPIC FIRST LAST DELETE PLCYCL-ISOTROPIC FIRST LAST
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PLCYCL-ISOTROPIC MEMORY-EXPONENTIAL
PLCYCL-ISOTROPIC MEMORY- EXPONENTIAL NAME YIELD Q0 QM MU B ETA Sets up a PLCYCL-ISOTROPIC definition of type memory-exponential. This definition can be used in the MATERIAL PLASTIC-CYCLIC command. The strain memory surface algorithm of Lemaitre and Chaboche is used, see the Theory and Modeling Guide. NAME [(current highest plcycl-isotropic label number) + 1] Label number of the plcycl-isotropic definition. If the label number of an existing plcyclisotropic data set is defined, then the previous definition is overwritten. YIELD Yield stress (radius of yield surface). This parameter must be entered. Q0 [0.0] QM [0.0] MU [0.0] B [0.0] ETA [0.5] Parameters giving the change in yield surface radius with respect to the accumulated effective plastic strain and the strain memory, see the Theory and Modeling Guide. All of these parameters, except for ETA, default to 0.0; ETA defaults to 0.5. Auxiliary commands LIST PLCYCL-ISOTROPIC FIRST LAST DELETE PLCYCL-ISOTROPIC FIRST LAST
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PLCYCL-KINEMATIC ARMSTRONG-FREDRICK
Sec. 7.1 Material models
PLCYCL-KINEMATIC ARMSTRONG-FREDRICK NAME hi
zetai
Sets up a PLCYCL-KINEMATIC definition of type Armstrong-Fredrick. This definition can be used in the MATERIAL PLASTIC-CYCLIC command. NAME [(current highest plcycl-kinematic label number) + 1] Label number of the plcycl-kinematic definition. If the label number of an existing plcyclkinematic data set is defined, then the previous definition is overwritten. hi Linear kinematic hardening constant. zetai Nonlinear kinematic hardening constant. It is allowed to set zetai=0.0.
[0.0]
Note: When zetai=0.0, then hi is equal to the plastic hardening modulus Ep. It is allowed to enter several values of hi and zetai, each with a different value of zetai. Auxiliary commands LIST PLCYCL-KINEMATIC FIRST LAST DELETE PLCYCL-KINEMATIC FIRST LAST
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PLCYCL-RUPTURE AEPS
Chap. 7 Model definition
PLCYCL-RUPTURE AEPS
NAME VALUE
Sets up a PLCYCL-RUPTURE definition of type AEPS (accumulated effective plastic strain). This definition can be used in the MATERIAL PLASTIC-CYCLIC command. NAME [(current highest plcycl-rupture label number) + 1] Label number of the plcycl-rupture definition. If the label number of an existing plcycl-rupture data set is defined, then the previous definition is overwritten. VALUE The value of accumulated effective plastic strain at which the material ruptures. It is allowed to enter nothing for this value, then the material will not rupture. Auxiliary commands LIST PLCYCL-RUPTURE FIRST LAST DELETE PLCYCL-RUPTURE FIRST LAST
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RUBBER-TABLE MOONEY-RIVLIN
RUBBER-TABLE MOONEY-RIVLIN
Sec. 7.1 Material models
NAME
thetai alphai c1i c2i c3i c4i c5i c6i c7i c8i c9i d1i d2i kappai fitting-curvei rubber-viscoelastici rubber-mullinsi rubber-orthotropici Defines a rubber-table data set of type Mooney-Rivlin. This data set can be used to describe the temperature dependence of the Mooney-Rivlin material constants in the MATERIAL MOONEY-RIVLIN command. NAME [(current highest rubber-table label number) + 1] Label number of the rubber-table data set to define. If the label number of an existing rubbertable data set is defined, then the previous definition is overwritten. thetai The temperature corresponding to the material properties entered in this data input line. alphai The coefficient of thermal expansion.
[0.0]
c1i ... c9i d1i ... d2i kappai The material properties.
[0.0] [0.0] [0.0]
fitting-curvei [0] If fitting-curvei is zero, no fitting curve is used. If fitting-curvei is nonzero, curve-fitting data from the CURVE-FITTING command is used to compute the material properties, and c1i to d2i are ignored. rubber-viscoelastici [0] If rubber-viscoelastici is zero, no viscoelastic effects are included. If rubber-viscoelastici is non-zero, viscoelastic effects are included, using the data set from the corresponding RUBBER-VISCOELASTIC command. rubber-mullinsi If rubber-mullinsi is zero, no Mullins effects are included. If rubber-mullinsi is non-zero, Mullins effects are included, using the data set from the corresponding RUBBER-MULLINS command.
[0]
[0] rubber-orthotropici If rubber-orthotropici is zero, no orthotropic effects are included. If rubber-orthotropici is non-zero, orthotropic effects are included, using the data set from the corresponding RUBBER-ORTHOTROPIC command.
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RUBBER-TABLE MOONEY RIVLIN
Chap. 7 Model definition
Auxiliary commands LIST RUBBER-TABLE DELETE RUBBER-TABLE
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RUBBER-TABLE OGDEN
Sec. 7.1 Material models
RUBBER-TABLE OGDEN NAME thetai alphai mu1i alpha1i mu2i alpha2i mu3i alpha3i mu4i alpha4i mu5i alpha5i mu6i alpha6i mu7i alpha7i mu8i alpha8i mu9i alpha9i kappai fitting-curvei rubber-viscoelastici rubber-mullinsi rubber-orthotropici Defines a rubber-table data set of type Ogden. This data set can be used to describe the temperature dependence of the Ogden material constants in the MATERIAL OGDEN command. NAME [(current highest rubber-table label number) + 1] Label number of the rubber-table data set to define. If the label number of an existing rubbertable data set is defined, then the previous definition is overwritten. thetai The temperature corresponding to the material properties entered in this data input line. alphai The coefficient of thermal expansion.
[0.0]
mu1i ... mu9i alpha1i ... alpha9i kappai The material properties.
[0.0] [0.0] [0.0]
fittting-curvei [0] If fittting-curvei is zero, no fitting curve is used. If fittting-curvei is nonzero, curve-fitting data from the CURVE-FITTING command is used to compute the material properties, and mu1i to alpha9i are ignored. rubber-viscoelastici [0] If rubber-viscoelastici is zero, no viscoelastic effects are included. If rubber-viscoelastici is non-zero, viscoelastic effects are included, using the data set from the corresponding RUBBER-VISCOELASTIC command. rubber-mullinsi If rubber-mullinsi is zero, no Mullins effects are included. If rubber-mullinsi is non-zero, Mullins effects are included, using the data set from the corresponding RUBBER-MULLINS command.
[0]
[0] rubber-orthotropici If rubber-orthotropici is zero, no orthotropic effects are included. If rubber-orthotropici is non-zero, orthotropic effects are included, using the data set from the corresponding RUBBER-ORTHOTROPIC command. ADINA R & D, Inc.
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Auxiliary commands LIST RUBBER-TABLE DELETE RUBBER-TABLE
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RUBBER-TABLE ARRUDA-BOYCE
RUBBER-TABLE ARRUDA-BOYCE
Sec. 7.1 Material models
NAME
thetai alphai mui lambdai kappai fitting-curvei rubber-viscoelastici rubber-mullinsi rubber-orthotropici Defines a rubber-table data set of type Arruda-Boyce. This data set can be used to describe the temperature dependence of the Arruda-Boyce material constants in the MATERIAL ARRUDA-BOYCE command. NAME [(current highest rubber-table label number) + 1] Label number of the rubber-table data set to define. If the label number of an existing rubbertable data set is defined, then the previous definition is overwritten. thetai The temperature corresponding to the material properties entered in this data input line. alphai The coefficient of thermal expansion.
[0.0]
mui lambdai kappai The material properties.
[0.0] [0.0] [0.0]
fittting-curvei [0] If fittting-curvei is zero, no fitting curve is used. If fittting-curvei is nonzero, curve-fitting data from the CURVE-FITTING command is used to compute the material properties, and mui , lambdai are ignored. rubber-viscoelastici [0] If rubber-viscoelastici is zero, no viscoelastic effects are included. If rubber-viscoelastici is non-zero, viscoelastic effects are included, using the data set from the corresponding RUBBER-VISCOELASTIC command. rubber-mullinsi If rubber-mullinsi is zero, no Mullins effects are included. If rubber-mullinsi is non-zero, Mullins effects are included, using the data set from the corresponding RUBBER-MULLINS command.
[0]
[0] rubber-orthotropici If rubber-orthotropici is zero, no orthotropic effects are included. If rubber-orthotropici is non-zero, orthotropic effects are included, using the data set from the corresponding RUBBER-ORTHOTROPIC command.
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RUBBER-TABLE ARRUDA-BOYCE
Chap. 7 Model definition
Auxiliary commands LIST RUBBER-TABLE DELETE RUBBER-TABLE
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RUBBER-TABLE HYPER-FOAM
RUBBER-TABLE HYPER-FOAM
Sec. 7.1 Material models
NAME
thetai alphai mu1i alpha1i beta1i mu2i alpha2i beta2i mu3i alpha3i beta3i mu4i alpha4i beta4i mu5i alpha5i beta5i mu6i alpha6i beta6i mu7i alpha7i beta7i mu8i alpha8i beta8i mu9i alpha9i beta9i fitting-curvei rubber-viscoelastici rubber-mullinsi rubber-orthotropici Defines a rubber-table data set of type hyper-foam. This data set can be used to describe the temperature dependence of the hyper-foam material constants in the MATERIAL HYPERFOAM command. NAME [(current highest rubber-table label number) + 1] Label number of the rubber-table data set to define. If the label number of an existing rubbertable data set is defined, then the previous definition is overwritten. thetai The temperature corresponding to the material properties entered in this data input line. alphai The coefficient of thermal expansion.
[0.0]
mu1i ... betai The material properties.
[0.0]
fittting-curvei [0] If fittting-curvei is zero, no fitting curve is used. If fittting-curvei is nonzero, curve-fitting data from the CURVE-FITTING command is used to compute the material properties, and mu1i to alpha9i are ignored. rubber-viscoelastici [0] If rubber-viscoelastici is zero, no viscoelastic effects are included. If rubber-viscoelastici is non-zero, viscoelastic effects are included, using the data set from the corresponding RUBBER-VISCOELASTIC command. rubber-mullinsi If rubber-mullinsi is zero, no Mullins effects are included. If rubber-mullinsi is non-zero, Mullins effects are included, using the data set from the corresponding RUBBER-MULLINS command.
[0]
rubber-orthotropici [0] If rubber-orthotropici is zero, no orthotropic effects are included. If rubber-orthotropici is non-zero, orthotropic effects are included, using the data set from the corresponding RUBBER-ORTHOTROPIC command.
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RUBBER-TABLE HYPER-FOAM
Chap. 7 Model definition
Auxiliary commands LIST RUBBER-TABLE DELETE RUBBER-TABLE
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RUBBER-TABLE SUSSMAN-BATHE
Sec. 7.1 Material models
RUBBER-TABLE SUSSMAN-BATHE NAME thetai alphai sscurvei sstypei relerrori kappai rubber-viscoelastici rubber-mullinsi rubber-orthotropici Defines a rubber-table data set of type Sussman-Bathe. This data set can be used to describe the temperature dependence of the Sussman-Bathe material model in the MATERIAL SUSSMAN-BATHE command. NAME [(current highest rubber-table label number) + 1] Label number of the rubber-table data set to define. If the label number of an existing rubbertable data set is defined, then the previous definition is overwritten. thetai The temperature corresponding to the material properties entered in this data input line. alphai The coefficient of thermal expansion.
[0.0]
sscurvei The uniaxial tension/compression stress-strain curve for this temperature, defined by the SSCURVE command. sstypei [ENGINEERING] The interpretation of the stress-strain data. {ENGINEERING/TRUE/STRETCH} ENGINEERING
engineering strains, engineering stresses
TRUE
true strains, true stresses
STRETCH
stretches, engineering stresses
relerrori The relative error, used to determine the number of splines for this temperature. relerrori cannot equal 0.0.
[0.01]
kappai [0.0] The bulk modulus, used for 3-D, plane strain and axisymmetric elements. If kappai = 0.0, then the AUI computes the bulk modulus based on a Poisson’s ratio of 0.499. rubber-viscoelastici [0] If rubber-viscoelastici is zero, no viscoelastic effects are included. If rubber-viscoelastici is non-zero, viscoelastic effects are included, using the data set from the corresponding RUBBER-VISCOELASTIC command. ADINA R & D, Inc.
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rubber-mullinsi If rubber-mullinsi is zero, no Mullins effects are included. If rubber-mullinsi is non-zero, Mullins effects are included, using the data set from the corresponding RUBBER-MULLINS command.
[0]
rubber-orthotropici [0] If rubber-orthotropici is zero, no orthotropic effects are included. If rubber-orthotropici is non-zero, orthotropic effects are included, using the data set from the corresponding RUBBER-ORTHOTROPIC command.
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RUBBER-TABLE TRS
Sec. 7.1 Material models
RUBBER-TABLE TRS NAME thetai alphai Defines a rubber-table data set of type TRS. This data set can be used to specify the coefficients of thermal expansion for the MATERIAL MOONEY-RIVLIN, MATERIAL OGDEN, MATERIAL ARRUDA-BOYCE and MATERIAL HYPER-FOAM materials, when the TRS temperature dependence option is used. NAME [(current highest rubber-table label number) + 1] Label number of the rubber-table data set to define. If the label number of an existing rubbertable data set is defined, then the previous definition is overwritten. thetai The temperature corresponding to the material properties entered in this data input line. alphai The coefficient of thermal expansion.
[0.0]
Auxiliary commands LIST RUBBER-TABLE DELETE RUBBER-TABLE
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RUBBER-MULLINS OGDEN-ROXBURGH
Sec. 7.1 Material models
RUBBER-MULLINS OGDEN-ROXBURGH
NAME R M GENERATION_FACTOR
Defines a data set of type rubber-Mullins, subtype Ogden-Roxburgh. This data set can be referenced by the MATERIAL MOONEY-RIVLIN, MATERIAL OGDEN, MATERIAL ARRUDA-BOYCE and MATERIAL HYPER-FOAM commands to add the Mullins effect to any of these materials. NAME [current highest rubber-mullins label number + 1] Label number of the rubber-Mullins data set to define. If the label number of an existing rubber-Mullins data set is defined, then the previous definition is overwritten. R [0.0] M [0.0] The material constants of the Ogden-Roxburgh model for the Mullins effect, see the ADINA Theory and Modeling Guide. GENERATION_FACTOR [0.0] The fraction of energy dissipated by the Mullins effect model that is considered as heat generation. For example, if GENERATION_FACTOR = 1.0, then all energy dissipated by the Mullins effect model is considered as heat generation. Heat generation can cause heating in a TMC (thermo-mechanical coupling) analysis. Auxiliary commands: LIST RUBBER-MULLINS DELETE RUBBER-MULLINS
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RUBBER-MULLINS OGDEN-ROXBURGH
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Sec. 7.1 Material models
RUBBER-VISCOELASTIC HOLZAPFEL
RUBBER-VISCOELASTIC HOLZAPFEL
NAME SHIFT C1 C2
betai taui generation_factori usagei Defines a data set of type rubber-viscoelastic, subtype Holzapfel. This data set can be referenced by the MATERIAL MOONEY-RIVLIN, MATERIAL OGDEN, MATERIAL ARRUDA-BOYCE and MATERIAL HYPER-FOAM commands to add the viscoelastic effect to any of these materials. See the ADINA Theory and Modeling Guide for the meanings of the material parameters. NAME [current highest rubber-viscoelastic label number + 1] Label number of the rubber-viscoelastic data set to define. If the label number of an existing rubber-viscoelastic data set is defined, then the previous definition is overwritten. SHIFT [NONE] Specifies the time-temperature superposition shift law. {NONE/WLF/ARRHENIUS} NONE
Time-temperature superposition is not used.
WLF
The WLF (Williams-Landel-Ferry) shift function is used for the timetemperature superposition.
ARRHENIUS
The Arrhenius shift function is used for the time-temperature superposition.
C1 C2 The material constants for the WLF or Arrhenius shift functions.
[0.0] [0.0]
betai Beta for chain (i) of the viscoelastic model.
[0.0]
taui Tau for chain (i) of the viscoelastic model. Tau must be greater than 0.
[0.0]
generation_factori [0.0] The heat generation factor (fraction of dissipation energy convered into heat generation). If generation_factori = 0, the dissipation is not calculated and there is no heat generation. usagei [DEVIATORIC] The usage of the chain. {COMBINED/DEVIATORIC/VOLUMETRIC/AORTHO/BORTHO/ CORTHO}
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RUBBER-VISCOELASTIC HOLZAPFEL
COMBINED
The chain is based on the total strain energy.
DEVIATORIC
The chain is based on the deviatoric strain energy.
VOLUMETRIC
The chain is based on the volumetric strain energy.
AORTHO
The chain is based on the A direction orthotropic strain energy.
BORTHO
The chain is based on the B direction orthotropic strain energy.
CORTHO
The chain is based on the C direction orthotropic strain energy (not supported in this version)
Auxiliary commands LIST RUBBER-VISCOELASTIC DELETE RUBBER-VISCOELASTIC
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RUBBER-ORTHOTROPIC HOLZAPFEL
RUBBER-ORTHOTROPIC HOLZAPFEL
Sec. 7.1 Material models
NAME BETAA BETAB K1 K2 COMPRESSION
Defines a data set of type rubber-orthotropic, subtype Holzapfel. This data set can be referenced by the MATERIAL MOONEY-RIVLIN, MATERIAL OGDEN, MATERIAL ARRUDA-BOYCE and MATERIAL HYPER-FOAM commands to add the orthotropic effect to any of these materials. See the ADINA Theory and Modeling Guide for the meanings of the material parameters. NAME [current highest rubber-orthotropic label number + 1] Label number of the rubber-orthotropic data set to define. If the label number of an existing rubber-orthotropic data set is defined, then the previous definition is overwritten. BETAA The angle (in degrees) between the material a axis and the fiber A direction na.
[0.0]
BETAB [0.0] The angle (in degrees) between the material b axis and the fiber B direction nb. This parameter is not used if DIRECTION = AHOOP. K1 K1 The material constants of the orthotropic strain energy function.
[0.0] [0.0]
COMPRESSION [NO] If COMPRESSION = NO, then material fibers in compression do not contribute to the orthotropic strain energy (no strain energy in compression). If COMPRESSION = YES, then material fibers in compression contribute to the orthotropic strain energy. DIRECTION [AB] If DIRECTION = AB, then the fiber directions are na and nb. If DIRECTION = AHOOP, then the fiber directions are na and x (the hoop direction). AHOOP is allowed only for axisymmetric elements. Auxiliary commands LIST RUBBER-ORTHOTROPIC DELETE RUBBER-ORTHOTROPIC
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COEFFICIENTS-TABLE
COEFFICIENTS-TABLE
Sec. 7.1 Material models
NAME
sigmai a0i a1i a2i a3i a4i a5i a6i a7i Defines an effective-stress v creep-coefficients table, which can be referenced by command CREEP-COEFFICIENTS MULTILINEAR to define the temperature and/or effective-stress dependence of creep material models with variable coefficients, see commands MATERIAL CREEP-VARIABLE, MATERIAL PLASTIC-CREEP-VARIABLE, MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLE. See the Theory and Modeling Guide for further details. NAME [(current highest COEFFICIENTS-TABLE label number) + 1] Label number of the stress v creep-coefficient table to be defined. sigmai Stress at data point “i”. a0i Creep law coefficient a0 at stress sigmai. a1i Creep law coefficient a1 at stress sigmai. a2i Creep law coefficient a2 at stress sigmai. a3i Creep law coefficient a3 at stress sigmai. a4i Creep law coefficient a4 at stress sigmai. a5i Creep law coefficient a5 at stress sigmai. a6i Creep law coefficient a6 at stress sigmai. a7i Creep law coefficient a7 at stress sigmai. Auxiliary commands LIST COEFFICIENTS-TABLE DELETE COEFFICIENTS-TABLE
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CREEP-COEFFICIENTS LUBBY2
CREEP-COEFFICIENTS LUBBY2
NAME
thetai a0i a1i a2i a3i a4i a5i Defines the dependency of creep law coefficients on temperature. This creep coefficient function is referenced by the NCOEF parameter in the commands: MATERIAL CREEP-VARIABLE, MATERIAL PLASTIC-CREEP-VARIABLE, MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLE if CREEP-LAW=LUBBY2 is specified in those commands. NAME
[(current highest creep-coefficient function label number) + 1] Label number of the creep-coefficient function to be defined.
thetai Temperature at data point "i". a0i Creep law coefficient a0 at "thetai".
[0.0]
a1i Creep law coefficient a1 at "thetai".
[0.0]
a2i Creep law coefficient a2 at "thetai".
[0.0]
a3i Creep law coefficient a3 at "thetai". {≠ 0.0}
[1.21e8]
a4i Creep law coefficient a4 at "thetai". {≠ 0.0}
[188000]
a5i Creep law coefficient a5 at "thetai". {≠ 0.0}
[251000]
Auxiliary commands: LIST CREEP-COEFFICIENTS LUBBY2 DELETE CREEP-COEFFICIENTS LUBBY2
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CREEP-COEFFICIENTS MULTILINEAR
CREEP-COEFFICIENTS MULTILINEAR
Sec. 7.1 Material models
NAME
thetai ccurvei Defines the temperature and/or effective-stress dependence of creep material models with variable coefficients, see commands MATERIAL CREEP-VARIABLE, MATERIAL PLASTIC-CREEP-VARIABLE, MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLE, and COEFFICIENTS-TABLE. NAME
[(current highest creep-coefficient function label number) + 1] Label number of the creep-coefficient function to be defined.
thetai Temperature at data point “i”. ccurvei Stress vs. creep-coefficient table at temperature thetai, see command COEFFICIENTS-TABLE. Auxiliary commands LISTCREEP-COEFFICIENTS MULTILINEAR DELETE CREEP-COEFFICIENTS MULTILINEAR
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CREEP-COEFFICIENTS TEMPERATURE-ONLY
CREEP-COEFFICIENTS TEMPERATURE-ONLY
NAME
thetai a0i a1i a2i a3i a4i a5i a6i a7i Defines the dependency of creep law coefficients on temperature. This creep coefficient function is referenced by the NCOEF parameter in the commands: MATERIAL CREEP-VARIABLE, MATERIAL PLASTIC-CREEP-VARIABLE, MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLE if CREEP-LAW=LAW3 is specified in those commands. NAME
[(current highest creep-coefficient function label number) + 1] Label number of the creep-coefficient function to be defined.
thetai Temperature at data point “i”. a0i Creep law coefficient a0 at "thetai". a1i Creep law coefficient a1 at "thetai". a2i Creep law coefficient a2 at "thetai". a3i Creep law coefficient a3 at "thetai". a4i Creep law coefficient a4 at "thetai". a5i Creep law coefficient a5 at "thetai". a6i Creep law coefficient a6 at "thetai". a7i Creep law coefficient a7 at "thetai".
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CREEP-COEFFICIENTS TEMPERATURE-ONLY
Sec. 7.1 Material models
Auxiliary commands: LIST CREEP-COEFFICIENTS TEMPERATURE-ONLY DELETE CREEP-COEFFICIENTS TEMPERATURE-ONLY
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CREEP-COEFFICIENTS USER-SUPPLIED
CREEP-COEFFICIENTS USER-SUPPLIED
NAME
Defines the temperature and/or effective-stress dependence of creep material models with variable coefficients, see commands: MATERIAL CREEP-VARIABLE, MATERIAL PLASTIC-CREEP-VARIABLE, MATERIAL MULTILINEAR-PLASTIC-CREEP-VARIABLE. The dependence is defined via a user-supplied function, see the Theory and Modeling Guide for further details. NAME
[(current highest creep-coefficient function label number) + 1] Label number of the creep-coefficient function to be defined. Auxiliary commands LIST CREEP-COEFFICIENTS USER-SUPPLIED DELETE CREEP-COEFFICIENTS USER-SUPPLIED
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CURVATURE-MOMENT
CURVATURE-MOMENT
Sec. 7.1 Material models
NAME
curvaturei momenti Defines a curvature v moment curve which can be referenced by the command MOMENT-CURVATURE-FORCE . The curve is defined as piecewise linear through the data points (curvaturei, momenti). NAME
[(current highest CURVATURE-MOMENT label number) + 1] Label number of the curvature v moment curve to be defined. curvaturei Curvature at data point “i”. momenti Moment at curvaturei. Auxiliary commands LIST CURVATURE-MOMENT DELETE CURVATURE-MOMENT
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FTABLE
Chap. 7 Model definition
FTABLE
NAME F0 OPTION WEIGHTING W1 W2 TAU
modulusi
decayi
(OPTION=DIRECT)
modulusi
timei
(OPTION=TEST)
Defines a series of modulus and decay coefficients to represent a modulus relaxation function used by command MATERIAL VISCOELASTIC. F0 is 0th term of modulus and the corresponding decay coefficient is zero. If OPTION=TEST, input data are interpreted as the modulus response vs. time. The program will convert time history curve into a Prony-Dirichlet series representation. NAME [(current highest FTABLE label number) + 1] Label number of the modulus-decay function to be defined. If the label number of an existing function is given, existing function definition is overwritten. F0 The 0th term of modulus representation. Used only when OPTION=DIRECT OPTION
[0.0] [DIRECT]
DIRECT
Table data are input in Prony series
TEST
Table data are input in pairs of modulus vs. time
WEIGHTING Specifies if least squares fitting scheme is used to smooth moduli terms. Used only if OPTION=TEST. {NO/YES}
[NO]
W1 Weighting parameter 1. Active only if WEIGHTING=YES.
[0.0]
W2 Weighting parameter 2. Active only if WEIGHTING=YES.
[0.0]
TAU Relaxation parameter for calculating decayi.
[0.0]
modulusi Modulus at term "i", or modulus corresponding to time "i"
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FTABLE
Sec. 7.1 Material models
decayi Decay coefficient at term "i" timei Time corresponding to modulusi. Auxiliary commands LIST FTABLE DELETE FTABLE
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FORCE-STRAIN
Chap. 7 Model definition
FORCE-STRAIN straini
NAME
forcei
Defines a force-strain curve which can be referenced by the command RIGIDITY-MOMENT-CURVATURE. The curve is defined as piecewise linear through the data points (straini, forcei). NAME [(current highest FORCE-STRAIN label number) + 1] Label number of the force-strain curve to be defined. straini Axial strain at data point “i”. forcei Axial force at straini. Note:
The force is assumed to be zero when the effective plastic axial strain exceeds the maximum effective plastic axial strain on the yield curve (force vs. plastic-strain) obtained from the above force v total-strain curve.
Auxiliary commands LIST FORCE-STRAIN DELETE FORCE-STRAIN
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IRRADIATION_CREEP-TABLE
Sec. 7.1 Material models
IRRADIATION_CREEP-TABLE NAME temperaturei neutron-tablei Defines the dependency of irradiation creep variables on temperature and fast neutron fluence. NAME
[(current highest irradiation_creep-table label number) + 1] Label number of the irradiation creep table to be defined.
temperaturei Temperature at data point “i”. neutron-tablei Neutron fluence table at temperature “thetai”. Auxiliary commands LIST IRRADIATION_CREEP-TABLE DELETE IRRADIATION_CREEP-TABLE
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IRRADIATION_CREEP-TABLE
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MOMENT-CURVATURE-FORCE
MOMENT-CURVATURE-FORCE
Sec. 7.1 Material models
NAME
forcei curvature-momenti Defines a moment-curvature curve which can be referenced by the command RIGIDITY-MOMENT-CURVATURE . NAME
[(current highest MOMENT-CURVATURE-FORCE label number) + 1] Label number of the curvature v moment curve to be defined.
forcei Axial force at data point “i”. curvature-momenti Label number of the curvature-moment at forcei. (See CURVATURE-MOMENT ). Note:
For plasticity models, the curves defined by the input data are transformed to yield curves which are linearly interpolated to obtain the yield curve corresponding to the current axial force.
Note: The bending moment is assumed to be zero when the effective plastic curvature exceeds the maximum effective plastic curvature reached by the interpolated yield curves. Auxiliary commands LIST MOMENT-CURVATURE-FORCE DELETE MOMENT-CURVATURE-FORCE
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MOMENT-TWIST-FORCE
Chap. 7 Model definition
MOMENT-TWIST-FORCE NAME forcei twist-momenti Defines a moment-twist curve which can be referenced by the command RIGIDITY-MOMENT-CURVATURE. NAME
[(current highest MOMENT-TWIST-FORCE label number) + 1] Label number of the moment-twist curve to be defined. forcei Axial force at data point “i”. twist-momenti Label number of the twist-moment at forcei. (See TWIST-MOMENT ). Note:
For plasticity models, the curves defined by the input data are transformed to yield curves which are linearly interpolated to obtain the yield curve corresponding to the current axial force.
Note:
The bending moment is assumed to be zero when the effective plastic twist exceeds the maximum effective plastic twist reached by the interpolated yield curves.
Auxiliary commands LIST MOMENT-TWIST-FORCE DELETE MOMENT-TWIST-FORCE
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PORE-FLUID-PROPERTY
PORE-FLUID-PROPERTY
Sec. 7.1 Material models
MATERIAL PX PY PZ COMPRESS FLUIDBULK POROSITY
Defines pore fluid properties. MATERIAL Label number of the material (must be existing). PX PY PZ Permeability in X, Y and Z directions. Must be positive.
[1.0E-9] [1.0E-9] [1.0E-9]
COMPRESS Indicates whether the fluid is compressible. {NO/YES}
[NO]
FLUIDBULK Bulk modulus of the pore fluid. Used only when COMPRESS = YES. {>0.0}
[2.1E9]
POROSITY [0.75] Porosity of the porous solid material. Used only when COMPRESS = YES. {>0.0}
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NEUTRON-DOSE
Chap. 7 Model definition
NEUTRON-DOSE
NAME
timei neutron-fluencei Defines a neutron fluence as a function of time. The command defines a time dependent total neutron fluence for the irradiation creep material model. The time range input should cover the entire time interval required in the solution. NAME [(current highest neutron dose label number) + 1] Label number of neutron dose to be defined. If the label number of an existing neutron dose is given, then the previous definition is overwritten. timei Time at data point “i”. neutron-fluencei Neutron fluence at timei.
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NEUTRON-TABLE
NEUTRON-TABLE
Sec. 7.1 Material models
NAME
neutron-fluencei irradiation-straini Ei alphai Defines a neutron fluence table which can be referenced by an irradiation creep table. NAME [(current highest NEUTRON-TABLE label number) + 1] Label number of the neutron fluence table to be defined. neutron-fluencei Neutron-fluence at data point “i”. irradiation-straini Irradiation-strain at “neutron-fluencei ”. Ei Young’s modulus at “neutron-fluencei ”. alphai Mean coefficient of thermal expansion at “neutron-fluencei ”. Auxiliary commands: LIST NEUTRON-TABLE FIRST LAST DELETE NEUTRON-TABLE FIRST LAST
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PROPERTY NONLINEAR-C
Chap. 7 Model definition
PROPERTY NONLINEAR-C
NAME XC XN
Defines a nonlinear relationship between the damping force and the relative velocity of the nonlinear spring element. The relationship is of the form, úN FD = C ⋅ U
NAME [(current highest property label number) + 1] Label number of the property to be defined. XC Constant “C” in the definition of function FD, see above. XN Exponent “N” in the definition of function FD, see above. Auxiliary Commands LIST PROPERTY NONLINEAR-C DELETE PROPERTY NONLINEAR-C
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PROPERTY NONLINEAR-K
PROPERTY NONLINEAR-K
Sec. 7.1 Material models
NAME RUPTURE
relative-displacementi forcei Defines a nonlinear relationship between relative-displacement and force from which the stiffness and force of a nonlinear spring element are obtained. NAME [(current highest property label number) + 1] Label number of the property to be defined. RUPTURE [NO] Indicates whether a spring ruptures if the relative displacement exceeds the limiting values of the input relative-displacements. If YES then the force is assumed zero beyond the minimum, maximum values of the relative-displacement. {YES/NO} relative-displacementi Relative displacement (between spring nodes) at data point “i”. forcei Spring force at relative-displacementi. Auxiliary Commands LIST PROPERTY NONLINEAR-K DELETE PROPERTY NONLINEAR-K
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PROPERTY NONLINEAR-M
Chap. 7 Model definition
PROPERTY NONLINEAR-M
NAME
timei massi Defines the time-dependent total mass for nonlinear spring elements. The input time range should cover that of the entire analysis. NAME [(current highest property label number) + 1] Label number of the property to be defined. timei Time at data point “i”. massi Spring mass at timei. Auxiliary Commands LIST PROPERTY NONLINEAR-M DELETE PROPERTY NONLINEAR-M
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PROPERTYSET
Sec. 7.1 Material models
PROPERTYSET NAME K M C S NONLINEAR NK NM NC Defines stiffness, mass, damping, and stress transformation properties for SPRING elements in a set termed a “propertyset”. See the Theory and Modeling Guide for further details on the resulting spring element stiffness, mass, damping, and stress transformation matrices evaluated from these constants. NAME [(current highest property label number) + 1] Label number of the propertyset to be defined. K Linear spring element stiffness. {> 0.0} M [0.0] Total mass of linear spring element. The corresponding mass matrix is lumped or consistent according to the MASS-MATRIX command. C Linear spring element damping coefficient.
[0.0]
S [0.0] Stress transformation constant for a linear spring element. This constant is used to form a stress transformation matrix, which when multiplied by the element nodal displacements gives a stress value. NONLINEAR Indicates whether a nonlinear spring propertyset is to be defined. {YES/NO}
[NO]
NK Label number of a nonlinear stiffness property (see PROPERTY NONLINEAR-K ). For NONLINEAR = YES a value must be supplied.
[0]
NM Label number of a nonlinear mass property (see PROPERTY NONLINEAR-M ).
[0]
NC Label number of a nonlinear damping property (see PROPERTY NONLINEAR-C ).
[0]
Note:
If skew degree-of-freedom systems are applied at the nodes of a spring element then ADINA will make any necessary transformation to account for the skew system directions.
Note:
For a grounded spring, with one nodal degree of freedom specified, the total mass
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PROPERTYSET
Chap. 7 Model definition
of the element is lumped at the spring node degree of freedom. Note:
Stress calculations are carried out for spring elements only when RESULTS = STRESSES is set by the EGROUP SPRING command.
Auxiliary commands LIST PROPERTYSET DELETE PROPERTYSET
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RIGIDITY-MOMENT-CURVATURE NONLINEAR-ELASTIC
Sec. 7.1 Material models
RIGIDITY-MOMENT-CURVATURE NONLINEAR-ELASTIC NAME RIGIDITY-AXIAL MOMENT-R MOMENT-S MOMENT-T DENSITY MASS-AREA MASS-RINERTIA MASS-SINERTIA MASS-TINERTIA ALPHA Defines a nonlinear-elastic rigidity for BEAM elements. NAME
[(current highest RIGIDITY-MOMENT-CURVATURE label number) + 1] Label number of the rigidity to be defined. RIGIDITY-AXIAL Axial rigidity. MOMENT-R [0] Label number of a curve defined by MOMENT-TWIST-FORCE giving the torsional moment of inertia as a nonlinear elastic function of the twist per unit length. MOMENT-S [0] Label number of a curve defined by MOMENT-CURVATURE-FORCE giving the bending moment of inertia about the s-axis of a beam element as a nonlinear elastic function of the corresponding curvature. MOMENT-T [0] Label number of a curve defined by MOMENT-CURVATURE-FORCE giving the bending moment of inertia about the t-axis of a beam element as a nonlinear elastic function of the corresponding curvature. DENSITY Mass density (in units of mass/length3 ). Used in the calculation of the mass matrix.
[0.0]
MASS-AREA Cross-sectional area (in units of length2 ). Used only in the calculation of the mass matrix. MASS-RINERTIA Second moment of area for torsion about the r-axis of a beam element, including warping effects (in units of length4 ). Used only in the calculation of the mass matrix. MASS-SINERTIA Second moment of area for bending about the s-axis of a beam element (in units of length4 ). Used only in the calculation of the mass matrix.
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RIGIDITY-MOMENT-CURVATURE NONLINEAR-ELASTIC
MASS-TINERTIA Second moment of area for bending about the t-axis of a beam element (in units of length4 ). Used only in the calculation of the mass matrix. ALPHA Thermal expansion coefficient. Auxiliary commands LIST RIGIDITY-MOMENT-CURVATURE DELETE RIGIDITY-MOMENT-CURVATURE
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RIGIDITY-MOMENT-CURVATURE PLASTIC-MULTILINEAR
Sec. 7.1 Material models
RIGIDITY-MOMENT-CURVATURE PLASTIC-MULTILINEAR NAME HARDENING BETA FORCEAXIAL MOMENT-R MOMENT-S MOMENT-T AXIAL-CYCLIC-FACTOR BENDING-CYCLIC-FACTOR TORSION-CYCLIC-FACTOR DENSITY MASS-AREA MASS-RINERTIA MASS-SINERTIA MASS-TINERTIA ACURVE-TYPE TCURVE-TYPE BCURVE-TYPE ALPHA Defines a plastic-multilinear rigidity for BEAM elements. NAME
[(current highest RIGIDITY-MOMENT-CURVATURE label number) + 1] Label number of the rigidity to be defined. HARDENING Selects the type of strain hardening rule: ISOTROPIC
Linear isotropic strain hardening.
KINEMATIC
Linear kinematic strain hardening.
MIXED
Linear mixed strain hardening.
[ISOTROPIC]
BETA Factor used in mixed hardening to determine the amounts of kinematic and isotropic hardening. BETA = 0 results in purely kinematic hardening while BETA = 1 results in purely isotropic hardening. {0.0 < BETA < 1.0} FORCE-AXIAL [0] Label number of a curve defined by FORCE-STRAIN giving the axial force as a multilinear plastic function of the axial strain. MOMENT-R [0] Label number of a curve defined by MOMENT-TWIST-FORCE giving the torsional moment of inertia as a multilinear function of the twist per unit length. MOMENT-S [0] Label number of a curve defined by MOMENT-CURVATURE-FORCE giving the bending moment of inertia about the s-axis of a beam element as a multilinear function of the corresponding curvature.
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RIGIDITY-MOMENT-CURVATURE PLASTIC-MULTILINEAR
MOMENT-T [0] Label number of a curve defined by MOMENT-CURVATURE-FORCE giving the bending moment of inertia about the t-axis of a beam element as a multilinear function of the corresponding curvature. AXIAL-CYCLIC-FACTOR [1.0] Ratio of the initial elastic axial rigidity and the elastic axial rigitity after first yield. {≥ 1.0} BENDING-CYCLIC-FACTOR [1.0] Ratio of the initial elastic bending rigidity and the elastic bending rigidity after first yield. {≥ 1.0} TORSIONAL-CYCLIC-FACTOR [1.0] Ratio of the initial elastic torsional rigidity and the elastic torsional rigidity after first yield. {≥ 1.0} DENSITY Mass density (in units of mass/length3 ). Used in the calculation of the mass matrix.
[0.0]
MASS-AREA Cross-sectional area (in units of length2 ). Used only in the calculation of the mass matrix. MASS-RINERTIA Second moment of area for torsion about the r-axis of a beam element, including warping effects (in units of length4 ). Used only in the calculation of the mass matrix. MASS-SINERTIA Second moment of area for bending about the s-axis of a beam element (in units of length4 ). Used only in the calculation of the mass matrix. MASS-TINERTIA Second moment of area for bending about the t-axis of a beam element (in units of length4 ). Used only in the calculation of the mass matrix. Note:
For the curves input via FORCE-AXIAL, MOMENT-R, MOMENT-S, and MOMENT-T, the first data point corresponds to the yield point, all data points must have positive coordinates, and the slope (hardening modulus) of any curve segment cannot be greater than the elastic modulus of the curve.
Note:
Softening is not modeled.
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RIGIDITY-MOMENT-CURVATURE PLASTIC-MULTILINEAR
Sec. 7.1 Material models
ACURVE-TYPE Indicates whether the axial force-strain curve is symmetric or not. {SYMMETRIC/UNSYMMETRIC}
[SYMMETRIC]
TCURVE-TYPE [SYMMETRIC] Indicates whether the torsional moment-twist curves are symmetric or not. {SYMMETRIC/UNSYMMETRIC} BCURVE-TYPE [SYMMETRIC] Indicates whether the bending moment-curvature curves are symmetric or not. {SYMMETRIC/UNSYMMETRIC} ALPHA Thermal expansion coefficient. Auxiliary commands LIST RIGIDITY-MOMENT-CURVATURE DELETE RIGIDITY-MOMENT-CURVATURE
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RUPTURE MULTILINEAR
Chap. 7 Model definition
RUPTURE MULTILINEAR
NAME COMPRESS TRIAXIALITY
thetai rupture-curvei Defines a rupture criterion in terms of a multilinear relationship between temperature and creep rupture strain v. effective stress curves - see the Theory and Modeling Guide for details. The rupture criterion may be referenced by any of the creep material models, e.g. see command MATERIAL CREEP. NAME
[(current highest rupture criterion label number) + 1] Label number of the rupture criterion to be defined. COMPRESS Indicates whether creep rupture can occure in compression. {YES/NO}
[YES]
TRIAXIALITY Indicates whether triaxiality factor is used. {YES/NO}
[YES]
thetai Temperature at data point “i”. rupture-curvei Creep rupture-strain vs. effective stress curve at temperature thetai, defined by command RUPTURE-CURVE. Auxiliary commands LIST RUPTURE MULTILINEAR DELETE RUPTURE MULTILINEAR
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RUPTURE THREE-PARAMETER
RUPTURE THREE-PARAMETER
Sec. 7.1 Material models
NAME ALPHA BETA SIGMA
Defines a rupture criterion in terms of the first three stress invariants -- see the Theory and Modeling Guide for details. The rupture criterion may be referenced by any of the creep material models, e.g. see command MATERIAL CREEP. NAME
[(current highest rupture criterion label number) + 1] Label number of the rupture criterion to be defined. ALPHA First coefficient of the three-parameter rupture law.
[0.0]
BETA Second coefficient of the three-parameter rupture law.
[0.0]
SIGMA Effective stress at rupture for the three-parameter rupture law.
[0.0]
Auxiliary commands LIST RUPTURE THREE-PARAMETER DELETE RUPTURE THREE-PARAMETER
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RUPTURE-CURVE
Chap. 7 Model definition
RUPTURE-CURVE straini
NAME
stressi
Defines a creep rupture strain v. effective stress curve which may be referenced by command RUPTURE to define a rupture criterion for a creep material model. See the Theory and Modeling Guide for further details. NAME
[(current highest RUPTURE-CURVE label number) + 1] Label number of the creep rupture strain vs. effective stress curve to be defined.
straini Creep rupture strain at data point “i”. stress i Stress at creep rupture strain straini. Auxiliary commands LIST RUPTURE-CURVE DELETE RUPTURE-CURVE
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SCURVE
SCURVE
Sec. 7.1 Material models
NAME
straini stressi Defines a stress-strain curve which can be referenced by a material model. The stress-strain curve is defined as piecewise linear through the data points (straini, stressi). NAME [(current highest SCURVE label number) + 1] Label number of the stress-strain curve to be defined. straini Strain at data point “i”. stressi Stress at strain “straini”. Auxiliary commands LIST SCURVE DELETE SCURVE
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SSCURVE
SSCURVE
NAME CONSTANT-NU NU
straini stressi strain2i Defines a stress-strain curve which can be referenced by a material model. The stress-strain curve is defined as piecewise linear through the data points (straini , stressi ). This command is currrenlty used only for hyperelastic curve fitting. NAME [(current highest SSCURVE label number) + 1] Label number of the stress-strain curve to be defined. If the label number of an existing curve is given, then the previous curve definition is overwritten. CONSTANT-NU [NO] Flag indicate constant nu is used or not {YES/NO} This parameter is only used when this curve is referenced by the hyper-foam material model. NU Specifies the Poissons ratio when CONSTANT-NU=YES. This parameter is only used with the hyper-foam material model. Note that NU must be in one of the ranges: -1 < NU < 0.0,
0.0 < NU < 0.5
straini Strain at data point "i". stress i Stress at data point "i". strain2i Lateral strain at data point "i". strain2i is only used if CONSTANT-NU=NO is specified and this curve is used for a hyperfoam material model. Auxiliary commands LIST SSCURVE FIRST LAST DELETE SSCURVE FIRST LAST
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SSCURVE
Sec. 7.1 Material models
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LCURVE
Chap. 7 Model definition
LCURVE
NAME
closurei pressurei Defines a loading-unloading curve which can be referenced by the gasket material model. The loading-unloading curve is defined as piecewise linear through the data points (pressurei , closurei ). NAME [(current highest LCURVE label number) + 1 ] Label number of the loading-unloading curve to be defined. If the label number of an existing curve is given, then the previous curve definition is overwritten. closurei Closure at data point "i". pressurei Pressure at data point "i". Note: First point must have pressure =0. Auxiliary commands LIST LCURVE DELETELCURVE
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STRAINRATE-FIT
Chap. 7 Model definition
STRAINRATE-FIT
NAME
strainratei scurvei Defines a strainrate-fit. The strainrate-fit can be specified in the MATERIAL PLASTICBILINEAR and MATERIAL PLASTIC-MULTILINEAR commands, for the curve fitting of strainrate material parameters. NAME [(current highest strainrate-fit label number) + 1] Label number of the strain-rate fit to be defined. If the label number of an existing strainrate-fit is given, then the previous strainrate-fit definition is overwritten. strainratei The strainrate associated with scurvei. The strainrate must be greater than 0.0. scurvei The stress-strain curve, specified by the SCURVE command, for strainratei.
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TWIST-MOMENT
TWIST-MOMENT
Sec. 7.2 Cross-sections / layers
NAME
twisti momenti Defines a twist v moment curve which can be referenced by the MOMENT-TWIST-FORCE command. The curve is defined as piecewise linear through the data points (twisti, momenti). NAME [(current highest TWIST-MOMENT label number) + 1] Label number of the twist v moment curve to be defined. twisti Twist per unit length at data point “i”. momenti Moment at twisti. Auxiliary commands LIST TWIST-MOMENT DELETE TWIST-MOMENT
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CROSS-SECTION BOX
Chap. 7 Model definition
CROSS-SECTION BOX
NAME WIDTH HEIGHT THICK1 THICK2 SC TC TORFAC SSHEARF TSHEARF
CROSS-SECTION BOX defines a box cross-section which can be used to describe the crosssectional characteristics of an elastic Hermitian BEAM element. THICK1
THICK1
THICK2
X'
HEIGHT
Y'
centroid
THICK2 WIDTH
NAME [(current highest cross-section label number) + 1] Label number of the cross-section to be defined. WIDTH HEIGHT THICK1 THICK2 The dimensions of the box cross-section. See Figure.
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CROSS-SECTION BOX
Sec. 7.2 Cross-sections / layers
SC [0.0] TC [0.0] Offset coordinates from the origin of the s-t beam axes to the centroid of the cross-section. Note that the principal axes x’-y’ of the cross-section are assumed parallel to the s-t axes of the beam. TORFAC [1.0] The torsional rigidity of the cross-section, corresponding to St. Venant torsion with free warping, is multiplied by the factor TORFAC. (See Theory and Modeling Guide for details). SSHEARF [0.0 (no s-direction shear effect)] TSHEARF [0.0 (no t-direction shear effect)] The shear areas corresponding to the beam s and t directions are calculated as the total cross-sectional area multiplied by the factors SSHEARF, TSHEARF, respectively. Auxiliary commands LIST CROSS-SECTION DELETE CROSS-SECTION
CROSS-SECTION I defines an I cross-section which can be used to describe the crosssectional characteristics of an elastic Hermitian BEAM element. WIDTH2
THICK3
HEIGHT
THICK2 Y' centroid
X'
THICK1 WIDTH1
NAME [(current highest cross-section label number) + 1] Label number of the cross-section to be defined. WIDTH1 HEIGHT WIDTH2 THICK1 THICK2 THICK3 The dimensions of the I cross-section. See Figure.
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CROSS-SECTION I
Sec. 7.2 Cross-sections / layers
SC [0.0] TC [0.0] Offset coordinates from the origin of the s-t beam axes to the centroid of the cross-section. Note that the principal axes x’-y’ of the cross-section are assumed parallel to the s-t axes of the beam. TORFAC [1.0] The torsional rigidity of the cross-section, corresponding to St. Venant torsion with free warping, is multiplied by the factor TORFAC. (See Theory and Modeling Guide for details). SSHEARF [0.0 (no s-direction shear effect)] TSHEARF [0.0 (no t-direction shear effect)] The shear areas corresponding to the beam s and t directions are calculated as the total cross-sectional area multiplied by the factors SSHEARF, TSHEARF, respectively. Auxiliary commands LIST CROSS-SECTION DELETE CROSS-SECTION
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CROSS-SECTION L
Chap. 7 Model definition
CROSS-SECTION L
NAME WIDTH HEIGHT THICK1 THICK2 SC TC TORFAC SSHEARF TSHEARF
CROSS-SECTION L defines an L cross-section which can be used to describe the crosssectional characteristics of an elastic Hermitian BEAM element.
THICK1
X'
THICK2
HEIGHT
Y' centroid
NAME [(current highest cross-section label number) + 1] Label number of the cross-section to be defined. WIDTH1 HEIGHT THICK1 THICK2 The dimensions of the L cross-section. See Figure. SC [0.0] TC [0.0] Offset coordinates from the origin of the s-t beam axes to the centroid of the cross-section. Note that the principal axes x’-y’ of the cross-section are assumed parallel to the s-t axes of the beam. TORFAC [1.0] The torsional rigidity of the cross-section, corresponding to St. Venant torsion with free warping, is multiplied by the factor TORFAC. (See Theory and Modeling Guide for details). 7-172
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CROSS-SECTION L
Sec. 7.2 Cross-sections / layers
SSHEARF [0.0 (no s-direction shear effect)] TSHEARF [0.0 (no t-direction shear effect)] The shear areas corresponding to the beam s and t directions are calculated as the total cross-sectional area multiplied by the factors SSHEARF, TSHEARF, respectively. Auxiliary commands LIST CROSS-SECTION DELETE CROSS-SECTION
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CROSS-SECTION PIPE
Chap. 7 Model definition
CROSS-SECTION PIPE
NAME DIAMETER THICKNESS SC TC TORFAC SSHEARF TSHEARF SOLID
CROSS-SECTION PIPE defines a pipe cross-section which can be used to describe the crosssectional characteristics of a BEAM or PIPE element.
TH
IC
K
N
ES S
NAME [(current highest cross-section label number) + 1] Label number of the cross-section to be defined.
Y'
X' centroid
DIAMETER DIAMETER THICKNESS The diameter and thickness dimensions, respectively, of the pipe cross-section. See Figure. SC [0.0] TC [0.0] Offset coordinates from the origin of the s-t beam axes to the centroid of the cross-section. Note that the principal axes x’-y’ of the cross-section are assumed parallel to the s-t axes of the beam.
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CROSS-SECTION PIPE
Sec. 7.2 Cross-sections / layers
TORFAC [1.0] The torsional rigidity of the cross-section, corresponding to St. Venant torsion with free warping, is multiplied by the factor TORFAC. (See Theory and Modeling Guide for details). SSHEARF [0.0 (no s-direction shear effect)] TSHEARF [0.0 (no t-direction shear effect)] The shear areas corresponding to the beam s and t directions are calculated as the total cross-sectional area multiplied by the factors SSHEARF, TSHEARF, respectively. Note:
The parameters SC, TC, TORFAC, SSHEARF, TSHEARF are only applicable to elastic Hermitian BEAM elements.
SOLID [NO] Indicates whether the cross section is solid, i.e. not hollow. If SOLID=YES, THICKNESS input is ignored and the thickness is set to half the diameter value. {YES/NO} Auxiliary commands LIST CROSS-SECTION DELETE CROSS-SECTION
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CROSS-SECTION RECTANGULAR
Chap. 7 Model definition
CROSS-SECTION RECTANGULAR
NAME WIDTH HEIGHT SC TC TORFAC SSHEARF TSHEARF ISHEAR SQUARE
CROSS-SECTION RECTANGULAR defines a rectangular cross-section which can be used to describe the cross-sectional characteristics of a BEAM or ISOBEAM element.
X'
HEIGHT
Y'
centroid
WIDTH
NAME [(current highest cross-section label number) + 1] Label number of the cross-section to be defined. WIDTH HEIGHT The width and height dimensions, respectively, of the rectangular cross-section. See Figure. SC [0.0] TC [0.0] Offset coordinates from the origin of the s-t beam axes to the centroid of the cross-section. Note that the principal axes x’-y’ of the cross-section are assumed parallel to the s-t axes of the beam. 7-176
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CROSS-SECTION RECTANGULAR
Sec. 7.2 Cross-sections / layers
TORFAC [1.0] The torsional rigidity of the cross-section, corresponding to St. Venant torsion with free warping, is multiplied by the factor TORFAC. (See Theory and Modeling Guide for details). SSHEARF [0.0 (no s-direction shear effect)] TSHEARF [0.0 (no t-direction shear effect)] The shear areas corresponding to the beam s and t directions are calculated as the total cross-sectional area multiplied by the factors SSHEARF, TSHEARF, respectively. ISHEAR Indicates whether transverse shear effects are to be included. {YES/NO}
[NO]
Note: The parameters SC, TC, TORFAC, SSHEARF, TSHEARF are applicable only to elastic Hermitian BEAM elements. Note:
The parameter ISHEAR is applicable only to plastic Hermitian BEAM elements.
SQUARE [NO] Indicates whether the cross section shape is square. If SQUARE=YES, HEIGHT input is ignored and the height is set equal to the width.{YES/NO} Auxiliary commands LIST CROSS-SECTION DELETE CROSS-SECTION
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CROSS-SECTION U
Chap. 7 Model definition
CROSS-SECTION U
NAME WIDTH HEIGHT THICK1 THICK2 SC TC TORFAC SSHEARF TSHEARF
THICK2
CROSS-SECTION U defines a U cross-section which can be used to describe the crosssectional characteristics of an elastic Hermitian BEAM element.
HEIGHT
Y' centroid
X'
THICK1
WIDTH
NAME [(current highest cross-section label number) + 1] Label number of the cross-section to be defined. WIDTH HEIGHT THICK1 THICK2 The dimensions of the U cross-section. See Figure.
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CROSS-SECTION U
Sec. 7.2 Cross-sections / layers
SC [0.0] TC [0.0] Offset coordinates from the origin of the s-t beam axes to the centroid of the cross-section. Note that the principal axes x’-y’ of the cross-section are assumed parallel to the s-t axes of the beam. TORFAC [1.0] The torsional rigidity of the cross-section, corresponding to St. Venant torsion with free warping, is multiplied by the factor TORFAC. (See Theory and Modeling Guide for details). SSHEARF [0.0 (no s-direction shear effect)] TSHEARF [0.0 (no t-direction shear effect)] The shear areas corresponding to the beam s and t directions are calculated as the total cross-sectional area multiplied by the factors SSHEARF, TSHEARF, respectively. Auxiliary commands LIST CROSS-SECTION DELETE CROSS-SECTION
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CROSS-SECTION PROPERTIES
Chap. 7 Model definition
CROSS-SECTION PROPERTIES NAME RINERTIA SINERTIA TINERTIA AREA SAREA TAREA CTOFFSET CSOFFSET STINERTIA SRINERTIA TRINERTIA WINERTIA WRINERTIA DRINERTIA CROSS-SECTION PROPERTIES defines a general cross-section in terms of principal moments of inertia and areas. This cross-section definition can be used to describe the cross-sectional characteristics of an elastic Hermitian BEAM element. (See Figure for beam element coordinate system.)
Node AUX lies in r-s plane
s AUX
r N2
Z N1 t X
The r-axis represents the beam axis, but not necessarily the principal axis of the section
Y
BEAM ELEMENT COORDINATE SYSTEM NAME [(current highest cross-section label number) + 1] Label number of the cross-section to be defined. RINERTIA Torsional moment of inertia, about the beam r-axis. This includes warping effects. SINERTIA Bending moment of inertia about the beam s-axis.
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CROSS-SECTION PROPERTIES
Sec. 7.2 Cross-sections / layers
TINERTIA Bending moment of inertia about the t-axis. AREA Cross-sectional area. SAREA Effective shear area in the s-direction.
[0.0]
TAREA Effective shear area in the t-direction.
[0.0]
CTOFFSET [0.0] Distance between the centroid and shear center of the cross section along the T direction (zero if section is symmetric about the local S axis). CSOFFSET [0.0] Distance between the centroid and shear center of the cross section along the S direction (zero if section is symmetric about the local T axis). STINERTIA [0.0] Inertia term causing coupling between bending about the S axis and bending about the T axis (zero if section is symmetric about either S or T axis). SRINERTIA [0.0] Inertia term causing coupling between twist/warping and bending about the T axis (zero if section is symmetric about the T axis). This term is caused by the Wagner term in the kinematics. TRINERTIA [0.0] Inertia term causing coupling between twist/warping and bending about the S axis (zero if the section is symmetric about the local S axis). This is caused by the Wagner term in the kinematics. WINERTIA Warping constant.{≥0}
[0.0]
WRINERTIA [0.0] Inertia term causing bi-moment due to warping (zero if the section is symmetric about either S or T axis). It is caused by the Wagner term. DRINERTIA Inertia term causing nonlinear twist due to the Wagner effect. {≥0}
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Chap. 7 Model definition
Notes: 1.
The S-axis and T-axis are not the principal axes of the cross section. They are parallel to the sides of the L-section, U-section and I-section and pass through the centroid of the cross section.
2.
Warping beam should not be used as a bolt.
3.
Warping beam should not be used as a rigid link.
4.
Warping beam should not be used as a 2D beam.
5.
SAREA and TAREA should not be used with the warping beam.
6.
CTOFFSET, CSOFFSET, STINERTIA, SRINERTIA, TRINERTIA, WINERTIA, WRINERTIA and DRINERTIA should only be used with the warping beam.
Auxiliary commands LIST CROSS-SECTION DELETE CROSS-SECTION
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Sec. 7.2 Cross-sections / layers
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LAYER
Chap. 7 Model definition
LAYER
SUBSTRUCTURE GROUP PLY-DATA
namei materiali tinti pthicki maxesi phii iaxesi phiii printi savei intloci failurei plydatai LAYER defines the control parameters for each surface layer for use by multi-layer shell elements.
layer 3 layer 2
thickness
layer 1
midsurface midsurface node
SUBSTRUCTURE Label number of the substructure. GROUP The label number of the element group.
[current substructure label number] [current element group]
PLY-DATA [NO] This flag determines whether ply data defined by the PLY-DATA command are used to calculate layer thicknesses. {YES/NO} YES
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LAYER
Sec. 7.2 Cross-sections / layers
The thickness of each layer are calculated using pthicki.
NO
namei Layer label number. {1 ≤ namei ≤ NLAYER, NLAYER = total number of layers, see EGROUP SHELL} materiali Material label number used for layer namei.
[1]
tinti Integration order for the through-thickness direction (local t-direction) in layer namei.
[2]
2
≤
tinti ≤
6
-7
≤
tinti ≤
-3
Gauss formulas. Closed Newton-Cotes formulas.
pthicki [(1./NLAYER) × 100] Percentage of element thickness assigned to this layer. (NLAYER is the total number of layers, see EGROUP SHELL). maxesi Material axes for orthotropic model, for layer namei. phii Offset angle for orthotropic model, for layer namei.
[0] [0.0]
iaxesi Initial strain axes, for layer namei. phiii Offset angle for initial strains, for layer namei.
[0] [0.0]
printi [DEFAULT] This parameter controls the printing of element results for the layer namei. {YES / NO / STRAINS / DEFAULT} YES
Print the element results for layer namei.
NO
No results are printed for layer namei.
STRAINS
Strains are printed in addition to the stresses for layer namei.
DEFAULT
Layer printing is governed by element data commands.
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LAYER
Chap. 7 Model definition
savei [DEFAULT] This parameter controls the saving of element results for the layer namei. {YES / NO / DEFAULT} YES
Save the element results on the porthole file for layer namei.
NO
No saving of results for layer namei.
DEFAULT
Layer saving is governed by element data commands.
intloci [DEFAULT] This parameter controls the printing of integration point coordinates for the layer namei. {YES / NO / DEFAULT} YES
Print integration point (global) coordinates for layer namei.
NO
No printing of integration point data for layer namei.
DEFAULT
Printout of integration point data is governed by element data commands.
failurei The label number of failure criterion. (See FAILURE ). A zero value indicates no failure criterion for layer namei.
[0]
plydatai The label number of the command PLY-DATA, from which the layer thickness is calculated. If the parameter PLY-DATA = NO, or number of layers is equal 1, this parameter will be ignored. Auxiliary commands LIST LAYER DELETELAYER
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PLY-DATA
PLY-DATA
Sec. 7.2 Cross-sections / layers
NAME WEIGHT DENSITY FRACTION
Command PLY-DATA defines the layer thickness for a fiber-matrix composite. It is used in definition of shell elements by the LAYER command. NAME [(current highest ply-data label number) + 1] Label number of the ply-data to be defined. If the label number of an existing ply-data is given, then the previous ply-data definition is overwritten. WEIGHT Weight per unit surface of the fiber. DENSITY Density of the fiber. FRACTION Fiber volume fraction of the fiber-matrix compound. Auxiliary commands LIST PLY-DATA DELETE PLY-DATA
edgei materiali areai printi savei tbirthi tdeathi gapwidthi intloci epsini LINE-ELEMDATA TRUSS assigns data for TRUSS elements to geometry lines. EDGE-ELEMDATA TRUSS assigns data for TRUSS elements to solid geometry edges. BODY The geometry body label number.
[current active BODY]
linei Line label number. edgei Edge label number (for BODY). materiali [0] Material label number. A zero input value indicates that elements generated on the line/ edge will take the default material for the host element group. areai Cross-sectional area for each TRUSS element on the line/edge. printi
[0]
[DEFAULT]
YES
Print results for TRUSS elements on line/edge.
NO
No results are printed for TRUSS elements on the line/edge.
DEFAULT
Element printing is governed by PRINTOUT PRINTDEFAULT.
savei
[DEFAULT]
YES
Save results for TRUSS elements on line/edge.
NO
No saving of results for TRUSS elements on the line/edge.
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LINE-ELEMDATA TRUSS
DEFAULT
Sec. 7.3 Element properties
Saving of element results is governed by PORTHOLE SAVEDEFAULT.
tbirthi The time of element birth.
[0.0]
tdeathi The time of element death.
[0.0]
gapwidthi Gap width for each TRUSS element on the line/edge. A zero value indicates no gap.
[0.0]
intloci [NO] Indicates whether to print element integration point coordinates (global) in the undeformed configuration. {YES/NO} epsini Initial strain for each TRUSS element on the line/edge.
[0.0]
Auxiliary commands LIST LINE-ELEMDATA TRUSS DELETE LINE-ELEMDATA TRUSS
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LIST EDGE-ELEMDATA TRUSS DELETE EDGE-ELEMDATA TRUSS
facei materiali betai printi savei tbirthi tdeathi intloci gammai SURF-ELEMDATA TWODSOLID assigns data for TWODSOLID elements to geometry surfaces. FACE-ELEMDATA TWODSOLID assigns data for TWODSOLID elements to solid geometry faces. BODY The geometry body label number.
[current active BODY]
surfacei Surface label number. facei Face label number (for BODY). materiali [0] Material label number. A zero input value indicates that elements generated on the surface/ face will take the default material for the host element group. betai [0.0] Material angle, in degrees, for each TWODSOLID element on the surface/face. Used in conjunction with orthotropic material types. printi
[DEFAULT]
YES
Print results as requested by EGROUP RESULTS.
NO
No results are printed for TWODSOLID elements on the surface/face.
STRAINS
In addition to stresses, strains are printed.
DEFAULT
Printout is governed by PRINTOUT PRINTDEFAULT.
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SURF-ELEMDATA TWODSOLID
Sec. 7.3 Element properties
savei
[DEFAULT]
YES
Save, on the porthole file, element results as requested by EGROUP RESULTS.
NO
No saving of results for TWODSOLID elements on the surface/face.
DEFAULT
Saving of element results is governed by PORTHOLE SAVEDEFAULT.
tbirthi The time of element birth.
[0.0]
tdeathi The time of element death.
[0.0]
intloci [NO] Specifies whether element integration point (global) coordinates, in the undeformed configuration are printed. {YES/NO} gammai [0.0] Initial strain angle, in degrees, used in conjunction with any definition of element initial strains. Auxiliary commands LIST SURF-ELEMDATA TWODSOLID DELETE SURF-ELEMDATA TWODSOLID
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LIST FACE-ELEMDATA TWODSOLID DELETE FACE-ELEMDATA TWODSOLID
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VOL-ELEMDATA THREEDSOLID
Chap. 7 Model definition
VOL-ELEMDATA THREEDSOLID volumei materiali maxesi printi savei tbirthi tdeathi intloci maxesii ngeomi BODY-ELEMDATA THREEDSOLID bodyi materiali maxesi printi savei tbirthi tdeathi intlocii maxesii ngeomi VOL-ELEMDATA THREEDSOLID assigns data for THREEDSOLID elements to geometry volumes. BODY-ELEMDATA THREEDSOLID assigns data for THREEDSOLID elements to solid geometry bodies. volumei Volume label number. bodyi Body label number. materiali [0] Material label number. A zero input value indicates that elements generated in the volume/ body will take the default material for the host element group. maxesi [0] Material axes set for each THREEDSOLID element in the volume/body. Used in conjunction with orthotropic material types. printi
[DEFAULT]
YES
Print element results as requested by EGROUP RESULTS.
NO
No results are printed for THREEDSOLID elements in the volume/body.
STRAINS
Strains as well as stresses are printed for THREEDSOLID elements in the volume/body.
DEFAULT
Element printing is governed by PRINTOUT PRINTDEFAULT.
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VOL-ELEMDATA THREEDSOLID
Sec. 7.3 Element properties
savei
[DEFAULT]
YES
Save, on the porthole file, element results as requested by EGROUP RESULTS.
NO
No saving of results for THREEDSOLID elements in the volume/ body.
DEFAULT
Saving of element results is governed by command PORTHOLE SAVEDEFAULT.
tbirthi The time of element birth.
[0.0]
tdeathi The time of element death.
[0.0]
intloci [NO] Determines whether or not element integration point (global) coordinates in the undeformed configuration are printed. {YES/NO} maxesii [0] Initial strain axes set for each THREEDSOLID element in the volume/body. Used in conjunction with element initial strains. ngeomi This parameter is obsolete. Auxiliary commands LIST VOL-ELEMDATA THREEDSOLID DELETE VOL-ELEMDATA THREEDSOLID
FIRST LAST FIRST LAST
LIST BODY-ELEMDATA THREEDSOLID DELETE BODY-ELEMDATA THREEDSOLID
edgei materiali sectioni endreleasei printi savei tbirthi tdeathi intloci epsini, moment-ri moment-si moment-ti rigid-starti rigid-endi LINE-ELEMDATA BEAM assigns data for BEAM elements to geometry lines. EDGE-ELEMDATA BEAM assigns data for BEAM elements to solid geometry edges. BODY Body label number
[current active BODY]
linei Line label number. edgei Edge label number. materiali [0] Material label number. A zero input value indicates that elements generated on the line/edge will take the default material for the host element group. sectioni [0] Cross-section label number for each BEAM element on the line/edge. See CROSS-SECTION. endreleasei End-release condition label number for each BEAM element on the line/edge. See ENDRELEASE. printi
[DEFAULT]
YES
Print element results as requested by EGROUP RESULTS.
NO
No results are printed for BEAM elements on the line/edge.
DEFAULT
Element printing is governed by PRINTOUT PRINTDEFAULT.
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LINE-ELEMDATA BEAM
Sec. 7.3 Element properties
savei
[DEFAULT]
YES
Save, on the porthole file, element results as requested by EGROUP RESULTS.
NO
No saving of results for BEAM elements on the line/edge.
DEFAULT
Saving of element results is governed by command PORTHOLE SAVEDEFAULT.
tbirthi The time of element birth.
[0.0]
tdeathi The time of element death.
[0.0]
[NO] intloci Indicates whether to print element integration point (global) coordinates in the undeformed configuration. {YES/NO} epsini Initial axial strain for each BEAM element on the line/edge, or initial force if BEAM OPTION=BOLT is used.
[0.0]
moment-ri moment-si moment-ti [0.0] rigid-starti Length of the rigid end-zone connected to the start-point (at u=0.0) of the geometry line/ edge. Note that this zone can span at most one element meshed onto the line. [0.0] rigid-endi Length of the rigid end-zone connected to the end-point (at u=1.0) of the geometry line/edge. Note that this zone can span at most one element meshed onto the line. Auxiliary commands LIST LINE-ELEMDATA BEAM DELETE LINE-ELEMDATA BEAM
edgei materiali sectioni printi savei tbirthi tdeathi intloci epaxli ephoopi LINE-ELEMDATA ISOBEAM assigns data for ISOBEAM elements to geometry lines. EDGE-ELEMDATA ISOBEAM assigns data for ISOBEAM elements to solid geometry edges. BODY Body label number
[current active BODY]
linei Line label number. edgei Edge label number (for BODY). materiali [0] Material label number. A zero input value indicates that elements generated on the line/edge will take the default material for the host element group. sectioni [0] Cross-section label number for each ISOBEAM element on the line/edge. See CROSS-SECTION. printi
[DEFAULT]
YES
Print element results as requested by EGROUP RESULTS.
NO
No results are printed for ISOBEAM elements on the line/edge.
DEFAULT
Element printing is governed by PRINTOUT PRINTDEFAULT.
savei YES
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LINE-ELEMDATA ISOBEAM
Sec. 7.3 Element properties
NO
No saving of results for ISOBEAM elements on the line/edge.
DEFAULT
Saving of element results is governed by command PORTHOLE SAVEDEFAULT.
tbirthi The time of element birth.
[0.0]
tdeathi The time of element death.
[0.0]
intloci [NO] Indicates whether to print element integration point (global) coordinates in the undeformed configuration. {YES/NO} epaxli Initial axial strain for each ISOBEAM element on the line/edge.
[0.0]
ephoopi Initial hoop strain for each ISOBEAM element on the line/edge.
[0.0]
Auxiliary commands LIST LINE-ELEMDATA ISOBEAM DELETE LINE-ELEMDATA ISOBEAM
FIRST LAST FIRST LAST
LIST EDGE-ELEMDATA ISBEAM DELETE EDGE-ELEMDATA ISOBEAM
facei materiali betai printi savei tbirthi tdeathi intloci gammai, eps11i eps22i eps12i flex11i flex22i flex12i SURF-ELEMDATA PLATE assigns data for PLATE elements to geometry surfaces. FACE-ELEMDATA PLATE assigns data for PLATE elements to solid geometry faces. BODY Body label number
[current active BODY]
surfacei Surface label number. facei Face label number (for BODY). materiali [0] Material label number. A zero input value indicates that elements generated on the surface/ facve will take the default material for the host element group. betai [0.0] Material angle, in degrees, for each PLATE element on the surface/face. Used in conjunction with orthotropic material types. printi
[DEFAULT]
YES
Print element results as requested by EGROUP RESULTS.
NO
No results are printed for PLATE elements on the surface/face.
DEFAULT
Printout is governed by PRINTOUT PRINTDEFAULT.
savei YES
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SURF-ELEMDATA PLATE
Sec. 7.3 Element properties
NO
No saving of results for PLATE elements on the surface/face.
DEFAULT
Saving of element results is governed by command PORTHOLE SAVEDEFAULT.
tbirthi The time of element birth.
[0.0]
tdeathi The time of element death.
[0.0]
intloci [NO] Specifies whether or not element integration point (global) coordinates, in the undeformed configuration, together with direction cosines of stress reference axes are printed. {YES/NO} gammai [0.0] Initial strain angle, in degrees, used in conjunction with any definition of element initial strains. eps11i [0.0] eps22i [0.0] eps12i [0.0] Initial membrane strain components in the element, assumed constant within the element. flex11i [0.0] flex22i [0.0] flex12i [0.0] Initial flexural strain components in the element, assumed constant within the element. Auxiliary commands LIST SURF-ELEMDATA PLATE DELETE SURF-ELEMDATA PLATE
FIRST LAST FIRST LAST
LIST FACE-ELEMDATA PLATE DELETE FACE-ELEMDATA PLATE
facei materiali betai printi savei tbirthi tdeathi ithsi intloci gammai eps11i, eps22i eps12i eps13i eps23i geps11i geps22i geps12i geps13i geps23i SURF-ELEMDATA SHELL assigns data for SHELL elements to geometry surfaces. FACE-ELEMDATA SHELL assigns data for SHELL elements to solid geometry faces. BODY Body label number
[current active BODY]
surfacei Surface label number. facei Face label number (for BODY). materiali [0] Material label number. A zero input value indicates that elements generated on the surface/ face will take the default material for the host element group. betai [0.0] Material angle, in degrees, for each SHELL element on the surface/face. Used in conjunction with orthotropic material types. printi
[DEFAULT]
YES
Print results as requested by EGROUP RESULTS.
NO
No results are printed for SHELL elements on the surface/face.
STRAINS
In addition to stresses, strains are printed.
DEFAULT
Printout is governed by PRINTOUT PRINTDEFAULT.
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SURF-ELEMDATA SHELL
Sec. 7.3 Element properties
savei
[DEFAULT]
YES
Save, on the porthole file, element results as requested by EGROUP RESULTS.
NO
No saving of results for SHELL elements on the surface/face.
DEFAULT
Saving of element results is governed by command PORTHOLE SAVEDEFAULT.
tbirthi The time of element birth.
[0.0]
tdeathi The time of element death.
[0.0]
ithsi [NO] Specifies whether or not the thick shell assumption is made for transverse shear behavior of SHELL elements on the surface/face. {YES/NO} intloci [NO] Specifies whether or not element integration point (global) coordinates, in the undeformed configuration, together with direction cosines of stress reference axes are printed. {YES/NO} gammai [0.0] Initial strain angle, in degrees, used in conjunction with any definition of element initial strains. epsjki (jk = 11, 22, 12, 13, 23) Initial strain components in the element, assumed constant within the element.
[0.0]
gepsjki (jk = 11, 22, 12, 13, 23) [0.0] Initial strain gradient components in the element, assumed constant within the element. Auxiliary commands LIST SURF-ELEMDATA SHELL DELETE SURF-ELEMDATA SHELL
FIRST LAST FIRST LAST
LIST FACE-ELEMDATA SHELL DELETE FACE-ELEMDATA SHELL
FIRST LAST FIRST LAST
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ELAYER
ELAYER GROUP elementi layeri materiali ELAYER assigns material to individual elements on different layers for shell elements. GROUP The label number of the element group.
[Current element group]
elementi The element label number. layeri The layer label number. materiali The material label number.
[1]
Auxiliary commands LIST ELAYER GROUP DELETE ELAYER GROUP
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edgei materiali sectioni printi savei tbirthi tdeathi intloci epsini LINE-ELEMDATA PIPE assigns data for PIPE elements on geometry lines. EDGE-ELEMDATA PIPE assigns data for PIPE elements on solid geometry edges. BODY Body label number.
[current active BODY]
linei Line label number. edgei Edge label number (for BODY). materiali [0] Material label number. A zero input value indicates that elements generated on the line/edge will take the default material for the host element group. sectioni [0] Cross-section label number for each PIPE element on the line/edge. See CROSS- SECTION. printi
[DEFAULT]
YES
Print element results as requested by EGROUP RESULTS.
NO
No results are printed for PIPE elements on the line/edge.
DEFAULT
Element printing is governed by PRINTOUT PRINTDEFAULT.
savei
[DEFAULT]
YES
Save, on the porthole file, element results as requested by EGROUP RESULTS.
NO
No saving of results for PIPE elements on the line/edge.
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LINE-ELEMDATA PIPE
DEFAULT
Sec. 7.3 Element properties
Saving of element results is governed by command PORTHOLE SAVEDEFAULT.
tbirthi The time of element birth.
[0.0]
tdeathi The time of element death.
[0.0]
intloci [NO] Indicates whether to print element integration point (global) coordinates in the undeformed configuration. {YES/NO} epsini Initial axial strain for each PIPE element on the line/edge.
[0.0]
Auxiliary commands LIST LINE-ELEMDATA PIPE DELETE LINE-ELEMDATA PIPE
FIRST LAST FIRST LAST
LIST EDGE-ELEMDATA PIPE DELETE EDGE-ELEMDATA PIPE
FIRST LAST FIRST LAST
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LINE-ELEMDATA GENERAL
Chap. 7 Model definition
LINE-ELEMDATA GENERAL linei mseti printi savei tbirthi tdeathi EDGE-ELEMDATA GENERAL
BODY
edgei mseti printi savei tbirthi tdeathi SURF-ELEMDATA GENERAL surfacei mseti printi savei tbirthi tdeathi FACE-ELEMDATA GENERAL
BODY
facei mseti printi savei tbirthi tdeathi VOL-ELEMDATA GENERAL volumei mseti printi savei tbirthi tdeathi BODY-ELEMDATA GENERAL bodyi mseti printi savei tbirthi tdeathi LINE-ELEMDATA GENERAL assigns data for GENERAL elements on lines. EDGE-ELEMDATA GENERAL assigns data for GENERAL elements to solid geometry edges. SURF-ELEMDATA GENERAL assigns data for GENERAL elements to geometry surfaces FACE-ELEMDATA GENERAL assigns data for GENERAL elements to solid geometry faces. VOL-ELEMDATA GENERAL assigns data for GENERAL elements to geometry volumes. BODY-ELEMDATA GENERAL assigns data for GENERAL elements to solid geometry bodies. BODY Body label number.
[currently active BODY]
linei Line label number.
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LINE-ELEMDATA GENERAL
Sec. 7.3 Element properties
edgei Edge label number (for BODY). surfacei Surface label number. facei Face label number (for BODY). volumei Volume label number. bodyi Body label number. mseti [0] Matrixset label number. A zero input value indicates that elements generated on the geometry will take the default matrixset for the host element group. printi
[DEFAULT]
YES
Print element results as requested by EGROUP RESULTS.
NO
No results are printed for GENERAL elements on the geometry.
DEFAULT
Element printing is governed by PRINTOUT PRINTDEFAULT.
savei
[DEFAULT]
YES
Save, on the porthole file, element results as requested by EGROUP RESULTS.
NO
No saving of results for GENERAL elements on the geometry.
DEFAULT
Saving of element results is governed by command PORTHOLE SAVEDEFAULT.
tbirthi Element birth time.
[0.0]
tdeathi Element death time.
[0.0]
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Note:
LINE-ELEMDATA GENERAL
tbirthi < tdeathi, or tbirthi = tdeathi = 0.0
Auxiliary commands LIST LINE-ELEMDATA GENERAL DELETE LINE-ELEMDATA GENERAL
FIRST LAST FIRST LAST
LIST EDGE-ELEMDATA GENERAL DELETE EDGE-ELEMDATA GENERAL
FIRST LAST FIRST LAST
LIST SURF-ELEMDATA GENERAL DELETE SURF-ELEMDATA GENERAL
FIRST LAST FIRST LAST
LIST FACE-ELEMDATA GENERAL DELETE FACE-ELEMDATA GENERAL
FIRST LAST FIRST LAST
LIST VOL-ELEMDATA GENERAL DELETE VOL-ELEMDATA GENERAL
FIRST LAST FIRST LAST
LIST BODY-ELEMDATA GENERAL DELETE BODY-ELEMDATA GENERAL
FIRST LAST FIRST LAST
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facei materiali printi savei tbirthi tdeathi intloci SURF-ELEMDATA FLUID2 assigns data for FLUID2 elements on surfaces. FACE-ELEMDATA FLUID2 assigns data for FLUID2 elements on solid geometry faces. BODY Body label number.
[currently active BODY]
surfacei Surface label number. facei Face label number (for BODY). materiali [0] Material label number. A zero input value indicates that elements generated on the surface/ face will take the default material for the host element group. printi
[DEFAULT]
YES
Print element results as requested by EGROUP RESULTS.
NO
No results are printed for FLUID2 elements on the surface/face.
DEFAULT
Element printing is governed by PRINTOUT PRINTDEFAULT.
savei
[DEFAULT]
YES
Save, on the porthole file, element results as requested by EGROUP RESULTS.
NO
No saving of results for FLUID2 elements on the surface/face.
DEFAULT
Saving of element results is governed by command PORTHOLE SAVEDEFAULT.
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Chap. 7 Model definition
SURF-ELEMDATA FLUID2
tbirthi The time of element birth.
[0.0]
tdeathi The time of element death.
[0.0]
intloci [NO] Indicates whether to print element integration point (global) coordinates in the undeformed configuration. {YES/NO} Auxiliary commands LIST SURF-ELEMDATA FLUID2 DELETE SURF-ELEMDATA FLUID2
FIRST LAST FIRST LAST
LIST FACE-ELEMDATA FLUID2 DELETE FACE-ELEMDATA FLUID2
FIRST LAST FIRST LAST
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VOL-ELEMDATA FLUID3
Sec. 7.3 Element properties
VOL-ELEMDATAFLUID3 volumei materiali printi savei tbirthi tdeathi intloci ngeomi BODY-ELEMDATAFLUID3 bodyi materiali printi savei tbirthi tdeathi intloci ngeomi VOL-ELEMDATA FLUID3 assigns data for FLUID3 elements in volumes. BODY-ELEMDATA FLUID3 assigns data for FLUID3 elements in solid geometry bodies. volumei Volume label number. bodyi Body label number. materiali [0] Material label number. A zero input value indicates that elements generated on the volume/ body will take the default material for the host element group. printi
[DEFAULT]
YES
Print element results as requested by EGROUP RESULTS.
NO
No results are printed for FLUID3 elements on the volume/body.
DEFAULT
Element printing is governed by PRINTOUT PRINTDEFAULT.
savei
[DEFAULT]
YES
Save, on the porthole file, element results as requested by EGROUP RESULTS.
NO
No saving of results for FLUID3 elements on the volume/body.
DEFAULT
Saving of element results is governed by command PORTHOLE SAVEDEFAULT.
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VOL-ELEMDATA FLUID3
tbirthi The time of element birth.
[0.0]
tdeathi The time of element death.
[0.0]
intloci [NO] Indicates whether to print element integration point (global) coordinates in the undeformed configuration. {YES/NO} ngeomi This parameter is obsolete. Auxiliary commands LIST VOL-ELEMDATAFLUID3 DELETE VOL-ELEMDATAFLUID3
FIRST LAST FIRST LAST
LIST BODY-ELEMDATAFLUID3 DELETE BODY-ELEMDATAFLUID3
FIRST LAST FIRST LAST
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MATRIX STIFFNESS
Sec. 7.3 Element properties
MATRIX STIFFNESS rowi ... kij ...
NAME ND (j = i, i + 1, ..., ND)
Defines a stiffness matrix for use by GENERAL elements. It may be referenced by MATRIXSET. NAME [(current highest matrix label number) + 1] Label number of the matrix to be defined. ND [1] The total number of rows entered in this matrix, equal to the number of nodes in the general element multiplied by the number of active degrees of freedom per node. {1 ≤ ND ≤ 600} rowi Row index number for matrix. k ij Entries in the stiffness matrix (kij = entry for row “i”, column “j”).
[0.0]
Note: Only the upper-diagonal part of the stiffness matrix is entered by this command. Thus, for rowi, only the first (ND - i + 1) entries are used - the rest are ignored due to symmetry. Auxiliary Commands LIST MATRIX DELETE MATRIX
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MATRIX MASS
Chap. 7 Model definition
MATRIX MASS
NAME ND
rowi ... mij ... (j = i, (i + 1), ..., ND) Defines a mass matrix for use by GENERAL elements. It may be referenced by MATRIXSET. NAME [(current highest matrix label number) + 1] Label number of the matrix to be defined. ND [1] The total number of rows entered in this matrix, equal to the number of nodes in the general element multiplied by the number of active degrees of freedom per node. {1 ≤ ND ≤ 600} rowi Row index number for matrix. mij Entries in the mass matrix (mij = entry for row “i”, column “j”).
[0.0]
Note: For a consistent mass matrix, only the upper-diagonal part of the mass matrix is entered by this command. Thus, for rowi, only the first (ND - i + 1) entries are used. When the mass matrix is lumped, only the diagonal term, mij, should be entered - the rest are ignored due to symmetry. Auxiliary Commands LIST MATRIX DELETE MATRIX
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MATRIX DAMPING
MATRIX DAMPING rowi ... cij ...
Sec. 7.3 Element properties
NAME ND (j = i, (i + 1), ..., ND)
Defines a damping matrix for use by GENERAL elements. It may be referenced by MATRIXSET. NAME [(current highest matrix label number) + 1] Label number of the matrix to be defined. ND [1] The total number of rows entered in this matrix, equal to the number of nodes in the general element multiplied by the number of active degrees of freedom per node. {1 ≤ ND ≤ 600} rowi Row index number for matrix. cij Entries in the damping matrix (cij = entry for row “i”, column “j”).
[0.0]
Note: Only the upper-diagonal part of the damping matrix is entered by this command. Thus, for rowi only the first (ND - i + 1) entries are used, the rest are ignored due to symmetry. Auxiliary Commands LIST MATRIX DELETE MATRIX
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MATRIX STRESS
Chap. 7 Model definition
MATRIX STRESS rowi ... sij ...
NAME NS ND (i=1…NS; j=1…ND)
Defines a stress matrix for use by GENERAL elements. It may be referenced by MATRIXSET. NAME [(current highest matrix label number) + 1] Label number of the matrix to be defined. NS The total number rows in the matrix, equal to the number of stress components. {1 ≤ NS ≤ 60}
[1]
ND [1] The number of nodes in the general element multiplied by the number of active degrees of freedom per node. {1 ≤ ND ≤ 600} rowi Row index number. s ij Entries in the stress-transformation matrix (sij = entry for row “i”, column “j”). Note:
[0.0]
The full matrix should be entered - no symmetry is assumed.
Auxiliary Commands LIST MATRIX DELETE MATRIX
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MATRIXSET
MATRIXSET
Sec. 7.3 Element properties
NAME STIFFNESS MASS DAMPING STRESS
Defines a “matrixset” of stiffness, mass, damping and stress-transformation label numbers for general elements. One stiffness, one mass, one damping and one stress-transformation label number are grouped into a matrix set, which can be associated with the elements of an EGROUP GENERAL element group through its MATRIXSET parameter. NAME [(current highest matrix label number) + 1] Label number of the matrixset to be defined. STIFFNESS Label number of stiffness matrix defined by MATRIX STIFFNESS.
[0]
MASS Label number of mass matrix defined by MATRIX MASS.
[0]
DAMPING Label number of damping matrix defined by MATRIX DAMPING.
[0]
STRESS Label number of stress-transformation matrix defined by MATRIX STRESS.
[0]
Auxiliary commands LIST MATRIXSET DELETE MATRIXSET
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Chap. 7 Model definition
MATRIX USER-SUPPLIED
MATRIX USER-SUPPLIED
NAME ELEMENT-SUBTYPE ELNDOF MATERIAL NUIPT NUIT1 NUIT2 NUIT3
Command MATRIX USER-SUPPLIED defines the element stiffness matrix and nodal force vector in a general element group, to be provided in the ADINA subroutine CUSERG. The material constants, variables and solution control parameters required in subroutine CUSERG can be input via parameter MATERIAL. The element subtype must be input to predetermine the sizes of arrays RE (element nodal forces) and AS (element stiffness) in CUSERG. If some element results, e.g. stresses and strains, are to be displayed by ADINA-PLOT, the integration scheme locations need to be provided through parameters NUIPT, NUIT1, NUIT2 and NUIT3. NAME [(current highest matrix label number) + 1] Label number of the matrix to be defined. If the label of an existing matrix is given, then the previous matrix definition is overwritten. ELEMENT-SUBTYPE Element subtype indicator for assembling the general element stiffness. This parameter must be entered. {TWODSOLID/THREEDSOLID/BEAM/SHELL} ELNDOF [subtype dependent] This parameter is not used. However, note that the number of active degrees of freedom per node for a user-supplied element is set by the IDOF parameter of the MASTER command. MATERIAL The label number of MATERIAL USER-SUPPLIED, in which material constants/variables and solution control parameters to be used in the calculations of element stiffness matrices and force vectors are entered. The material constants/variables can be temperature-independent or temperature-dependent. NUIPT [NUIT1 × NUIT2 × NUIT3] Number of user-provided interior points used to assemble the element stiffness matrix and to display the element results at these locations. NUIT1 [1] NUIT2 [1] NUIT3 [1] Integration orders in the first, second and third local directions of general elements (less than or equal to 6).
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facei mass1i mass2i mass3i mass4i mass5i mass6i MASSES POINTS assigns concentrated masses to the nodes at a set of geometry points. MASSES LINES assigns concentrated masses to the nodes on a set of geometry lines. MASSES VOLUMES assigns concentrated masses to the nodes in a set of geometry volumes. MASSES NODESETS assigns concentrated masses to the nodes in a node set. MASSES EDGES assigns concentrated masses to the nodes on solid geometry edges. MASSES FACES assigns concentrated masses to the nodes on solid geometry faces.
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BODY Body label number.
MASSES
[currently active BODY]
pointi Label number of a geometry point. All nodes coincident with this geometry point are assigned a value equal to the specified concentrated mass divided by the number of nodes. linei Label number of a geometry line. All nodes on this line are assigned a value equal to the specified concentrated mass divided by the number of nodes. surfacei Label number of a geometry surface. All nodes on this surface are assigned a value equal to the specified concentrated mass divided by the number of nodes. volumei Label number of a geometry volume. All nodes in this volume are assigned a value equal to the specified concentrated mass divided by the number of nodes. nodeseti Label number of a node set. All nodes in this node set are assigned a value equal to the specified concentrated mass divided by the number of nodes. edgei Label number of a solid geometry edge (for BODY). All nodes of this entity are assigned a value equal to the specified concentrated mass divided by the number of nodes. facei Label number of a solid geometry face (for BODY). All nodes of this entity are assigned a value equal to the specified concentrated mass divided by the number of nodes. mass1i [0.0] Mass assigned to the geometry entity for the nodal x-translation degree-of-freedom (global or skew). mass2i [0.0] Mass assigned to the geometry entity for the nodal y-translation degree-of-freedom (global or skew). mass3i [0.0] Mass assigned to the geometry entity for the nodal z-translation degree-of-freedom (global or skew).
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MASSES
Sec. 7.3 Element properties
mass4i [0.0] Mass moment of inertia assigned to the geometry entity for the nodal x-rotation degree-offreedom (global or skew). mass5i [0.0] Mass moment of inertia assigned to the geometry entity for the nodal y-rotation degree-offreedom (global or skew). mass6i [0.0] Mass moment of inertia assigned to the geometry entity for the nodal z-rotation degree-offreedom (global or skew). Auxiliary commands LIST MASSES POINTS DELETE MASSES POINTS
facei damp1i damp2i damp3i damp4i damp5i damp6i DAMPERS POINTS assigns concentrated dampers to the nodes at a set of geometry points. DAMPERS LINES assigns concentrated dampers to the nodes on a set of geometry lines. DAMPERS SURFACES assigns concentrated dampers to the nodes on a set of geometry surfaces. DAMPERS VOLUMES assigns concentrated dampers to the nodes on a set of geometry volumes. DAMPERS NODESETS assigns concentrated masses to the nodes in a node set. DAMPERS EDGES assigns concentrated dampers to the nodes on solid geometry edges.
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DAMPERS
Sec. 7.3 Element properties
DAMPERS FACES assigns concentrated dampers to the nodes on a set of solid geometry faces. BODY Body label number.
[currently active BODY]
pointi Label number of a geometry point. All nodes coincident with this geometry point are assigned a value equal to the specified concentrated damper divided by the number of nodes. linei Label number of a geometry line. All nodes on this line are assigned a value equal to the specified concentrated damper divided by the number of nodes. surfacei Label number of a geometry surface. All nodes on this surface are assigned a value equal to the specified concentrated damper divided by the number of nodes. volumei Label number of a geometry volume. All nodes in this volume are assigned a value equal to the specified concentrated damper divided by the number of nodes. nodeseti Label number of a node set. All nodes in this node set are assigned a value equal to the specified concentrated mass divided by the number of nodes. edgei Label number of a geometry edge (for BODY). All nodes on this entity are assigned a value equal to the specified concentrated damper divided by the number of nodes. facei Label number of a geometry face (for BODY). All nodes on this entity are assigned a value equal to the specified concentrated damper divided by the number of nodes. damp1i [0.0] Damper assigned to the geometry entity for the nodal x-translation degree-of-freedom (global or skew). damp2i [0.0] Damper assigned to the geometry entity for the nodal y-translation degree-of-freedom (global or skew). damp3i [0.0] Damper assigned to the geometry entity for the nodal z-translation degree-of-freedom (global ADINA R & D, Inc.
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DAMPERS
Chap. 7 Model definition
or skew). damp4i [0.0] Rotational damper assigned to the geometry entity for the nodal x-rotation degree-of-freedom (global or skew). damp5i [0.0] Rotational damper assigned to the geometry entity for the nodal y-rotation degree-of-freedom (global or skew). damp6i [0.0] Rotational damper assigned to the geometry entity for the nodal z-rotation degree-of-freedom (global or skew). Auxiliary commands LIST DAMPERS POINTS DELETE DAMPERS POINTS
FIRST LAST FIRST LAST
LIST DAMPERS LINES DELETE DAMPERS LINES
FIRST LAST FIRST LAST
LIST DAMPERS SURFACES DELETE DAMPERS SURFACES
FIRST LAST FIRST LAST
LIST DAMPERS VOLUMES DELETE DAMPERS VOLUMES
FIRST LAST FIRST LAST
LIST DAMPERS NODESETS DELETE DAMPERS NODESETS
FIRST LAST FIRST LAST
LIST DAMPERS EDGES DELETE DAMPERS EDGES
FIRST LAST FIRST LAST
LIST DAMPERS FACES DELETE DAMPERS FACES
FIRST LAST FIRST LAST
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SUBSTRUCTURE
SUBSTRUCTURE
Sec. 7.4 Substructure and cyclic symmetry
NAME
The model can consist of a main structure and one or more substructures. This command sets the current substructure. Substructuring cannot be used with - multiple time step blocks - explicit time integration - rigid link constraint equations in substructure nodes, or between substructure nodes and the main structure nodes - potential-based fluid elements - user-supplied elements, user-supplied loading - temperature loading and other loading restrictions (see ADINA Theory and Modeling Guide, Section 11.1.3) - FSI/TMC analysis - cyclic symmetry structures - mapping options - consistent mass damping - 3D-iterative solver, multigrid solver, iterative solver - load penetration - pressure-update (load stiffening effect of shells) - frequency analysis, mode-superposition analysis, response analysis, response spectrum analysis, harmonic analysis and random vibration analysis - linearized buckling analysis NAME [(current highest substructure label number) + 1] Label number of the current substructure. Auxiliary commands LIST SUBSTRUCTURE DELETE SUBSTRUCTURE
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REUSE
Chap. 7 Model definition
REUSE
NAME LOAD-REUSE CONNECT TRANSFORM
slavenamei masternamei typei sbodyi mbodyi connecti transformationi Connects the current substructure to the main structure. As the command name implies, each substructure can be used several times and the command REUSE therefore defines the reuse identifying number for the current substructure. Input data provided to the following commands refers only to the current reuse number of the current substructure: PRINT-STEPS, SET-INITCONDITION, APPLY-LOAD NAME The label number of the reuse.
[(highest reuse label number) + 1]
LOAD-REUSE Loading indicator for the reuse.
[SAME]
SAME
Same loading as for the previous (i.e. NAME-1) reuse of the current substructure.
DIFFERENT
Loading for this reuse of the current substructure is specified by subsequent uses of command APPLY-LOAD.
CONNECT [PARAMETRIC] Default setting for how nodes on substructure are to be connected to nodes on main structure when connection is between geometry lines or surfaces. {PARAMETRIC/MATCHING} Note: When connection is between geometry edges, faces or nodesets, CONNECT=MATCHING is always used. Note: When connection is between lines or surfaces and CONNECT=PARAMETRIC, connection between main structure and substructure is constructed between nodes at the corresponding parametric order on each entity. Parametric order is in the increasing u-parameter direction for lines, increasing u- then v-parameter for surfaces. TRANSFORM [0] Default coordinate transformation system to match nodes for connecting substructure to main structure. When connection is between geometry edges, faces or nodesets, TRANSFORM is always applicable. When connection is between geometry lines or surfaces, TRANSFORM is only applicable if CONNECT=MATCHING. Transformation is defined from the main structure to the substructure. slavenamei The label number of the substructure boundary entity (point, line, surface, edge, face, node or
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REUSE
Sec. 7.4 Substructure and cyclic symmetry
nodeset) for the ith term of the reuse. masternamei The label number of the main structure connection entity (point, line, surface, edge, face, node or nodeset) for the ith term of the reuse. typei The type of entity. {POINT/LINE(EDGE)/SURFACE(FACE)/NODE/NODESET} Note: A connection between main structure and substructure is constructed between nodes at the corresponding parametric order on each entity. Parametric order is in the increasing u-parameter direction for lines, increasing u- then v-parameter for surfaces. In this case the number of nodes on the slave and master geometry entity must be the same. sbodyi [0] Body label number of slave geometry edge (typei=LINE) or face (typei=SURFACE). For geometry line or surface, sbodyi=0 must be specified. For other entities, sbodyi is ignored. mbodyi [0] Body label number of master geometry edge (typei=LINE) or face (typei=SURFACE). For geometry line or surface, mbodyi=0 must be specified. For other entities, mbodyi is ignored. connecti [from parameter CONNECT] Indicates how nodes on substructure are to be connected to nodes on main structure when connection is between geometry line or surface. {PARAMETRIC/MATCHING} transformi [from parameter TRANSFORMATION] Specifies a coordinate transformation system to match nodes for connecting a substructure to the main structure. When connection is between geometry edges, faces or nodesets, transformi is always applicable. When connection is between geometry lines or surfaces, transformi is only applicable if connecti=MATCHING. Transformation is defined from the main structure to the substructure. Auxiliary commands LIST REUSE DELETE REUSE
Specifies parameters that control cyclic symmetry analysis. CYCLICPARTS [1] The number of cyclic symmetric parts of the main structure. If the value is greater than or equal to 2 then a cyclic symmetric analysis is performed. The maximum number of cyclic symmetric parts allowed is 999. CYCLICPARTS = 1 indicates no cyclic symmetry. AXIS-CYCLIC [0] Label number of cyclic symmetry axis defined by axis-rotation command. Default AXISCYCLIC = 0 means use global X axis. PERIODIC Specifies whether the cyclic models are also under periodic symmetry. {NO/YES}
[NO]
NO
No periodic symmetry analysis. A full cyclic symmetry analysis will be performed. Different loads are used for different cyclic parts.
YES
Periodic symmetry analysis. Only the 0 harmonic will be analyzed. Unlike basic cyclic symmetry analysis, a periodic symmetry analysis can be nonlinear. It can also be used with explicit dynamic time integration. The load applied on the first cyclic part is rotated about the cyclic axis and applied to the other cyclic parts.
LOW-HARMONIC Gives the lowest harmonic to use in cyclic symmetry frequency analysis. {0 ≤ LOW-HARMONIC ≤ N/2} where N is the number of cyclic parts.
[0]
HIGH-HARMONIC Gives the highest harmonic to use in cyclic symmetry frequency analysis. {0 ≤ HIGH-HARMONIC ≤ N/2} where N is the number of cyclic parts. HIGH-HARMONIC = DEFAULT sets the value to N/2.
[DEFAULT]
FREQ-HARMONIC Gives the number of frequencies to calculate per harmonic. { ≥ 0}
[0]
FREQ-HALF [NO] This flag which tells the program to only calculate one of every two complex frequency pairs.{NO/YES}
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CYCLIC-CONTROL
Sec. 7.4 Substructure and cyclic symmetry
BOUND-ELEMENT [SINGLE] Specifies whether structural elements lying completely on the cyclic boundary are defined once or twice. Applies to beam, isobeam, plate and shell elements. {SINGLE/DOUBLE} SINGLE Structural elements completely on the cyclic boundary will only be defined once by the user. The elements may be defined on either the master or the slave cyclic boundaries, but not both. Some elements can be defined on the slave boundary and others on the master. DOUBLE Structural elements completely on the cyclic boundary will be define twice by the user, once on each cyclic boundary. ADINA will handle the stiffness/mass matrix modifications required for proper solution.
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CYCLICLOADS
CYCLICLOADS
Sec. 7.4 Substructure and cyclic symmetry
NAME
A cyclic symmetry analysis can be performed by defining the finite element discretization of the fundamental part of the geometrically cyclic symmetric structure. This fundamental part is rotated M times about a cyclic axis to represent the complete structure. CYCLICLOADS indicates that the loads subsequently defined are to be on a particular one of these M parts. NAME Label number of the cyclic part to be loaded. Auxiliary commands LIST CYCLICLOADS DELETE CYCLICLOADS
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CYCLICBOUNDARY
Chap. 7 Model definition
CYCLICBOUNDARY
POINTS / LINES / SURFACES / NODES / NODESET
slavenamei masternamei CYCLICBOUNDARY is used to associate cyclic boundaries (defined by points, lines, surfaces, nodes, or nodesets) with each other. The command specifies the cyclic boundaries of the fundamental part of a cyclicaly symmetric structure termed the master cyclic boundary and the slave cyclic boundary. When the nodes on the master cyclic boundary are rotated 360/M (where M is the number of cyclic parts) degrees counter clockwise about the cyclic symmetry axis, they should coincide with the nodes on the slave cyclic boundary. slavenamei The label number of the slave entity (point, line, surface, node, or nodeset) for the “i”th term of the cyclic boundary. masternamei The label number of the master entity (point, line, surface, node, or nodeset) for the “i”th term of the cyclic boundary.
Slave cyclic boundary o
360 M
Cyclic symmetry axis (Default: X axis)
Fundamental cyclic part
Master cyclic boundary
Note: When cyclic boundaries are based on geometric entities, the number of nodes on both the master and slave geometries must be the same. The cyclic boundaries are not restricted to straight lines and flat surfaces. Auxiliary commands LIST CYCLICBOUNDARY POINTS / LINES / SURFACES / NODES / NODESET DELETE CYCLICBOUNDARY POINTS / LINES / SURFACES / NODES / NODESET MASTER ... AXIS-CYCLIC PERIODIC
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CYCLICBOUNDARY TWO-D
CYCLICBOUNDARY
Sec. 7.4 Substructure and cyclic symmetry
TWO-D
slavenamei sbody masternamei mbody CYCLICBOUNDARY TWO-D is used to associate cyclic boundaries with each other (defined by lines or edges).The command specifies the cyclic boundary nodes of the fundamental part of a cyclically symmetric structure. The cyclic boundaries of the fundamental part consist of two sets of lines or edges, namely, the cyclic boundary 1 (master cyclic boundary) and the cyclic boundary 2 (slave cyclic boundary).
Slave cyclic boundary o
360 M
Cyclic symmetry axis (Default: X axis)
Fundamental cyclic part
Master cyclic boundary
slavenamei The label number of the geometry slave entity (line or edge) for the “i”’th independent term of the cyclic boundary. sbody Geometry body label of slave edge. masternamei The label number of the geometry master entity (line or edge) for the “i”’th independent term of the cyclic boundary. mbody Geometry body label of master edge. Auxiliary commands LIST CYCLICBOUNDARY TWO-D DELETE CYCLICBOUNDARY TWO-D MASTER ... AXIS-CYCLIC PERIODIC
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CYCLICBOUNDARY
CYCLICBOUNDARY THREE-D
THREE-D
slavenamei sbody masternamei mbody Command CYCLICBOUNDARY THREE-D is used to associate cyclic boundaries with each other (defined by surfaces or faces).The command specifies the cyclic boundary nodes of the fundamental part of a cyclically symmetric structure. The cyclic boundaries of the fundamental part consist of two sets of surfaces or faces, namely, the cyclic boundary 1 (master cyclic boundary) and the cyclic boundary 2 (slave cyclic boundary).
Slave cyclic boundary o
360 M
Cyclic symmetry axis (Default: X axis)
Fundamental cyclic part
Master cyclic boundary
slavenamei The label number of the geometry slave entity (line or edge) for the “i”’th independent term of the cyclic boundary. sbody Geometry body label of slave edge. masternamei The label number of the geometry master entity (line or edge) for the “i”’th independent term of the cyclic boundary. mbody Geometry body label of master edge. Auxiliary commands LIST CYCLICBOUNDARY THREE-D DELETE CYCLICBOUNDARY THREE-D MASTER ... AXIS-CYCLIC PERIODIC
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AXIS-ROTATION
Sec. 7.4 Substructure and cyclic symmetry
AXIS-ROTATION
NAME MODE SYSTEM AXIS ALINE AP1 AP2 X0 Y0 Z0 XA YA ZA
Defines a rotational axis which can be referenced by other commands. NAME Label number of the axis.
[(current highest axis label number) + 1]
MODE [AXIS] Selects the method used to define the axis. The parameters (parenthesized) used to define the axis depends on the method selected. AXIS -
The rotational axis is defined by a coordinate axis of a coordinate system. (SYSTEM, AXIS)
LINE -
The rotational axis is defined by a straight line between the end points of a geometry line (which is not necessarily straight, but must be open - i.e., have non-coincident end points). (ALINE)
POINTS -
The rotational axis is defined by a straight line between two non-coincident geometry points. (AP1, AP2)
VECTOR -
The rotational axis is defined by the coordinate position and direction of a vector. (X0, Y0, Z0, XA, YA, ZA)
SYSTEM [current active coordinate system] Label number of a coordinate system. One of the axes of this coordinate system may be used to define the rotational axis, via parameter AXIS, when MODE = AXIS. AXIS [XL] Selects the axis of the coordinate system, given by parameter SYSTEM, to be used as the axis of rotation. {XL/YL/ZL} ALINE Label number of the geometry line used to define the rotational axis. The direction of the axis is taken from the start point of the line to the end point of the line. AP1, AP2 Label numbers of the geometry points used to define the rotational axis. The direction of the axis is taken from point AP1 to point AP2.
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AXIS-ROTATION
X0, Y0, Z0 [0.0, 0.0, 0.0] The coordinates (in global coordinates) of the starting position of the vector that defines the rotational axis. XA, YA, ZA [1.0, 0.0, 0.0] The direction (in global coordinates) of the vector that defines the rotational axis. Auxiliary commands LIST AXIS-ROTATION DELETEAXIS-ROTATION
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EG-SUBSTRUCTURE
EG-SUBSTRUCTURE
Sec. 7.4 Substructure and cyclic symmetry
NEG
substructurei egi Creates substructures as sets of existing element groups. NEG The maximum number of element groups to be allocated to one substructure.
[1]
substructurei Label number of a new substructure. egi Label number of element group in main structure.
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ANALYTICAL-RIGID-TARGET
ANALYTICAL-RIGID-TARGET
ANALYTICAL X0 Y0 Z0 RADIUS GTYPE GNAME
Command ANALYTICAL-RIGID-TARGET defines parameters for analytical rigid target contact analysis. Note: This command is only available for node-to-node contact (i.e., NODETONODE=YES in the CGROUP CONTACT... command). ANALYTICAL Analytical rigid target type: NONE
Analytical rigid target is not used.
PLANE
Infinite plane.
SPHERE
Sphere (3D), or circle (2D).
CYLINDER
Infinite cylinder.
[NONE]
X0 Y0 Z0 Global cartesian component of:
[0.0] [0.0] [0.0]
- initial plane normal verctor inside the target body (ANALYTICAL=PLANE). - initial cylinder axis verctor (ANALYTICAL=CYLINDER). RADIUS [0.0] Radius of sphere (ANALYTICAL=SPHERE) or cylinder (ANALYTICAL=CYLINDER). GTYPE Geometry type for reference node: node or point. {NODE/POINT}
[POINT]
GNAME Label number of reference node or point. An existing label number must be specified. Auxiliary commands LIST ANALYTICAL-RIGID-TARGET
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Specifies certain parameters controlling the behavior of the algorithms used in modeling contact. For further details on these parameters, please consult the Theory and Modeling Guide. CONTACT-ALGORITHM [CONSTRAINT-FUNCTION] Selects the default algorithm used to solve contact problems in implicit analysis. {CONSTRAINT-FUNCTION / SEGMENT-METHOD / RIGID-TARGET} XCONT-ALGORITHM [KINEMATIC-CONSTRAINT] Selects the default algorithm used to solve contact problems in explicit analysis. {KINEMATIC-CONSTRAINT / PENALTY / EXPLICIT-RIGID-TARGET} DISPLACEMENT [LARGE] Specifies the default displacement formulation used for contact analysis. A different formulation may be selected for each individual contact group via the CGROUP command. {LARGE/ SMALL} LARGE
Large displacement is assumed for contact where the contact search is performed in each iteration to generate new contact constraints.
SMALL
Small displacement is assumed for contact. The contact constraints are generated once in the beginning of the analysis and kept constant throughout the analysis.
NSUPPRESS [0] Indicates the number of iterations for which previous target segments are stored for contactor nodes -- in order to suppress oscillation between adjacent segments. Such oscillation can occur when a contactor node approaches the junction between two adjacent target segments. Use of NSUPPRESS > 0 allows for such oscillation to be detected and eliminated. NSUPPRESS = 0 (the default) indicates that no such checking and associated storage is required. {≥ 0} For NSUPPRESS >0, ADINA stores all target segments that have previously (during equilibrium iterations) come into contact with a contactor node. To limit the amount of memory required, NSUPPRESS is limited to a maximum value of 99.
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CONTACT-CONTROL
Notes: 1 NSUPPRESS has no effect if the node-to-node contact algorithm is used. 2 NSUPPRESS should be less than the maximum number of equilibrium iterations. DAMPING [NO] Indicates whether damping stabilization is applied for contact analysis. This feature is generally useful when rigid body motion exists in a model. {NO/INITIAL/CONSTANT} INITIAL
Damping is applied at the first time step only. The specified damping coefficients are applied and ramped down to zero by the end of the first time step.
CONSTANT
The specified damping coefficients are applied at all time steps.
DAMP-NORMAL Specified the normal damping coefficient. { ≥ 0.0 }
[0.0]
DAMP-TANGENTIAL Specified the tangential damping coefficient. { ≥ 0.0 }
[0.0]
TENSION-CONSISTENT [NO] Specifies whether to allow tensile consistent contact forces (quadratic 3D elements only). {YES/NO} CSTYPE Selects the type of contact segment to use. {OLD/NEW} OLD
Use the old contact segment.
NEW
Use the new contact segment.
FRICTION-ALGORITHM Selects which friction algorithm is used in the solution. {V83/CURRENT}
[NEW]
[CURRENT]
POST-IMPACT [YES] Indicates whether the post-impact correction of velocities and accelerations is performed along with the displacement constraint in dynamic contact problems. {YES/NO} RT-SUBD [MAGNITUDE] Selects the subdivision scheme used in the rigid-target algorithm when the tensile contact force (and penetration if selected) is too large. Used only for the rigid-target contact algorithm of version 8.3. {MAGNITUDE/ATS}
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CONTACT-CONTROL
Sec. 7.5 Contact conditions
MAGNITUDE Subdivision is based on the magnitude of the tensile contact force (and penetration), i.e., the larger the magnitude, the smaller will be the subdivided time step size. ATS
Subdivision is based on the global automatic time stepping (ATS) subdivsion settings.
SEGMENT-INNER-ITERATION [YES] Indicates whether the inner iteration loop is to be performed for the segment method contact algorithm. {YES/NO} RT-ALGORITHM [CURRENT] Selects the rigid-target contact algorithm. Details are in Chapter 4 of the ADINA Theory and Modeling Guide. {V83/CURRENT} V83
Use the rigid-target contact algorithm of ADINA version 8.3 and earlier
CURRENT
Use the rigid-target contact algorithm of the current ADINA version.
Auxiliary commands LIST CONTACT-CONTROL
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CGROUP CONTACT2
Sec. 7.5 Contact conditions
CGROUP CONTACT2 This command is split, for better readability, based on the contact algorithm. There are 6 possibilities: Implicit analysis 1. Constraint Function Algorithm - ALGORITHM=CONSTRAINT-FUNCTION - ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACTCONTROL)=CONSTRAINT-FUNCTION 2. Segment Method Algorithm - ALGORITHM=SEGMENT - ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACTCONTROL)=SEGMENT 3. Rigid Target Algorithm - ALGORITHM=RIGID-TARGET - ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACTCONTROL)=RIGID-TARGET Explicit analysis 4. Kinematic Constraint Algorithm - XALGORITHM=KINEMATIC-CONSTRAINT - XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACTCONTROL)= KINEMATIC-CONSTRAINT 5. Penalty Algorithm - XALGORITHM=PENALTY - XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACTCONTROL)=PENALTY 6. Rigid Target Algorithm - XALGORITHM=EXPLICIT-RIGID-TARGET - XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACTCONTROL)=EXPLICIT-RIGID-TARGET Note that: - Algorithms #1, #2, #4 support node-to-node contact (the default is node-tosegment) via parameter NODETONODE=YES. - Algorithms #1, #2 support tied contact via parameter TIED=SMALL Auxiliary Commands LIST CGROUP2 FIRST LAST DELETE CGROUP2 FIRST LAST NODES
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CGROUP CONTACT2
NODES = YES (the default) will remove nodes which were only attached to contact segments in the deleted contact group. The summary of parameters applicable for each contact algorithm is presented in two tables following the command descriptions for the 3D contact command (CGROUP CONTACT3). One table is for implicit analysis and the other for explicit analysis.
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CGROUP CONTACT2
Sec. 7.5 Contact conditions
Case 1: Implicit – Constraint Function Algorithm CGROUP CONTACT2
Activated when: - ALGORITHM=CONSTRAINT-FUNCTION - ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACTCONTROL)=CONSTRAINT-FUNCTION The following superscripts are used for some of the parameters: 1. 2.
Only applicable to (the default) node-to-segment contact Only applicable to node-to-node contact
The absence of a superscript indicates general applicability. The CGROUP parameters are divided into 3 subgroups: Basic, Advanced, and Multiphysics: Basic parameters NAME [(current highest contact group label number) + 1] Label number of the contact group to be defined. ALGORITHM [DEFAULT] Selects the contact algorithm for current group if the analysis is implicit. If DEFAULT is selected the algorithm type is determined based on the CONTACT-ALGORITHM parameter of the MASTER command. See comment above for activating the current contact algorithm. {DEFAULT/ CONSTRAINT-FUNCTION/ SEGMENT-METHOD/ RIGID-TARGET} NODETONODE [NO] Indicates whether node-to-segment or node-to-node contact algorithm is used by the contact group. {YES/NO}
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CGROUP CONTACT2
- Use node-to-segment contact - Use node-to-node contact
NO YES
DISPLACEMENT 1 [DEFAULT] Specifies the displacement formulation used for this contact group. {DEFAULT/LARGE/ SMALL} DEFAULT
-
LARGE
-
SMALL
-
The displacement formulation specified in the CONTACT-CONTROL command is used. Large displacement is assumed for contact where the contact search is performed in each iteration to generate new contact constraints. Small displacement is assumed for contact. The contact constraints are generated once in the beginning of the analysis and kept constant throughout the analysis.
FRICTION [0.0] Default coefficient of Coulomb friction. FRICTION = 0.0 indicates frictionless contact. Contact pairs can set their own friction coefficient. CFACTOR1 Compliance factor for all contact surfaces in this contact group. {≥ 0.0}
[0.0]
DEPTH 1 [0.0] If DEPTH > 0.0, then penetration is detected when the penetration depth is less than or equal to DEPTH, and if the penetration distance is greater than DEPTH, penetration is deemed not to occur. TIED1 Indicates the type of TIED contact. This parameter is ignored when PENETRATIONALGORITHM = TWO. {NO/SMALL}
[NO]
NO - No TIED contact. SMALL - Small displacement is used in TIED contact. TIED-OFFSET 1 [0.0] If TIED = SMALL, contactor nodes are tied to target if the gap between them is less than or equal to this parameter. This parameter is ignored when TIED = NO. OFFSET [0.001] Two contact surfaces are constructed for each defined contact surface, each contact surface placed a distance OFFSET from the defined contact surface. { ≥ 0.0} Note:
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CGROUP CONTACT2
Sec. 7.5 Contact conditions
contact surface, a different offset distance can be specified using the command CS-OFFSET. OFFSET-TYPE [CONSTANT] Specifies the type of offset to be used for contact surfaces belonging to this group. {CONSTANT/TRUE/NONE} CONSTANT - Constant offset as specified by the parameter OFFSET is used. See note under OFFSET. TRUE - The actual shell half thickness is used as the offset distance even for large strains. NONE - No offset is used (regardless of the value of the parameter OFFSET). FORCES 1 [YES] Indicates whether or not concentrated contact nodal forces are calculated for every contact surface node of this contact group. The contact forces are evaluated with respect to the global Cartesian coordinate system. {YES/NO} Note: - If NODETONODE = YES, nodal forces are always calculated and this parameter is ignored. - The combination FORCES = NO, TRACTIONS = NO is not permitted. TRACTIONS 1 [YES] Indicates whether or not contactor segment tractions (and concentrated contact nodal forces at solitary nodes in contact) are calculated for every contactor surface of this contact group. {YES/NO} Note:
The combination FORCES = NO, TRACTIONS = NO is not permitted.
CONTINUOUS-NORMAL 1
[YES if PENETRATION = ONE] [NO if PENETRATION = TWO] Indicates whether or not a continuous (interpolated) contact segment normal is to be used for contact surfaces in the contact group. {YES/NO}
DIRECTION 2 [NORMAL] Specifies the vector used to describe the normal direction for a nodal pair in node-to-node contact. {NORMAL/VECTOR} NORMAL - Use the normal vector inside the target body. VECTOR - Use the vector connecting target and contactor nodes.
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CGROUP CONTACT2
Advanced parameters TBIRTH 1 [0.0] TDEATH 1 [0.0] The birth and death times for the whole contact group. If TBIRTH=0.0 and TDEATH=0.0, the birth and death feature is not used. INITIAL-PENETRATION1 Initial contactor node penetration flag. {ALLOWED/PRINT/DISCARDED/GAP-OVERRIDE}
[ALLOWED]
- Any initial penetration of a contactor node into a target surface is eliminated either in the first solution step or over a specified time interval (see TIME-PENETRATION parameter). In successive steps each contactor node cannot penetrate. PRINT - Same as ALLOWED, but a printout of the penetrating contactor nodes is produced. DISCARDED - Any initial penetration of a contactor node into a target surface is not eliminated in the first solution step. In successive steps each contactor node is allowed to penetrate up to the initial penetration. GAP-OVERRIDE - Initial penetrations or gaps are overridden by user-specified GAPVALUE parameter. ALLOWED
TIME-PENETRATION 1 Specifies the time used to eliminate any initial penetration. {≥ 0.0}
[0.0]
If INITIAL-PENETRATION = ALLOWED or PRINT, and TIME-PENETRATION=0.0, then the initial penetration is eliminated in the first time step. By specifying TIME-PENETRATION > 0.0, initial penetration can be eliminated gradually. This may help in the convergence of the solution. GAP-VALUE 1 [0.0] Specifies a constant gap distance between the contactor and target surfaces when INITIALPENETRATION = GAP-OVERRIDE. This value overrides the value measured from the contact surfaces. A negative GAP-VALUE means initial penetrations which will be eliminated. CS-EXTENSION 1 The maximum non-dimensional extension of target contact surfaces. {0.0 < CS-EXTENSION < 0.1}
[0.001]
EPSN [0.0] The normal contact w-function εΝ parameter. Guidelines for choosing this parameter are provided in the ADINA-AUI Online Help. When EPSN = 0.0, ADINA automatically determines this parameter. 7-248
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Sec. 7.5 Contact conditions
EPST [0.0] The friction contact v-function εT parameter. Guidelines for choosing this parameter are provided in the ADINA-AUI Online Help. When EPST = 0.0, ADINA automatically sets it to 0.001. CONSISTENT-STIFF 1 [DEFAULT] Indicates whether consistent contact stiffness is used. {DEFAULT/OFF/ON} When CONSISTENT-STIFF = DEFAULT, consistent contact stiffness is used if the following conditions are all satisfied: - the skyline direct equation solver is not used, i.e., SOLVER is not set to SKYLINE in the MASTER command, - CONTINUOUS-NORMAL = NO is specified. - Old contact surfaces are used (CSTYPE=OLD in CONTACT-CONTROL command). Otherwise, the default is set to off. Note that this option is not used in small displacement analysis (DISPLACEMENT=SMALL in the KINEMATICS command). It is also not used if small displacements are selected in the contact group (DISPLACEMENT parameter). The use of consistent contact stiffness increases the size of the stiffness matrix. However, it can improve the convergence rate in contact problems, especially in cases where the normal vector between the contacting surfaces frequently changes direction during the analysis. FRIC-DELAY [NO] Indicates whether the application of friction is delayed, i.e., applied one time step after contact is established. {NO/YES} USER-FRICTION 1 [NO] Indicates whether a user-supplied friction law is used for this contact group. If USERFRICTION=YES is specified, additional parameters for defining the user-supplied friction law can be input using the USER-FRICTION command. {YES/NO} SUBTYPE [DEFAULT] Indicates the type of CONTACT2 contact-surfaces, all defined in the global YZ plane. {DEFAULT/AXISYMMETRIC/STRAIN/STRESS} DEFAULT - Subtype automatically determined based on underlying elements. AXISYMMETRIC - Axisymmetric contact-surfaces. The global Z axis is that of rotational symmetry, and Y is the radial direction (Y ≥ 0). STRAIN - Planar contact-surfaces. STRESS - Planar contact-surfaces (identical to STRAIN).
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CGROUP CONTACT2
Multiphysics parameters HHATTMC1 [0.0] Contact heat transfer coefficient used for thermo-mechanical coupling (TMC) analysis. { ≥ 0.0} [0.5] FCTMC 1 Friction contact heat distribution fraction coefficient for contactor used for thermo-mechanical coupling (TMC) analysis. {0.0 ≤ FCTMC ≤ 1.0} FTTMC 1 [0.5] Friction contact heat distribution fraction coefficient for target used for thermo-mechanical coupling (TMC) analysis. {0.0 ≤ FTTMC ≤ 1.0} EKTMC1 [0.0] Electrical conductivity for current flow through contact surfaces in a thermo-mechanical coupling (TMC) analysis. (Units: electrical conductance/length, e.g., Siemens/m) {≥ 0.0}
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CGROUP CONTACT2
Sec. 7.5 Contact conditions
Case 2: Implicit – Segment Method Algorithm CGROUP CONTACT2
Activated when: - ALGORITHM=SEGMENT-METHOD - ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACTCONTROL)=SEGMENT-METHOD All the parameters for the Segment Method Algorithm are described in Case 1: Implicit Constraint Function Algorithm
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Case 3: Implicit - Rigid Target Algorithm CGROUP CONTACT2
Activated when: - ALGORITHM=RIGID-TARGET - ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACT-CONTROL)= RIGID-TARGET Note: This algorithm is equivalent to the Old 3D Implicit Rigid Target Algorithm. For the following parameters, see description for Case 1: Implicit - Constraint Function Algorithm NAME ALGORITHM FRICTION DEPTH TBIRTH TDEATH SUBTYPE NORMAL-STIFFNESS Contact stiffness in direction normal to the contact surface. TANGENTIAL-STIFFNESS Contact stiffness in direction tangential to the contact surface.
[1.0E11]
[0.0]
PTOLERANCE [1.0E-8] Maximum allowable penetration of target surface. If penetration is less than PTOLERANCE, contact is assumed to be not yet established for the node in consideration. OFFSET [0.0] The actual contact surface is raised a distance OFFSET away from the surface defined by the nodes. { ≥ 0.0} OFFSET-TYPE [CONSTANT] Specifies the type of offset to be used for contact surfaces belonging to this group. {CONSTANT/TRUE}
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CONSTANT - Constant offset as specified by the parameter OFFSET is used. TRUE - The actual shell half thickness is used as the offset distance even for large strains. RESIDUAL-FORCE [0.001] Minimum tensile contact force required to change state of a contact node from "node in contact" to "free node". If the normal component of a tensile contact force is less than RESIDUAL-FORCE, a "node in contact" remains in contact. If the normal tensile force is greater than RESIDUAL-FORCE, a "node in contact" becomes a "free node". LIMIT-FORCE [1.0] Limit (maximum) for the sum of all contact forces for nodes changing from the state of "node in contact" to "free node". If the absolute value of the sum of the forces is bigger than LIMIT-FORCE, then the automatic time stepping (ATS) method will be activated to subdivide the current time step into smaller time increments. ITERATION-LIMIT [2] Maximum number of ATS time step subdivisions due to LIMIT-FORCE criterion described above. RTP-CHECK [NO] Specifies whether penetration is checked (in addition to checking the tensile contact force) against the maximum allowable penetration when the rigid-target algorithm is used. {NO/ RELATIVE/ABSOLUTE} NO
-
RELATIVE
-
ABSOLUTE
-
Penetration is not checked. Note that with this setting, there is a possibility that the rigid target surface may excessively penetrate the contactor surface. Penetration is checked and RTP-MAX is specified as a factor of the overall model size. Penetration is checked and RTP-MAX is the absolute value of penetration allowed.
Note that if penetration check is selected, the program will perform subdivision of time steps if the penetration exceeds the maximum allowable penetration. The subdivision scheme is specified in the RT-SUBD parameter in the CONTACT-CONTROL command. RTP-MAX [0.001] Specifies the maximum allowable penetration when the rigid target algorithm is used. RTP-MAX is either a factor of the model size or an absolute value depending on the RTP-CHECK parameter. {> 0.0}
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CGROUP CONTACT2
SUBTYPE [DEFAULT] Indicates the type of CONTACT2 contact-surfaces, all defined in the global YZ plane. {DEFAULT/AXISYMMETRIC/STRAIN/STRESS} DEFAULT - Subtype automatically determined based on underlying elements. AXISYMMETRIC - Axisymmetric contact-surfaces. The global Z axis is that of rotational symmetry, and Y is the radial direction (Y ≥ 0). STRAIN - Planar contact-surfaces. STRESS - Planar contact-surfaces (identical to STRAIN). RIGID-TARGET (obsolete) [NO] Indicates whether rigid target contact algorithm is used for current contact group. It is preferable to set ALGORITHM instead. {NO/YES}
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Case 4: Explicit - Kinematic Constraint Algorithm CGROUP CONTACT2
NAME XALGORITHM NODETONODE DISPLACEMENT FRICTION DEPTH OFFSET OFFSET-TYPE FORCES TRACTIONS DIRECTION TBIRTH TDEATH INITIAL-PENETRATION TIME-PENETRATION GAP-VALUE CS-EXTENSION SUBTYPE
Activated when: - XALGORITHM=KINEMATIC-CONSTRAINT - XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-CONTROL)= KINEMATIC-CONSTRAINT The following superscripts are used for some of the parameters: 1. 2.
Only applicable to (the default) node-to-segment contact Only applicable to node-to-node contact
The absence of a superscript indicates general applicability. The CGROUP parameters are divided into 2 subgroups: Basic and Advanced. Basic parameters NAME [(current highest contact group label number) + 1] Label number of the contact group to be defined. XALGORITHM [DEFAULT] Selects the contact algorithm for current group if the analysis is explicit. If DEFAULT is selected the algorithm type is determined based on XCONT-ALGORITHM variable of the CONTACT-CONTROL command. See comment above for activating the current contact algorithm. {DEFAULT/KINEMATIC-CONSTRAINT/PENALTY/EXPLICIT-RIGID-TARGET} NODETONODE [NO] Indicates whether node-to-segment or node-to-node contact algorithm is used by the contact group. {YES/NO} NO YES
- Use node-to-segment contact - Use node-to-node contact
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DISPLACEMENT 1 [DEFAULT] Specifies the displacement formulation used for this contact group. {DEFAULT/LARGE/ SMALL} DEFAULT
-
LARGE
-
SMALL
-
The displacement formulation specified in the CONTACT-CONTROL command is used. Large displacement is assumed for contact where the contact search is performed in each iteration to generate new contact constraints. Small displacement is assumed for contact. The contact constraints are generated once in the beginning of the analysis and kept constant throughout the analysis.
FRICTION [0.0] Default coefficient of Coulomb friction. FRICTION = 0.0 indicates frictionless contact. Contact pairs can set their own friction coefficients. DEPTH 1 [0.0] If DEPTH > 0.0, then penetration is detected when the penetration depth is less than or equal to DEPTH, and if the penetration distance is greater than DEPTH, penetration is deemed not to occur. OFFSET [0.001] Two contact surfaces are constructed for each defined contact surface, each contact surface placed a distance OFFSET from the defined contact surface. { ≥ 0.0} Note:
The OFFSET parameter specifies the default offset distance. For each individual contact surface, a different offset distance can be specified using the command CS-OFFSET.
OFFSET-TYPE [CONSTANT] Specifies the type of offset to be used for contact surfaces belonging to this group. {CONSTANT/TRUE/NONE} CONSTANT - Constant offset as specified by the parameter OFFSET is used. See note under OFFSET. TRUE - The actual shell half thickness is used as the offset distance even for large strains. NONE - No offset is used (regardless of the value of the parameter OFFSET). FORCES 1 [YES] Indicates whether or not concentrated contact nodal forces are calculated for every contact surface node of this contact group. The contact forces are evaluated with respect to the global Cartesian coordinate system. {YES/NO}
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Note: - If NODETONODE = YES, nodal forces are always calculated and this parameter is ignored. - The combination FORCES = NO, TRACTIONS = NO is not permitted. TRACTIONS 1 [YES] Indicates whether or not contactor segment tractions (and concentrated contact nodal forces at solitary nodes in contact) are calculated for every contactor surface of this contact group. {YES/NO} Note:
The combination FORCES = NO, TRACTIONS = NO is not permitted.
DIRECTION 2 [NORMAL] Specifies the vector used to describe the normal direction for a nodal pair in node-to-node contact. {NORMAL/VECTOR} NORMAL - Use the normal vector inside the target body. VECTOR - Use the vector connecting target and contactor nodes. Advanced parameters TBIRTH 1 [0.0] TDEATH 1 [0.0] The birth and death times for the whole contact group. If TBIRTH=0.0 and TDEATH=0.0, the birth and death feature is not used. INITIAL-PENETRATION1 Initial contactor node penetration flag. {ALLOWED/PRINT/DISCARDED/GAP-OVERRIDE}
[ALLOWED]
- Any initial penetration of a contactor node into a target surface is eliminated either in the first solution step or over a specified time interval (see TIME-PENETRATION parameter). In successive steps each contactor node cannot penetrate. PRINT - Same as ALLOWED, but a printout of the penetrating contactor nodes is produced. DISCARDED - Any initial penetration of a contactor node into a target surface is not eliminated in the first solution step. In successive steps each contactor node is allowed to penetrate up to the initial penetration. GAP-OVERRIDE - Initial penetrations or gaps are overridden by user-specified GAPVALUE parameter. ALLOWED
TIME-PENETRATION 1 Specifies the time used to eliminate any initial penetration. {≥ 0.0}
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If INITIAL-PENETRATION = ALLOWED or PRINT, and TIME-PENETRATION=0.0, then the initial penetration is eliminated in the first time step. By specifying TIME-PENETRATION > 0.0, initial penetration can be eliminated gradually. This may help in the convergence of the solution. GAP-VALUE 1 [0.0] Specifies a constant gap distance between the contactor and target surfaces when INITIALPENETRATION = GAP-OVERRIDE. This value overrides the value measured from the contact surfaces. A negative GAP-VALUE means initial penetrations which will be eliminated. CS-EXTENSION 1 The maximum non-dimensional extension of target contact surfaces. {0.0 < CS-EXTENSION < 0.1}
[0.001]
SUBTYPE [DEFAULT] Indicates the type of CONTACT2 contact-surfaces, all defined in the global YZ plane. {DEFAULT/AXISYMMETRIC/STRAIN/STRESS} DEFAULT - Subtype automatically determined based on underlying elements. AXISYMMETRIC - Axisymmetric contact-surfaces. The global Z axis is that of rotational symmetry, and Y is the radial direction (Y ≥ 0). STRAIN - Planar contact-surfaces. STRESS - Planar contact-surfaces (identical to STRAIN).
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Case 5: Explicit – Penalty Algorithm CGROUP CONTACT2
XALGORITHM=PENALTY XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-CONTROL)= PENALTY
For the following parameters, see description for Case 4: Explicit - Kinematic constraint algorithm NAME XALGORITHM DISPLACEMENT FRICTION DEPTH OFFSET OFFSET-TYPE FORCES TRACTIONS TBIRTH TDEATH INITIAL-PENETRATION TIME-PENETRATION GAP-VALUE CS-EXTENSION SUBTYPE XKN-CRIT Criterion for evaluation of normal penalty stiffness. {GLOBAL/USER} GLOBAL USER
[GLOBAL]
- Penalty stiffness will be determined globally for the whole contact group. - The user sets the penalty stiffness.
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XK-NORMAL [0.0] The normal stiffness. It must be greater than 0.0. It is only used for XKN-CRIT=USER. XKT-CRIT Criterion for evaluation of tangential penalty stiffness. {GLOBAL/USER} GLOBAL USER
[GLOBAL]
- Penalty stiffness will be determined globally for the whole contact group. - The user sets the penalty stiffness.
XK-TANGENT [0.0] The tangetial stiffness. It must be greater than 0.0. It is only used for XKT-CRIT=USER. XDAMP [NO] Indicates whether normal damping (proportional to the rate of penetration) is used.{NO/ RELATIVE/ABSOLUTE} NO RELATIVE
-
ABSOLUTE
-
Damping is not used, i.e., XNDAMP parameter is ignored. Damping is used and XNDAMP is a factor of the critical damping, i.e., the normal contact damping coefficient is given by XNDAMP multiplied by the critical damping. This is the recommended choice if damping is used. Damping is included and the normal contact damping coefficient is specified directly by XNDAMP.
XNDAMP [0.1] Specifies the relative or absolute normal damping coefficient (for normal penalty stiffness). { ≥ 0.0}
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Case 6: Explicit – Rigid Target Algorithm CGROUP CONTACT2
Activated when: XALGORITHM=EXPLICIT-RIGID-TARGET XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-CONTROL)= EXPLICIT-RIGID-TARGET Note: This algorithm is equivalent to the old 3D Rigid Target Algorithm. For the following parameters, see description for Case 5: Explicit - Kinematic constraint algorithm NAME XALGORITHM FRICTION DEPTH TBIRTH TDEATH SUBTYPE NORMAL-STIFFNESS Contact stiffness in direction normal to the contact surface. TANGENTIAL-STIFFNESS Contact stiffness in direction tangential to the contact surface.
[1.0E11]
[0.0]
PTOLERANCE [1.0E-8] Maximum allowable penetration of target surface. If penetration is less than PTOLERANCE, contact is assumed to be not yet established for the node in consideration. OFFSET [0.0] The actual contact surface is raised a distance OFFSET away from the surface defined by the nodes. { ≥ 0.0} OFFSET-TYPE [CONSTANT] Specifies the type of offset to be used for contact surfaces belonging to this group. {CONSTANT/TRUE}
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CONSTANT - Constant offset as specified by the parameter OFFSET is used. See note under OFFSET. TRUE - The actual shell half thickness is used as the offset distance even for large strains. SUBTYPE [DEFAULT] Indicates the type of CONTACT2 contact-surfaces, all defined in the global YZ plane. {DEFAULT/AXISYMMETRIC/STRAIN/STRESS} DEFAULT - Subtype automatically determined based on underlying elements. AXISYMMETRIC - Axisymmetric contact-surfaces. The global Z axis is that of rotational symmetry, and Y is the radial direction (Y ≥ 0). STRAIN - Planar contact-surfaces. STRESS - Planar contact-surfaces (identical to STRAIN). RIGID-TARGET (obsolete) [NO] Indicates whether rigid target contact algorithm is used for current contact group. It is preferable to set XALGORITHM instead. {NO/YES}
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CGROUP CONTACT3
CGROUP CONTACT3 This command is split, for better readability, based on the contact algorithm. There are 8 possibilities: Implicit analysis 1. Constraint Function Algorithm - ALGORITHM=CONSTRAINT-FUNCTION - ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACTCONTROL)=CONSTRAINT-FUNCTION 2. Segment Method Algorithm - ALGORITHM=SEGMENT - ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACTCONTROL)=SEGMENT 3. Rigid Target Algorithm - ALGORITHM=RIGID-TARGET - ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACTCONTROL)=RIGID-TARGET 4. Old Rigid Target Algorithm (version 8.3 – now obsolete) - Same as Case #3 with RT-ALGORITHM (in CONTACT-CONTROL)=V83 Explicit analysis 5. Kinematic Constraint Algorithm - XALGORITHM=KINEMATIC-CONSTRAINT - XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACTCONTROL)= KINEMATIC-CONSTRAINT 6. Penalty Algorithm - XALGORITHM=PENALTY - XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACTCONTROL)=PENALTY 7. Rigid Target Algorithm - XALGORITHM=EXPLICIT-RIGID-TARGET - XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACTCONTROL)=EXPLICIT-RIGID-TARGET 8. Old Rigid Target Algorithm (version 8.3 – now obsolete) - Same as Case #7 with RT-ALGORITHM (in CONTACT-CONTROL)=V83 Note that: - Algorithms #1, #2, #5 support node-to-node contact (the default is node-tosegment) via parameter NODETONODE=YES. - Algorithms #1, #2 support tied contact via parameter TIED=SMALL - Algorithms #1, #2, #5, #6 support double-sided contact via parameter PENETRATION-ALGORITHM=TWO
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Sec. 7.5 Contact conditions
Auxiliary Commands LIST CGROUP3 FIRST LAST DELETE CGROUP3 FIRST LAST NODES NODES = YES (the default) will remove nodes which were only attached to contact segments in the deleted contact group. The summary of parameters applicable for each contact algorithm is presented in two tables following the command descriptions, one for implicit analysis and one for explicit analysis.
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Case 1: Implicit – Constraint Function Algorithm CGROUP CONTACT3
Activated when: - ALGORITHM=CONSTRAINT-FUNCTION - ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACTCONTROL)=CONSTRAINT-FUNCTION The following superscripts are used for some of the parameters: 1. 2.
Only applicable to (the default) node-to-segment contact Only applicable to node-to-node contact
The absence of a superscript indicates general applicability. The CGROUP parameters are divided into 3 subgroups: Basic, Advanced, and Multiphysics: Basic parameters NAME [(current highest contact group label number) + 1] Label number of the contact group to be defined. ALGORITHM [DEFAULT] Selects the contact algorithm for current group if the analysis is implicit. If DEFAULT is selected the algorithm type is determined based on the CONTACT-ALGORITHM parameter of the MASTER command. See comment above for activating the current contact algorithm. {DEFAULT/ CONSTRAINT-FUNCTION/ SEGMENT-METHOD/ RIGID-TARGET} NODETONODE [NO] Indicates whether node-to-segment or node-to-node contact algorithm is used by the contact group. {YES/NO}
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NO YES
Sec. 7.5 Contact conditions
- Use node-to-segment contact - Use node-to-node contact
DISPLACEMENT 1 [DEFAULT] Specifies the displacement formulation used for this contact group. {DEFAULT/LARGE/ SMALL} DEFAULT
-
LARGE
-
SMALL
-
The displacement formulation specified in the CONTACT-CONTROL command is used. Large displacement is assumed for contact where the contact search is performed in each iteration to generate new contact constraints. Small displacement is assumed for contact. The contact constraints are generated once in the beginning of the analysis and kept constant throughout the analysis.
FRICTION [0.0] Default coefficient of Coulomb friction. FRICTION = 0.0 indicates frictionless contact. Contact pairs can set their own friction coefficient. CFACTOR1 Compliance factor for all contact surfaces in this contact group. {≥ 0.0}
[0.0]
PENETRATION-ALGORITHM1 The penetration algorithm can be chosen as follows:
[ONE]
ONE - Each contact surface is single-sided. You must insure that each contact surface has proper orientation. TWO - Each contact surface is double-sided. The contact surface orientation does not matter. It is recommended that the nodal offset be greater than zero in this case. DEPTH 1 [0.0] This parameter is used when PENETRATION-ALGORITHM=ONE. If DEPTH > 0.0, then penetration is detected when the penetration depth is less than or equal to DEPTH, and if the penetration distance is greater than DEPTH, penetration is deemed not to occur. TIED1 Indicates the type of TIED contact. This parameter is ignored when PENETRATIONALGORITHM = TWO. {NO/SMALL}
[NO]
NO - No TIED contact. SMALL - Small displacement is used in TIED contact.
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TIED-OFFSET 1 [0.0] If TIED = SMALL, contactor nodes are tied to target if the gap between them is less than or equal to this parameter. This parameter is ignored when TIED = NO. OFFSET
[0.0 if PENETRATION = ONE] [0.001 if PENETRATION = TWO] For PENETRATION-ALGORITHM=ONE, the actual contact surface is raised a distance OFFSET away from the surface defined by the nodes. { ≥ 0.0}
For PENETRATION-ALGORITHM=TWO, two contact surfaces are constructed for each defined contact surface, each contact surface placed a distance OFFSET from the defined contact surface. { ≥ 0.0} Note:
The OFFSET parameter specifies the default offset distance. For each individual contact surface, a different offset distance can be specified using the command CS-OFFSET.
OFFSET-TYPE [CONSTANT] Specifies the type of offset to be used for contact surfaces belonging to this group. {CONSTANT/TRUE/NONE} CONSTANT - Constant offset as specified by the parameter OFFSET is used. See note under OFFSET. TRUE - The actual shell half thickness is used as the offset distance even for large strains. NONE - No offset is used (regardless of the value of the parameter OFFSET). FORCES 1 [YES] Indicates whether or not concentrated contact nodal forces are calculated for every contact surface node of this contact group. The contact forces are evaluated with respect to the global Cartesian coordinate system. {YES/NO} Note: - If NODETONODE = YES, nodal forces are always calculated and this parameter is ignored. - The combination FORCES = NO, TRACTIONS = NO is not permitted. TRACTIONS 1 [YES] Indicates whether or not contactor segment tractions (and concentrated contact nodal forces at solitary nodes in contact) are calculated for every contactor surface of this contact group. {YES/NO} Note:
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CONTINUOUS-NORMAL 1
[YES if PENETRATION = ONE] [NO if PENETRATION = TWO] Indicates whether or not a continuous (interpolated) contact segment normal is to be used for contact surfaces in the contact group. {YES/NO}
DIRECTION 2 [NORMAL] Specifies the vector used to describe the normal direction for a nodal pair in node-to-node contact. {NORMAL/VECTOR} NORMAL - Use the normal vector inside the target body. VECTOR - Use the vector connecting target and contactor nodes. Advanced parameters TBIRTH 1 [0.0] TDEATH 1 [0.0] The birth and death times for the whole contact group. If TBIRTH=0.0 and TDEATH=0.0, the birth and death feature is not used. INITIAL-PENETRATION1 Initial contactor node penetration flag. {ALLOWED/PRINT/DISCARDED/GAP-OVERRIDE}
[ALLOWED]
- Any initial penetration of a contactor node into a target surface is eliminated either in the first solution step or over a specified time interval (see TIME-PENETRATION parameter). In successive steps each contactor node cannot penetrate. PRINT - Same as ALLOWED, but a printout of the penetrating contactor nodes is produced. DISCARDED - Any initial penetration of a contactor node into a target surface is not eliminated in the first solution step. In successive steps each contactor node is allowed to penetrate up to the initial penetration. GAP-OVERRIDE - Initial penetrations or gaps are overridden by user-specified GAPVALUE parameter. ALLOWED
TIME-PENETRATION 1 Specifies the time used to eliminate any initial penetration. {≥ 0.0}
[0.0]
If INITIAL-PENETRATION = ALLOWED or PRINT, and TIME-PENETRATION=0.0, then the initial penetration is eliminated in the first time step. By specifying TIME-PENETRATION > 0.0, initial penetration can be eliminated gradually. This may help in the convergence of the solution.
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GAP-VALUE 1 [0.0] Specifies a constant gap distance between the contactor and target surfaces when INITIALPENETRATION = GAP-OVERRIDE. This value overrides the value measured from the contact surfaces. A negative GAP-VALUE means initial penetrations which will be eliminated. CS-EXTENSION 1 The maximum non-dimensional extension of target contact surfaces. {0.0 < CS-EXTENSION < 0.1}
[0.001]
EPSN [0.0] The normal contact w-function εΝ parameter. Guidelines for choosing this parameter are provided in the ADINA-AUI Online Help. When EPSN = 0.0, ADINA automatically determines this parameter. EPST [0.0] The friction contact v-function εT parameter. Guidelines for choosing this parameter are provided in the ADINA-AUI Online Help. When EPST = 0.0, ADINA automatically sets it to 0.001. CONSISTENT-STIFF 1 [DEFAULT] Indicates whether consistent contact stiffness is used. {DEFAULT/OFF/ON} When CONSISTENT-STIFF = DEFAULT, consistent contact stiffness is used if the following conditions are all satisfied: - the skyline direct equation solver is not used, i.e., SOLVER is not set to SKYLINE in the MASTER command, - CONTINUOUS-NORMAL = NO is specified. - Old contact surfaces are used (CSTYPE=OLD in CONTACT-CONTROL command). Otherwise, the default is set to off. Note that this option is not used in small displacement analysis (DISPLACEMENT=SMALL in the KINEMATICS command). It is also not used if small displacements are selected in the contact group (DISPLACEMENT parameter). The use of consistent contact stiffness increases the size of the stiffness matrix. However, it can improve the convergence rate in contact problems, especially in cases where the normal vector between the contacting surfaces frequently changes direction during the analysis. FRIC-DELAY [NO] Indicates whether the application of friction is delayed, i.e., applied one time step after contact is established. {NO/YES}
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USER-FRICTION 1 [NO] Indicates whether a user-supplied friction law is used for this contact group. If USERFRICTION=YES is specified, additional parameters for defining the user-supplied friction law can be input using the USER-FRICTION command. {YES/NO} Multiphysics parameters HHATTMC1 [0.0] Contact heat transfer coefficient used for thermo-mechanical coupling (TMC) analysis. { ≥ 0.0} [0.5] FCTMC 1 Friction contact heat distribution fraction coefficient for contactor used for thermo-mechanical coupling (TMC) analysis. {0.0 ≤ FCTMC ≤ 1.0} FTTMC 1 [0.5] Friction contact heat distribution fraction coefficient for target used for thermo-mechanical coupling (TMC) analysis. {0.0 ≤ FTTMC ≤ 1.0} EKTMC1 [0.0] Electrical conductivity for current flow through contact surfaces in a thermo-mechanical coupling (TMC) analysis. (Units: electrical conductance/length, e.g., Siemens/m) {≥ 0.0}
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Case 2: Implicit – Segment Method Algorithm CGROUP CONTACT3
Activated when: - ALGORITHM=SEGMENT-METHOD - ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACTCONTROL)=SEGMENT-METHOD All the parameters for the Segment Method Algorithm are described in Case 1: Implicit Constraint Function Algorithm
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Case 3: Implicit - Rigid Target Algorithm CGROUP CONTACT3
Activated when: - ALGORITHM=RIGID-TARGET - ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACT-CONTROL)= RIGID-TARGET For the following parameters, see description for Case 1: Implicit - Constraint Function Algorithm NAME ALGORITHM FRICTION DEPTH TBIRTH TDEATH NORMAL-STIFFNESS Contact stiffness in direction normal to the contact surface. TENSILE-FORCE The maximum tensile contact force allowed for a converged solution. {≥ 0.0}
[1.0E11]
[0.001]
SLIDING-VELOCITY [1E-10] The maximum sliding velocity used in modeling sticking friction. When the velocity is smaller than SLIDING-VELOCITY, sticking is assumed; when the velocity is larger than SLIDINGVELOCITY, sliding is assumed. {>0.0} OSCILLATION-CHECKING [5] The intent of this parameter is to increase the likelihood of convergence during the equilibrium iterations. {≥ 0.0} OSCILLATION-CHECKING=0 turns off oscillation checking. OSCILLATION-CHECKING>0 signals oscillation checking after equilibrium iteration OSCIL-
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LATION-CHECKING. For example, when OSCILLATION-CHECKING=5, then oscillation checking is activated after equilibrium iteration 5. Oscillation checking consists of two checks: a)
If a contactor node oscillates between two neighboring target segments during the equilibrium iterations, oscillation checking puts the contactor node into contact with the boundary edge between the target segments.
b) In analysis with friction, if the sliding velocity of a contactor node oscillates during the equilibrium iterations, oscillation checking puts the contactor node into sticking contact. The oscillation check is only applied for the iteration in which the oscillation is detected. GAP-BIAS [0.0] Contact is detected when the distance between the target and contactor (accounting for any offsets) is less than GAP-BIAS. GAP-BIAS can be positive, negative or zero. OFFSET [0.0] The actual contact surface is raised a distance OFFSET away from the surface defined by the nodes. { ≥ 0.0} OFFSET-TYPE [CONSTANT] Specifies the type of offset to be used for contact surfaces belonging to this group. {CONSTANT/TRUE} CONSTANT - Constant offset as specified by the parameter OFFSET is used. TRUE - The actual shell half thickness is used as the offset distance even for large strains. OFFSET-DETECT [AUTOMATIC] This parameter determines the implementation of offsets for the current rigid-target contact algorithm. {NORMALS/SPHERES/AUTOMATIC} NORMALS
SPHERES
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- Two surfaces are constructed for each contactor surface: an upper surface and a lower surface. These surface are constructed using the offsets and the averaged contactor normals. Contact is then detected between points on the constructed contactor surfaces and target surfaces. - A sphere with a radius equal to the offset is placed around each contactor node, and contact is detected between the spheres and the target surfaces.
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AUTOMATIC
-
Sec. 7.5 Contact conditions
ADINA chooses the implementation based upon the shape of the target surfaces; if a target surface is flat or convex, spheres are used, otherwise normals are used.
TENS-CONTACT This parameter controls the use of the tensile contact feature. {NO/YES}
[NO]
FREE-OVERLAP This parameter controls the use of the free overlap feature. {NO/YES}
[NO]
GAP-PUSH This parameter controls the gap-push feature. { ≥ 0.0}
[0.0]
RIGID-TARGET (obsolete) [NO] Indicates whether rigid target contact algorithm is used for current contact group. It is preferable to set ALGORITHM instead. {NO/YES}
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CGROUP CONTACT3
Chap. 7 Model definition
Case 4: Implicit - Old Rigid Target Algorithm (version 8.3 - now obsolete) Note: This is an obsolete algorithm that should only be used for backward compatibility. CGROUP CONTACT3
Activated when: - ALGORITHM=RIGID-TARGET - ALGORITHM=DEFAULT & CONTACT-ALGORITHM (in CONTACT-CONTROL)= RIGID-TARGET & - RT-ALGORITHM (in CONTACT-CONTROL)=V83 For the following parameters, see description for Case 1: Implicit - Constraint Function Algorithm NAME ALGORITHM FRICTION DEPTH TBIRTH TDEATH NORMAL-STIFFNESS Contact stiffness in direction normal to the contact surface. TANGENTIAL-STIFFNESS Contact stiffness in direction tangential to the contact surface.
[1.0E11]
[0.0]
PTOLERANCE [1.0E-8] Maximum allowable penetration of target surface. If penetration is less than PTOLERANCE, contact is assumed to be not yet established for the node in consideration. OFFSET [0.0] The actual contact surface is raised a distance OFFSET away from the surface defined by the nodes. { ≥ 0.0}
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Sec. 7.5 Contact conditions
OFFSET-TYPE [CONSTANT] Specifies the type of offset to be used for contact surfaces belonging to this group. {CONSTANT/TRUE} CONSTANT - Constant offset as specified by the parameter OFFSET is used. TRUE - The actual shell half thickness is used as the offset distance even for large strains. RESIDUAL-FORCE [0.001] Minimum tensile contact force required to change state of a contact node from "node in contact" to "free node". If the normal component of a tensile contact force is less than RESIDUAL-FORCE, a "node in contact" remains in contact. If the normal tensile force is greater than RESIDUAL-FORCE, a "node in contact" becomes a "free node". LIMIT-FORCE [1.0] Limit (maximum) for the sum of all contact forces for nodes changing from the state of "node in contact" to "free node". If the absolute value of the sum of the forces is bigger than LIMIT-FORCE, then the automatic time stepping (ATS) method will be activated to subdivide the current time step into smaller time increments. ITERATION-LIMIT [2] Maximum number of ATS time step subdivisions due to LIMIT-FORCE criterion described above. RTP-CHECK [NO] Specifies whether penetration is checked (in addition to checking the tensile contact force) against the maximum allowable penetration when the rigid-target algorithm is used. {NO/ RELATIVE/ABSOLUTE} NO
-
RELATIVE
-
ABSOLUTE
-
Penetration is not checked. Note that with this setting, there is a possibility that the rigid target surface may excessively penetrate the contactor surface. Penetration is checked and RTP-MAX is specified as a factor of the overall model size. Penetration is checked and RTP-MAX is the absolute value of penetration allowed.
Note that if penetration check is selected, the program will perform subdivision of time steps if the penetration exceeds the maximum allowable penetration. The subdivision scheme is specified in the RT-SUBD parameter in the CONTACT-CONTROL command. RTP-MAX [0.001] Specifies the maximum allowable penetration when the rigid target algorithm is used.
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CGROUP CONTACT3
RTP-MAX is either a factor of the model size or an absolute value depending on the RTP-CHECK parameter. {> 0.0} RIGID-TARGET (obsolete) [NO] Indicates whether rigid target contact algorithm is used for current contact group. It is preferable to set ALGORITHM instead. {NO/YES}
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CGROUP CONTACT3
Sec. 7.5 Contact conditions
Case 5: Explicit - Kinematic Constraint Algorithm CGROUP CONTACT3
NAME XALGORITHM NODETONODE DISPLACEMENT FRICTION PENETRATION-ALGORITHM DEPTH OFFSET OFFSET-TYPE FORCES TRACTIONS DIRECTION TBIRTH TDEATH INITIAL-PENETRATION
TIME-PENETRATION GAP-VALUE CS-EXTENSION Activated when: - XALGORITHM=KINEMATIC-CONSTRAINT - XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-CONTROL)= KINEMATIC-CONSTRAINT The following superscripts are used for some of the parameters: 1. 2.
Only applicable to (the default) node-to-segment contact Only applicable to node-to-node contact
The absence of a superscript indicates general applicability. The CGROUP parameters are divided into 2 subgroups: Basic and Advanced. Basic parameters NAME [(current highest contact group label number) + 1] Label number of the contact group to be defined. XALGORITHM [DEFAULT] Selects the contact algorithm for current group if the analysis is explicit. If DEFAULT is selected the algorithm type is determined based on XCONT-ALGORITHM variable of the CONTACT-CONTROL command. See comment above for activating the current contact algorithm. {DEFAULT/KINEMATIC-CONSTRAINT/PENALTY/EXPLICIT-RIGID-TARGET} NODETONODE [NO] Indicates whether node-to-segment or node-to-node contact algorithm is used by the contact group. {YES/NO} NO YES
- Use node-to-segment contact - Use node-to-node contact
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CGROUP CONTACT3
DISPLACEMENT 1 [DEFAULT] Specifies the displacement formulation used for this contact group. {DEFAULT/LARGE/ SMALL} DEFAULT
-
LARGE
-
SMALL
-
The displacement formulation specified in the CONTACT-CONTROL command is used. Large displacement is assumed for contact where the contact search is performed in each iteration to generate new contact constraints. Small displacement is assumed for contact. The contact constraints are generated once in the beginning of the analysis and kept constant throughout the analysis.
FRICTION [0.0] Default coefficient of Coulomb friction. FRICTION = 0.0 indicates frictionless contact. Contact pairs can set their own friction coefficients. PENETRATION-ALGORITHM1 The penetration algorithm can be chosen as follows:
[ONE]
ONE - Each contact surface is single-sided. You must insure that each contact surface has proper orientation. TWO - Each contact surface is double-sided. The contact surface orientation does not matter. It is recommended that the nodal offset be greater than zero in this case. DEPTH 1 [0.0] This parameter is used when PENETRATION-ALGORITHM=ONE. If DEPTH > 0.0, then penetration is detected when the penetration depth is less than or equal to DEPTH, and if the penetration distance is greater than DEPTH, penetration is deemed not to occur. OFFSET
[0.0 if PENETRATION = ONE] [0.001 if PENETRATION = TWO] For PENETRATION-ALGORITHM=ONE, the actual contact surface is raised a distance OFFSET away from the surface defined by the nodes. { ≥ 0.0}
For PENETRATION-ALGORITHM=TWO, two contact surfaces are constructed for each defined contact surface, each contact surface placed a distance OFFSET from the defined contact surface. { ≥ 0.0} Note:
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The OFFSET parameter specifies the default offset distance. For each individual contact surface, a different offset distance can be specified using the command CS-OFFSET.
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Sec. 7.5 Contact conditions
OFFSET-TYPE [CONSTANT] Specifies the type of offset to be used for contact surfaces belonging to this group. {CONSTANT/TRUE/NONE} CONSTANT - Constant offset as specified by the parameter OFFSET is used. See note under OFFSET. TRUE - The actual shell half thickness is used as the offset distance even for large strains. NONE - No offset is used (regardless of the value of the parameter OFFSET). FORCES 1 [YES] Indicates whether or not concentrated contact nodal forces are calculated for every contact surface node of this contact group. The contact forces are evaluated with respect to the global Cartesian coordinate system. {YES/NO} Note: - If NODETONODE = YES, nodal forces are always calculated and this parameter is ignored. - The combination FORCES = NO, TRACTIONS = NO is not permitted. TRACTIONS 1 [YES] Indicates whether or not contactor segment tractions (and concentrated contact nodal forces at solitary nodes in contact) are calculated for every contactor surface of this contact group. {YES/NO} Note:
The combination FORCES = NO, TRACTIONS = NO is not permitted.
DIRECTION 2 [NORMAL] Specifies the vector used to describe the normal direction for a nodal pair in node-to-node contact. {NORMAL/VECTOR} NORMAL - Use the normal vector inside the target body. VECTOR - Use the vector connecting target and contactor nodes. Advanced parameters TBIRTH 1 [0.0] TDEATH 1 [0.0] The birth and death times for the whole contact group. If TBIRTH=0.0 and TDEATH=0.0, the birth and death feature is not used. INITIAL-PENETRATION1 Initial contactor node penetration flag. {ALLOWED/PRINT/DISCARDED/GAP-OVERRIDE}
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CGROUP CONTACT3
- Any initial penetration of a contactor node into a target surface is eliminated either in the first solution step or over a specified time interval (see TIME-PENETRATION parameter). In successive steps each contactor node cannot penetrate. PRINT - Same as ALLOWED, but a printout of the penetrating contactor nodes is produced. DISCARDED - Any initial penetration of a contactor node into a target surface is not eliminated in the first solution step. In successive steps each contactor node is allowed to penetrate up to the initial penetration. GAP-OVERRIDE - Initial penetrations or gaps are overridden by user-specified GAPVALUE parameter. ALLOWED
TIME-PENETRATION 1 Specifies the time used to eliminate any initial penetration. {≥ 0.0}
[0.0]
If INITIAL-PENETRATION = ALLOWED or PRINT, and TIME-PENETRATION=0.0, then the initial penetration is eliminated in the first time step. By specifying TIME-PENETRATION > 0.0, initial penetration can be eliminated gradually. This may help in the convergence of the solution. GAP-VALUE 1 [0.0] Specifies a constant gap distance between the contactor and target surfaces when INITIALPENETRATION = GAP-OVERRIDE. This value overrides the value measured from the contact surfaces. A negative GAP-VALUE means initial penetrations which will be eliminated. CS-EXTENSION 1 The maximum non-dimensional extension of target contact surfaces. {0.0 < CS-EXTENSION < 0.1}
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[0.001]
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CGROUP CONTACT3
Sec. 7.5 Contact conditions
Case 6: Explicit – Penalty Algorithm CGROUP CONTACT3
XALGORITHM=PENALTY XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-CONTROL)= PENALTY
For the following parameters, see description for Case 5: Explicit - Kinematic constraint algorithm NAME XALGORITHM DISPLACEMENT FRICTION PENETRATION-ALGORITHM DEPTH OFFSET OFFSET-TYPE FORCES TRACTIONS TBIRTH TDEATH INITIAL-PENETRATION TIME-PENETRATION GAP-VALUE CS-EXTENSION XKN-CRIT Criterion for evaluation of normal penalty stiffness. {GLOBAL/USER} GLOBAL USER
[GLOBAL]
- Penalty stiffness will be determined globally for the whole contact group. - The user sets the penalty stiffness.
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CGROUP CONTACT3
XK-NORMAL [0.0] The normal stiffness. It must be greater than 0.0. It is only used for XKN-CRIT=USER. XKT-CRIT Criterion for evaluation of tangential penalty stiffness. {GLOBAL/USER} GLOBAL USER
[GLOBAL]
- Penalty stiffness will be determined globally for the whole contact group. - The user sets the penalty stiffness.
XK-TANGENT [0.0] The tangetial stiffness. It must be greater than 0.0. It is only used for XKT-CRIT=USER. XDAMP [NO] Indicates whether normal damping (proportional to the rate of penetration) is used.{NO/ RELATIVE/ABSOLUTE} NO RELATIVE
-
ABSOLUTE
-
Damping is not used, i.e., XNDAMP parameter is ignored. Damping is used and XNDAMP is a factor of the critical damping, i.e., the normal contact damping coefficient is given by XNDAMP multiplied by the critical damping. This is the recommended choice if damping is used. Damping is included and the normal contact damping coefficient is specified directly by XNDAMP.
XNDAMP [0.1] Specifies the relative or absolute normal damping coefficient (for normal penalty stiffness). { ≥ 0.0}
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CGROUP CONTACT3
Sec. 7.5 Contact conditions
Case 7: Explicit - Rigid Target Algorithm CGROUP CONTACT3
Activated when: - XALGORITHM=EXPLICIT-RIGID-TARGET - XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-CONTROL)= EXPLICIT-RIGID-TARGET For the following parameters, see description for Case 5: Explicit - Kinematic constraint algorithm NAME XALGORITHM FRICTION DEPTH TBIRTH TDEATH NORMAL-STIFFNESS Contact stiffness in direction normal to the contact surface.
[1.0E11]
SLIDING-VELOCITY [1E-10] The maximum sliding velocity used in modeling sticking friction, used only when friction is included. When the velocity is smaller than SLIDING-VELOCITY, sticking is assumed; when the velocity is larger than SLIDING-VELOCITY, sliding is assumed. {>0.0} GAP-BIAS [0.0] Contact is detected when the distance between the target and contactor (accounting for any offsets) is less than GAP-BIAS. GAP-BIAS can be positive, negative or zero. OFFSET [0.0] The actual contact surface is raised a distance OFFSET away from the surface defined by the nodes. { ≥ 0.0} OFFSET-TYPE [CONSTANT] Specifies the type of offset to be used for contact surfaces belonging to this group. {CONSTANT/TRUE}
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CGROUP CONTACT3
CONSTANT - Constant offset as specified by the parameter OFFSET is used. See note under OFFSET. TRUE - The actual shell half thickness is used as the offset distance even for large strains. OFFSET-DETECT [AUTOMATIC] This parameter determines the implementation of offsets for the current rigid-target contact algorithm. {NORMALS/SPHERES/AUTOMATIC} NORMALS
SPHERES
AUTOMATIC
- Two surfaces are constructed for each contactor surface: an upper surface and a lower surface. These surface are constructed using the offsets and the averaged contactor normals. Contact is then detected between points on the constructed contactor surfaces and target surfaces. - A sphere with a radius equal to the offset is placed around each contactor node, and contact is detected between the spheres and the target surfaces. - ADINA chooses the implementation based upon the shape of the target surfaces; if a target surface is flat or convex, spheres are used, otherwise normals are used.
RIGID-TARGET (obsolete) [NO] Indicates whether rigid target contact algorithm is used for current contact group. It is preferable to set XALGORITHM instead. {NO/YES}
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CGROUP CONTACT3
Sec. 7.5 Contact conditions
Case 8: Explicit – Old Rigid Target Algorithm (version 8.3 – now obsolete) Note: This is an obsolete algorithm that should only be used for backward compatibility CGROUP CONTACT3
Activated when: XALGORITHM=EXPLICIT-RIGID-TARGET XALGORITHM=DEFAULT & XCONT-ALGORITHM (in CONTACT-CONTROL)= EXPLICIT-RIGID-TARGET & RT-ALGORITHM (in CONTACT-CONTROL)=V83 For the following parameters, see description for Case 5: Explicit - Kinematic constraint algorithm NAME XALGORITHM FRICTION DEPTH TBIRTH TDEATH NORMAL-STIFFNESS Contact stiffness in direction normal to the contact surface. TANGENTIAL-STIFFNESS Contact stiffness in direction tangential to the contact surface.
[1.0E11]
[0.0]
PTOLERANCE [1.0E-8] Maximum allowable penetration of target surface. If penetration is less than PTOLERANCE, contact is assumed to be not yet established for the node in consideration. OFFSET [0.0] The actual contact surface is raised a distance OFFSET away from the surface defined by the nodes. { ≥ 0.0}
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CGROUP CONTACT3
OFFSET-TYPE [CONSTANT] Specifies the type of offset to be used for contact surfaces belonging to this group. {CONSTANT/TRUE} CONSTANT - Constant offset as specified by the parameter OFFSET is used. See note under OFFSET. TRUE - The actual shell half thickness is used as the offset distance even for large strains. RIGID-TARGET (obsolete) [NO] Indicates whether rigid target contact algorithm is used for current contact group. It is preferable to set XALGORITHM instead. {NO/YES}
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Sec. 7.5 Contact conditions
Summary of parameters applicable for each contact algorithm (Implicit analysis) * in
the case of 3D contact, denotes only applicable to the old Rigid Target Algorithm applicable to 2D contact applicable to 3D contact
1 only 2 only
C O N TAC T ALGO RITHM C O N STRAIN T- FUN C TIO N
S EGM EN T- M ETHO D
RIGID- TARGET
N AM E ALGO RITHM FRIC TIO N C FAC TO R1 O FFS ET O FF SET- TYPE
N AM E ALGO RITHM FRIC TIO N O FFS ET O F FSET- TYPE
N AM E ALGO RITHM FRIC TIO N DEP TH TBIRTH, TDEATH N O RM AL- STIFFN ES S TEN S ILE- FO RC E O FFS ET O FF SET- TYPE S UBTYPE 1
F RIC - DELAY S UBTYPE 1
EP SN EPS T F RIC - DELAY S UBTYPE 1 N O DETO N O DE = N O DISPLAC EM EN T PEN ETRATIO N - ALGO RITHM 2 DEP TH TIED TIED- O FFS ET FO RC ES TRAC TIO N S C O N TIN UO US - N O RM AL
DISPLAC EM EN T PEN ETRATIO N - ALGO RITHM 2 DEPTH TIED TIED- O FFS ET FO RC ES TRAC TIO N S C O N TIN UO US - N O RM AL
TBIRTH, TDEATH IN ITIAL- PEN ETRATIO N TIM E- P EN ETRATIO N GAP- VALUE C S - EXTEN S IO N C O N S IS TEN T- STIFF US ER- FRIC TIO N
TBIRTH, TDEATH IN ITIAL- PEN ETRATIO N TIM E- P EN ETRATIO N GAP- VALUE C S - EXTEN S IO N C O N S IS TEN T- S TIFF US ER- F RIC TIO N
S LIDIN G- VELO C ITY 2 O S C ILLATIO N - C HEC K IN G 2 GAPBIAS 2 O F FSET- DETEC T 2 TEN S- C O N TAC T 2 FREE- O VERLAP 2 GAP- PUSH 2 TAN GEN TIAL- STIFFN ES S * PTO LERAN C E* RESIDUAL- FO RC E* LIM IT- FO RC E* ITERATIO N - LIM IT* RTP- C HEC K * RTP- M AX*
HHATTM C FC TM C F TTM C EK TM C N O DETO N O DE = YES DIREC TIO N
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Summary of parameters applicable for each contact algorithm (Explicit analysis) * in the case of 3D contact, denotes 1 only applicable to 2D contact 2 only applicable to 3D contact
only applicable to the old Rigid Target Algorithm
C O N TAC T ALGO RITHM K IN EM ATIC C O N STRAIN T
PEN ALTY
EXPLIC IT RIGID-TARGET
N AM E XALGO RITHM FRIC TIO N O FFSET O FFS ET-TYPE S UBTYPE 1
N AM E XALGO RITHM DISPLAC EM EN T FRIC TIO N PEN ETRATIO N -ALGO RITHM 2 DEPTH O FFSET O FFSET- TYPE FO RC ES TRAC TIO N S XK N -C RIT XK -N O RM AL XK T-C RIT XK -TAN GEN T XDAM P XN DAM P
N AM E XALGO RITHM FRIC TIO N DEPTH TBIRTH, TDEATH N O RM AL-STIFFN ESS O FFSET O FFSET-TYPE S UBTYPE 1
N O DETO N O DE = N O DISPLAC EM EN T PEN ETRATIO N -ALGO RITHM 2 DEPTH FO RC ES TRAC TIO N S TBIRTH, TDEATH IN ITIAL-PEN ETRATIO N TIM E-PEN ETRATIO N GAP-VALUE C S -EXTEN SIO N
SLIDIN G-VELO C ITY 2 GAPBIAS 2 O FFSET-DETEC T 2 TAN GEN TIAL-STIFFN ESS* PTO LERAN C E*
TBIRTH, TDEATH IN ITIAL-PEN ETRATIO N TIM E- PEN ETRATIO N GAP-VALUE C S-EXTEN S IO N S UBTYPE 1
N O DETO N O DE = YES DIREC TIO N
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CONTACTBODY
CONTACTBODY
Sec. 7.5 Contact conditions
NAME PRINT SAVE SOLID BODY
operationi typei labeli Command CONTACTBODY defines a “contact body”, i.e. a geometry surface in 2D analysis or a geometry volume in 3D analysis, which is expected to be in contact with a defined contactsurface (from the command CONTACTSURFACE). This allows all the nodes in the volume to potentially be in contact with a target surface. The target surface should still be defined using the CONTACTSURFACE command. Each data input line specifies an operation, entity type and entity label. For example, you can create a contactbody composed of a geometry volume excluding a geometry point by specifying two data input lines, the first line adding the volume and the second line subtracting the point. NAME [(current highest contactbody/surface number) + 1] Label number of the contactbody to be defined. Note that the contactbody names are unique only within a contact group, i.e. two different contact groups may each define its own contactbody “1”. Note also that the name must be distinguished from that in the CONTACTSURFACE command, because a contactpair can be formed between a geometry defined by the CONTACTBODY and a geometry defined by the CONTACTSURFACE. PRINT [DEFAULT] Flag controlling printout of the results of the contact analysis as determined by the FORCES and TRACTIONS parameters of the CGROUP command. Choices are NO, YES and DEFAULT; when PRINT=DEFAULT, printout is controlled by the PRINTOUT PRINTDEFAULT parameter. SAVE [DEFAULT] Flag controlling saving (to the porthole file) of the results of the contact analysis as determined by the FORCES and TRACTIONS parameters of the CGROUP command. Choices are NO, YES and DEFAULT; when SAVE=DEFAULT, saving is controlled by the PORTHOLE SAVEDEFAULT parameter. SOLID [NO] Flag indicating whether the contact body is defined on a B-Rep solid model body. {NO/YES} BODY Geometry body label number of a B-Rep solid model. This parameter is required if SOLID=YES.
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Chap. 7 Model definition
operationi [ADD] The entity specified in this data line is either added to or subtracted from the contactbody. {ADD/SUBTRACT} typei The type of the entity specified in this data line. The entity can either be a geometry entity (POINT, LINE, SURFACE, VOLUME, EDGE, FACE, BODY) or a finite element entity (NODE). Command line parameter SOLID must be YES if the type is EDGE, FACE or BODY and the command line parameter BODY must be specified if the type is EDGE or FACE. labeli The label number of the entity. Auxilary commands LIST CONTACTBODY DELETE CONTACTBODY
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CONTACTSURFACE
CONTACTSURFACE
Sec. 7.5 Contact conditions
NAME PRINT SAVE SOLID BODY ORIENTATION SENSE
namei sensei bodyi CONTACTSURFACE defines a “contact-surface”, i.e., a set of boundary entities which are expected to be in contact either initially or during analysis with another similarly defined contact-surface. NAME [(current highest contactsurface label number) + 1] Label number of the contact surface to be defined. Note that the contact-surface names are unique only within a contact group, i.e., two different contact groups may each define its own contact-surface “1”. PRINT [DEFAULT] Flag controlling printout of the results of the contact analysis as determined by the FORCES and TRACTIONS parameters of CGROUP. If DEFAULT is specified, printout is controlled by PRINTOUT PRINTDEFAULT. {YES/NO/DEFAULT} SAVE [DEFAULT] Flag controlling saving (to the porthole file) of the results of the contact analysis as determined by the FORCES and TRACTIONS parameters of CGROUP. If DEFAULT is specified, saving is controlled by the PORTHOLE SAVEDEFAULT parameter. {YES/NO/DEFAULT} SOLID [NO] Indicates whether the contact surface is defined on solid body (or bodies). {NO/YES/ MULTI/BODY} NO
Contact surface is defined on native AUI geometry. Enter lines or surfaces in the data input lines.
YES
Contact surface is defined on a single solid body (specified by parameter BODY). Enter edges or faces in the data input lines.
MULTI
Contact surface is defined on surfaces or faces of multiple bodies. (Only for 3-D contact surface). Enter surfaces or faces (and parent bodies) in the data input lines.
BODY
Contact surface is defined on all boundary faces of a body (specified by parameter BODY). Do not enter data input lines.
The sense flag for each component of the contact-surface is determined automatically.
INPUT
The sense flag for contact-surface components is input in the following data lines.
SENSE Default for the data line entry for contact-surface orientation. {+1/-1}
[+1]
namei Label of geometric entities used to define this contact surface. The type of geometric entity depends on the contact group and the parameter SOLID as indicated below. Contact Group
SOLID
namei
2-D
NO
line label
2-D 3-D 3-D 3-D
YES NO YES MULTI
edge label surface label face label surface or face label
sensei Orientation flag for geometry component:
[SENSE]
+1 contact-surface uses same orientation as geometry. -1 contact-surface uses opposite orientation to geometry. bodyi Label of the parent solid body when namei is an edge label or a face label. Note:
The label numbers for contact-surface definitions include those defined by commands CONTACTSURFACE, CONTACTPOINT and CONTACT-FACENODES. Thus you cannot define CONTACTSURFACE “1” and CONTACTPOINT “1”, one would overwrite the prior definition.
Auxiliary commands LIST CONTACTSURFACE DELETE CONTACTSURFACE
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CONTACTPOINT
Chap. 7 Model definition
CONTACTPOINT
NAME PRINT SAVE POINT-TYPE
pointi tnxi tnyi tnzi Defines a “contact-point”, i.e., a contact-surface defined as a set of geometry points or nodes (in 2-D or 3-D analysis) which are expected to be in contact, either initially or during analysis, with another similarly defined contact-point or contact-surface (see CONTACTSURFACE ). Note: This command is only available for node-to-node contact (i.e., NODETONODE=YES in the CGROUP CONTACT... command). NAME [(current highest contact point label number) + 1] Label number of the contact-point to be defined. Note that the contact-point names are unique only within a contact group, i.e., two different contact groups may each define its own contact-point “1”. PRINT [DEFAULT] Flag controlling printout of the results of the contact analysis as determined by the FORCES and TRACTIONS parameters of CGROUP. If DEFAULT is specified, printout is controlled by PRINTOUT PRINTDEFAULT. {YES/NO/DEFAULT} SAVE [DEFAULT] Flag controlling saving (to the porthole file) of the results of the contact analysis as determined by the FORCES and TRACTIONS parameters of CGROUP. If DEFAULT is specified, saving is controlled by PORTHOLE SAVEDEFAULT. {YES/NO/DEFAULT} POINT-TYPE [GEOMETRY] Specify whether geometry points or nodal points are used to define the contact surface. {GEOMETRY/NODAL/NODESET} pointi Geometry point, nodal point, or node set label. tnxi X-component of normal vector directed inside target body. tnyi Y-component of normal vector directed inside target body. tnzi Z-component of normal vector directed inside target body.
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Note:
Sec. 7.5 Contact conditions
The label numbers for contact-surface definitions include those defined by commands CONTACTSURFACE , CONTACTPOINT and CONTACT-FACENODES. Thus you cannot define CONTACTSURFACE “1” and CONTACTPOINT “1”, one would overwrite the prior definition.
Auxiliary commands LIST CONTACTPOINT DELETE CONTACTPOINT
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Chap. 7 Model definition
DRAWBEAD
DRAWBEAD
NAME CONTACTOR TARGET1 TARGET2 HEIGHT R-FORCE U-FORCE PRINT SAVE DF-PRINT TBIRTH TDEATH GTYPE SLIDING-VELOCITY
namei Defines a drawbead for metal forming analysis. This command is only active if the current contact group is a rigid-target 3-D contact group. NAME [(current highest DRAWBEAD label number) + 1 ] Label number of the drawbead to be defined. CONTACTOR Specifies the contactor surface for the drawbead. A contactor surface is a contact surface that is assigned as a contactor in a contact pair definition. TARGET1 Specifies the first target surface for the drawbead. A target surface is a contact surface that is assigned as a target in a contact pair definition. TARGET2 Specifies the second target surface for the drawbead. HEIGHT Specifies the drawbead height. {HEIGHT>0.0} R-FORCE Specifies the restraining force per unit length of the drawbead. {R-FORCE>0.0} U-FORCE Specifies the uplifting force per unit length of the drawbead. {U-FORCE>=0.0} PRINT Indicates whether drawbead segment nodal forces are printed.
[0.0]
[NO]
NO - do not print drawbead forces R-FORCE - print only restraining forces RU-FORCE - print restraining and uplifting forces SAVE
[NO]
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DRAWBEAD
Sec. 7.5 Contact conditions
Indicates whether drawbead segment nodal forces are saved. NO - do not save drawbead forces R-FORCE - save only restraining forces RU-FORCE - save restraining and uplifting forces DF-PRINT [NO] Indicates whether drawbead segment distributed forces (traction) are printed and/or saved to the porthole file. NO YES
- do not print/save distributed forces - print/save distributed forces
Option DF-PRINT = YES takes effect only if drawbead segment nodal forces are printed/ saved (parameter PRINT or SAVE is set to R-FORCE or RU-FORCE). TBIRTH Specifies the birth time of the drawbead.
[TBIRTH of contact group]
TDEATH Specifies the death time of the drawbead.
[TDEATH of contact group]
GTYPE Specifies the entity type used to define the drawbead. {LINE/NODE}
[LINE]
SLIDING-VELOCITY [1E-8] The minimum velocity of the contactor surface through the drawbead for which the drawbead develops the full restraining traction. {>0} This parameter is used only by the current rigid-target algorithm. namei Specifies the geometry lines or nodes that defines the drawbead. Auxiliary commands LIST DRAWBEAD DELETE DRAWBEAD
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COULOMB-FRICTION
Sec. 7.5 Contact conditions
COULOMB-FRICTION cpairi modeli A1i A2i A3i Specifies variable Coulomb friction coefficient for each contact pair under the current contact group. Note that this command is not available for rigid target contact (i.e., the parameter RIGID-TARGET=YES is specified in the CGROUP command). cpairi Contact pair label number. If zero is specified, the parameter specified in the other fields of this row will apply to all contact pairs. modeli Specifies the formula to define Coulomb friction coefficient µ. {LAW1/LAW2} LAW1
µ
=
A1 [1.0 − exp ( − A2 Tn )] Tn
LAW2
µ
=
A2 + ( A1 − A2 ) ⋅ exp ( − A3 Tn )
where Tn is normal contact pressure and A1, A2, A3 are constants. A1i Constant A1. A2i Constant A2. A3i Constant A3. This constant is only applicable if LAW2 is used. Auxiliary commands LIST COULOMB-FRICTION DELETE COULOMB-FRICTION
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USER-FRICTION
USER-FRICTION integeri reali Specifies the integer and real parameters passed to the user-supplied friction subroutine (FUSER) for the current contact group. Note that this feature cannot be used with the rigid target contact option (i.e., RIGID-TARGET=YES is specified in the CGROUP command). In the current implementation of FUSER, the first integer parameter is used to select a friction model. Each friction model requires a number of real integer parameters as explained in Section 4.3.2 of the Theory and Modeling Guide, Volume I (ADINA).
integeri Integer number. reali Real number.
Auxiliary commands LIST USER-FRICTION DELETE USER-FRICTION
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CS-OFFSET
Sec. 7.5 Contact conditions
CS-OFFSET csurfi offseti Specifies offset distances for individual contact-surfaces under the current contact group. If an individual contact surface is not specified here, the contact surface will use the default offset distance specified by the OFFSET parameter in the CGROUP command. csurfi Contact surface label number. offseti Offset distance. { ≥ 0.0} Note:
This feature is not available for rigid target contact (i.e the parameter RIGID-TARGET=YES is specified in the CGROUP command).
Auxiliary commands LIST CS-OFFSET DELETE CS-OFFSET
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CONTACTPAIR
Chap. 7 Model definition
CONTACTPAIR
NAME TARGET CONTACTOR FRICTION TBIRTH TDEATH HHATTMC FCTMC FTTMC NX NY NZ OFFSET-CONTACT EKTMC
Defines a “contact pair,” i.e., two contact-surfaces (see CONTACTSURFACE ) which are either initially in contact or are anticipated to come into contact during analysis. One contact surface is termed the “contactor” contact-surface and must be deformable, i.e., has contact segments associated with the boundary surfaces of deformable finite elements (i.e., with nodes with free displacement degrees of freedom) within the model. The other contactsurface which makes up the contact pair is termed the “target” contact-surface. The target contact-surface may be deformable or have prescribed displacement.
Target surface top surface of Body I
Body III Contactor surface top surface of Body I
Contact Pair 2
Contact Pair 1
Body II
Target surface bottom surface of Body II
Contactor surface bottom surface of Body III
Body I
Three contact surafces forming 2 contact pairs
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CONTACTPAIR
Sec. 7.5 Contact conditions
NAME [(current highest contactpair label number) + 1] Label number of the contact pair to be defined. The contactpair numbering is independent for each contact group. TARGET Target contact-surface, which must have been defined by the command CONTACTSURFACE, CONTACTPOINT or CONTACT-FACENODES for the currently active group. CONTACTOR Contactor contact-surface, defined by the CONTACTSURFACE, CONTACTPOINT or CONTACT-FACENODES for the currently active contact group. Note:
To specify “self-contact”, you may specify TARGET and CONTACTOR to be the same contact-surface.
FRICTION [CGROUP FRICTION] Coefficient of friction between the target and contactor contact-surfaces. FRICTION = 0.0 implies the default friction specified by CGROUP command is used. Note:
FRICTION is not used in node-to-node contact (parameter NODETONODE in commands CGROUP CONTACT2 and CGROUP CONTACT3 ). Contact group friction is used instead.
TBIRTH [0.0] TDEATH [0.0] The birth and death times for current contact pair. If TBIRTH=0.0 and TDEATH=0.0, the birth and death feature is not used. Note:
TBIRTH and TDEATH options are not used in node-to-node contact (parameter NODETONODE in commands CGROUP CONTACT2 and CGROUP CONTACT3).
Note:
If FRICTION, TBIRTH and TDEATH parameters are not specified, default values defined by commands CGROUP CONTACT2 or CGROUP CONTACT3 are used.
HHATTMC [0.0] Contact heat transfer coefficient; used only when thermo-mechanical coupling is active. FCTMC [0.5] Friction contact heat distribution fraction coef. for contactor; used only when thermomechanical coupling is active. {0.0 ≤ FCTMC ≤ 1.0}
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FTTMC [0.5] Friction contact heat distribution fraction coef. for target; used only when thermo-mechanical coupling is active. {0.0 ≤ FTTMC ≤ 1.0} NX [0] NY NZ Number of sorting buckets in X, Y, Z direction. For 2D contact groups (CGROUP CONTACT2) parameter NX is ignored. {≥ 0.0} For rigid-target algorithm of version 8.3, “0” = “1” (set when writing data file). For current rigid-target algorithm, “0” = automatically calculated by ADINA. OFFSET-CONTACT [BOTH] This parameter is used only in the following special cases {LOWER/UPPER/BOTH}: 1) Current rigid-target algorithm, and 2a) CGROUP OFFSET-DETECT=NORMALS, or 2b) CGROUP OFFSET-DETECT=AUTOMATIC and ADINA chooses an offset implementation using normals. Then the contactor surface is split into two surfaces, an upper surface and a lower surface: LOWER
Only the lower surface can be in contact with the target.
UPPER
Only the upper surface can be in contact with the target.
BOTH
Both surfaces can be in contact with the target.
Note that OFFSETCONTACT is only used to provide a hint to the contact algorithm, to speed up the searching. EKTMC [0.0] Electrical conductivity for current flow through contact surfaces in a thermo-mechanical coupling (TMC) analysis. Applicable only if the constraint function algorithm is used in implicit analysis, i.e., ALGORITHM = CONSTRAINT-FUNCTION in CGROUP CONTACT2/ 3. (Units: electrical conductance/length, e.g., Siemens/m) {≥ 0.0} Auxiliary commands LIST CONTACTPAIR DELETE CONTACTPAIR
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CONTACT3-SEARCH creates 3D contact surfaces and contact pairs between two bodies within the given distance range. BODY1 Label number of the first body. The contact surfaces defined by the faces of BODY1 will be used as target surfaces in contact pair. BODY2 Label number of the second body. The contact surfaces defined by the faces of BODY2 will be used as contactor surfaces in contact pair. Please note that BODY1 and BODY2 cannot be the same. CGROUP [current 3D contact group label number] 3D contact group label number. The given 3D contact group needs to be defined before this command is used. CSURFACE [(current contact surface label number) + 1] Contact surface label number. If the contact surface label number exists, it will be overwritten. CPAIR [(current contact pair label number) + 1] Contact pair label number. If the contact pair label number exists, it will be overwritten. DIST-TYPE [CLOSEST] Selects the type of distance that will be used to measure the distance between faces. CLOSEST
The shortest distance between faces
FACE-CENTER
The distance between face centers
DIST-MAX DIST-MIN [0.0] Faces between BODY1 and BODY2 will be used to define contact surfaces and contact pairs if the distance is between DIST-MIN and DIST-MAX. EXISTING [OVERWRITE] Indicates how existing contact surfaces and pairs in the contact group CGROUP are handled. {OVERWRITE/REMOVE/KEEP} OVERWRITE
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CONTACT3-SEARCH
REMOVE
All existing contact surfaces and pairs are removed
KEEP
Existing contact surface and pairs are kept. Hence, if the label numbers specified in CSURFACE or CPAIR already exist, this command will give an error.
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FRACTURE
Chap. 7 Model definition
FRACTURE
TECHNIQUE METHOD DIMENSION TYPE PRESSURE TEMPERATURE DYNAMIC LVUS3
FRACTURE defines the controlling data for analysis of fracture mechanics problems. TECHNIQUE [STANDARD] Defines whether standard or user-supplied fracture criteria / propagation models are used in the analysis. STANDARD
Standard analysis model.
METHOD [VIRTUAL-CRACK-EXTENSION] The method of evaluating the J-parameter value. {VIRTUAL-CRACK-EXTENSION/ LINE-CONTOUR/BOTH} DIMENSION Dimension of fracture analysis. {2/3} 2
2-D crack.
3
3-D crack.
TYPE Type of crack. {STATIONARY/PROPAGATION} STATIONARY
Analysis of a stationary crack.
PROPAGATION
Analysis of a propagating crack.
PRESSURE Pressure correction for virtual crack extension method. {YES/NO} YES
Pressure correction applied.
NO
No correction.
TEMPERATURE Temperature correction for virtual crack extension method. {YES/NO} YES
Temperature correction applied.
NO
No correction.
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[YES]
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FRACTURE
Sec. 7.6 Fracture mechanics
DYNAMIC Dynamic correction for virtual crack extension method. {YES/NO} YES
Dynamic correction applied.
NO
No correction.
LVUS3 This parameter is obsolete.
[YES]
[0]
Auxiliary commands LIST FRACTURE
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CRACK-GROWTH
Chap. 7 Model definition
CRACK-GROWTH
CONTROL-TYPE J-VERSION FACTOR R-CURVE LOCTYPE DOF SHIFT-RELEASE POINT NODE
CRACK-GROWTH specifies parameters which govern the growth of a propagating crack. This command should be used whenever the FRACTURE command indicates a 2-D propagating crack. CONTROL-TYPE The type of crack growth control: FIXED
A fixed virtual material shift.
MOVING
A moving virtual material shift.
NODAL
A nodal degree of freedom.
J-VERSION The version of the J-parameter used in crack growth control.
[FIXED]
[CORRECTIONS]
CORRECTIONS
J-parameter with thermal, pressure and dynamic corrections.
NONE
J-parameter without thermal, pressure and dynamic corrections.
FACTOR This parameter is not used any more, and is permanently set to 1.0 by the program.
[1.0]
R-CURVE [1] The identifying number of a resistance curve used in crack growth control (see command RCURVE ). {POINT/NODE} LOCTYPE [POINT] The type of location where a specified degree of freedom is used to control the crack propagation. {POINT/NODE} DOF The degree of freedom at the point (or node) used to control the crack propagation. 1
X-translation.
2
Y-translation.
3
Z-translation.
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CRACK-GROWTH
Sec. 7.6 Fracture mechanics
SHIFT-RELEASE [SHIFT-RELEASE] Indicates the mesh updating method used for a propagating crack. See the Theory and Modeling Guide for details. SHIFT-RELEASE
The node “shift & release” technique is used to model the propagation of the crack tip through the finite element mesh.
RELEASE
Only the node “release” technique is applied, when the crack opens.
POINT The label number of a point where a specified degree of freedom is used to control the crack propagation. NODE The label number of a node where a specified degree of freedom is used to control the crack propagation. Auxiliary commands LIST CRACK-GROWTH
CRACK-PROPAGATION defines the initial crack front position, or the virtual/actual crack propagation path along which a crack would propagate. This command should always be used in a fracture mechanics analysis, whether it is a 7-314
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CRACK-PROPAGATION
Sec. 7.6 Fracture mechanics
stationary or a propagating crack analysis. Note that in 2-D analysis, the crack front corresponds to a single node – the crack tip node. The virtual propagation path corresponds to a single point or line of nodes starting at the crack tip node. The crack propagation line must be parallel to the Y axis in 2D mode. In 3-D analysis, the crack front corresponds to a line of nodes. The virtual/actual crack propagation path corresponds to a surface developed from the crack front line along “generator” lines originating from the crack front nodes. The crack propagation surface must be in the X-Y plane in 3D mode. NAME [1] The label number of the crack propagation surface. (At present only one crack is allowed.) pointi The label number of a geometry point. linei The label number of a geometry line. surfacei The label number of a geometry surface. front-linei The label number of a line which defines initial crack front. front-pointi The label number of a point which defines the initial crack front. nvshfti In the case of fixed virtual material shift (CRACK-GROWTH CONTROL-TYPE = FIXED) this specifies the label number of virtual shift (defined by J-VIRTUAL-SHIFT command). In the case of moving virtual material shift (CRACK-GROWTH CONTROL-TYPE = MOVING) this specifies the number of “rings” of elements about the (moving) crack tip on the generator line. Parameter nvshfti is used only in crack propagation analysis (FRACTURE TYPE =PROPAGATION). factori Resistance factor. This parameter is no longer used. Auxiliary commands LIST CRACK-PROPAGATION DELETE CRACK-PROPAGATION
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J-LINE POINT
Chap. 7 Model definition
J-LINE POINT
NAME POINT RADIUS PRINT SAVE START-FACE END-FACE
J-LINE POINT defines a line contour by using a circle defined by its center and radius. The line contour is defined by a series of elements intersected by the circle.
RA D
IU S
elements in J-LINE contour
POINT
NAME [(current highest label number) + 1] Label number of the line contour to be defined. If the label number of an existing line contour is given, then the previous line contour definition is overwritten. POINT The point label number; the center of the circle. RADIUS The radius of the circle.
[0]
[0.0]
PRINT SAVE START-FACE [0] If the first element of the contour does not have a unique face on the mesh boundary then this parameter determines which face is selected to start the contour. START-FACE should
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J-LINE POINT
Sec. 7.6 Fracture mechanics
be an integer in the range 0 - 4, inclusive. A zero value (the default) will cause the program to select the face opposite that of the second element in the contour definition. 1
face N1-N2.
2
face N2-N3.
3
face N3-N4.
4
face N4-N1.
(Where N1, N2, N3, N4 are the element vertex nodes.) END-FACE [0] If the last element of the contour does not have a unique face on the mesh boundary then this parameter determines which face is selected to terminate the contour. END-FACE should be an integer in the range 0 - 4, inclusive. A zero value (the default) will cause the program to select the face opposite that of the penultimate element in the contour definition. 1
face N1-N2.
2
face N2-N3.
3
face N3-N4.
4
face N4-N1.
(Where N1, N2, N3, N4 are the element vertex nodes.) Auxiliary commands LIST J-LINE POINT DELETE J-LINE POINT
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J-LINE RING
Chap. 7 Model definition
J-LINE RING
NAME NRING POINT PRINT SAVE START-FACE ENDFACE
J-LINE RING defines a line contour by using a “ring” number. A ring of elements is defined as follows. Given an origin node, ring number 1 consists of those elements connected at that node. Ring number 2 then consists of all elements connected to (and including) the elements in ring number 1, and so on. The line contour is defined by a series of elements. The “origin” node of the ring is taken to be the one coincident with a given geometry point.
element in J-LINE contour NRING=3
NAME [(current highest label number) + 1] Label number of the line contour to be defined. If the label number of an existing line contour is given, then the previous line contour definition is overwritten. NRING Determines the number of rings of elements around the “origin” node.
[0]
POINT The point label number. The node at this point is at the ring origin.
[0]
PRINT SAVE START-FACE [0] If the first element of the contour does not have a unique face on the mesh boundary then this parameter determines which face is selected to start the contour. START-FACE should
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J-LINE RING
Sec. 7.6 Fracture mechanics
be an integer in the range 0 - 4, inclusive. A zero value (the default) will cause the program to select the face opposite that of the second element in the contour definition. 1
face N1-N2.
2
face N2-N3.
3
face N3-N4.
4
face N4-N1.
(Where N1, N2, N3, N4 are the element vertex nodes.) END-FACE [0] If the last element of the contour does not have a unique face on the mesh boundary then this parameter determines which face is selected to terminate the contour. END-FACE should be an integer in the range 0 - 4, inclusive. A zero value (the default) will cause the program to select the face opposite that of the penultimate element in the contour defini- tion. 1
face N1-N2.
2
face N2-N3.
3
face N3-N4.
4
face N4-N1.
(Where N1, N2, N3, N4 are the element vertex nodes.) Auxiliary commands LIST J-LINE RING DELETE J-LINE RING
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J-VIRTUAL-SHIFT POINT
Chap. 7 Model definition
J-VIRTUAL-SHIFT POINT
NAME VECTOR VX VY VZ N3DSH NORMAL NX NY NZ THICKNESS POINT RADIUS
J-VIRTUAL-SHIFT POINT defines a virtual material shift by using a sphere defined by its center and radius.
RA
DI
US
POINT
nodes in virtual shift
NAME [(current highest label number) + 1] Label number of the virtual shift to be defined. If the label number of an existing virtual shift is given, then the previous virtual shift definition is overwritten. VECTOR [AUTOMATIC] Controls whether the actual material shift vector is calculated internally by ADINA, or is input via the global component values VX, VY, VZ below. AUTOMATIC
The shift vector is calculated automatically by ADINA, from the crack surface definition (see CRACK-PROPAGATION ). In the case of a 3-D crack, N3DSH is used to explicitly select a generator line associated with the automatic shift vector calculation.
INPUT
The shift vector is input directly via VX, VY, VZ.
VX VY VZ The global components of the material shift vector.
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J-VIRTUAL-SHIFT POINT
Sec. 7.6 Fracture mechanics
N3DSH [0] Identifies a generator line of the crack surface with automatic shift vector calculation for a 3-D crack. A zero value causes ADINA to calculate the shift vector based on the generator line whose crack tip node appears first in the list of nodes which comprises the virtual shift definition. NORMAL [NONE] Controls (for 3-D virtual material shift) whether or not the nodes of the shift are required to lie in a disk of given thickness. NONE
The nodes of the shift are not required to lie in a disk.
AUTOMATIC
The central plane of the disk is determined automatically from the crack surface definition. The plane is taken to be perpendicu lar to the crack tip node for the generator line associated with parameter N3DSH.
INPUT
The normal vector to the central plane of the disk is input via NX, NY, NZ. The central plane of the disk passes through the crack tip node for the generator line associated with parameter N3DSH.
NX [0.0] NY [0.0] NZ [0.0] The global components of the normal to the central plane of the disk in which shift nodes must lie. THICKNESS [1.0E-5] The thickness of the disk containing the shift nodes. If NORMAL ≠ NONE then a positive value for THICKNESS must be given. POINT The label number of the point which is the center of the sphere. RADIUS The radius of the sphere.
[0]
[0.0]
Auxiliary commands LIST J-VIRTUAL-SHIFT POINT DELETE J-VIRTUAL-SHIFT POINT
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J-VIRTUAL-SHIFT LINE
Chap. 7 Model definition
J-VIRTUAL-SHIFT LINE
NAME VECTOR VX VY VZ N3DSH
linei J-VIRTUAL-SHIFT LINE defines a virtual material shift. The shift is defined by those nodes lying on any of a given set of lines. NAME [(current highest label number) + 1] Label number of the virtual shift to be defined. If the label number of an existing virtual shift is given, then the previous virtual shift definition is overwritten. VECTOR [AUTOMATIC] Controls whether the actual material shift vector is calculated internally by ADINA, or is input via the global component values VX, VY, VZ below. AUTOMATIC
The shift vector is calculated automatically by ADINA, from the crack surface definition (see CRACK-PROPAGATION ). In the case of a 3-D crack, parameter N3DSH may be used to explicitly select a generator line associated with the automatic shift vector calculation.
INPUT
The shift vector is input directly via VX, VY, VZ.
VX VY VZ The global components of the material shift vector.
[0.0] [0.0] [0.0]
N3DSH [0] Identifies a generator line of the crack surface with automatic shift vector calculation for a 3-D crack. A zero value causes ADINA to calculate the shift vector based on the generator line whose crack tip node appears first in the list of nodes which comprises the virtual shift definition. linei Label number of a geometry line. Auxiliary commands LIST J-VIRTUAL-SHIFT LINE DELETE J-VIRTUAL-SHIFT LINE
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J-VIRTUAL-SHIFT SURFACE
Chap. 7 Model definition
J-VIRTUAL-SHIFT SURFACE
NAME VECTOR VX VY VZ N3DSH
surfacei J-VIRTUAL-SHIFT SURFACE defines a virtual material shift. The shift is defined by those nodes lying on any of a given set of surfaces. NAME [(current highest label number) + 1] Label number of the virtual shift to be defined. If the label number of an existing virtual shift is given, then the previous virtual shift definition is overwritten. VECTOR [AUTOMATIC] Controls whether the actual material shift vector is calculated internally by ADINA, or is input via the global component values VX, VY, VZ below. AUTOMATIC
The shift vector is calculated automatically by ADINA, from the crack surface definition (see CRACK-PROPAGATION ). In the case of a 3-D crack, parameter N3DSH may be used to explicitly select a generator line associated with the automatic shift vector calculation.
INPUT
The shift vector is input directly via VX, VY, VZ.
VX VY VZ The global components of the material shift vector.
[0.0] [0.0] [0.0]
N3DSH [0] Identifies a generator line of the crack surface with automatic shift vector calculation for a 3-D crack. A zero value causes ADINA to calculate the shift vector based on the generator line whose crack tip node appears first in the list of nodes which comprises the virtual shift definition.
surfacei Label number of a geometry surface. Auxiliary commands LIST J-VIRTUAL-SHIFT SURFACE DELETE J-VIRTUAL-SHIFT SURFACE
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J-VIRTUAL-SHIFT RING
Sec. 7.6 Fracture mechanics
J-VIRTUAL-SHIFT RING
NAME VECTOR VX VY VZ N3DSH NORMAL NX NY NZ THICKNESS RING-TYPE RING-NUMBER
namei J-VIRTUAL-SHIFT RING defines a virtual material shift by using a number of rings of elements around the crack front points. shifted elements
elements subject to virtual distortions NRING = 3
nodes in virtual shift
NAME [(current highest label number) + 1] Label number of the virtual shift to be defined. If the label number of an existing virtual shift is given, then the previous virtual shift definition is overwritten. VECTOR [AUTOMATIC] Controls whether the actual material shift vector is calculated internally by ADINA, or is input via the global component values VX, VY, VZ below. AUTOMATIC
The shift vector is calculated automatically by ADINA, from the crack surface definition (see CRACK-PROPAGATION ). In the case of a 3-D crack, parameter N3DSH may be used to explicitly select a generator line associated with the automatic shift vector calculation.
INPUT
The shift vector is input directly via VX, VY, VZ.
VX VY VZ The global components of the material shift vector. ADINA R & D, Inc.
[0.0] [0.0] [0.0]
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J-VIRTUAL-SHIFT RING
N3DSH [0] Identifies a generator line of the crack surface with automatic shift vector calculation for a 3-D crack. A zero value causes ADINA to calculate the shift vector based on the generator line whose crack tip node appears first in the list of nodes which comprises the virtual shift definition. NORMAL [NONE] Controls (for 3-D virtual material shift) whether or not the nodes of the shift are required to lie in a disk of given thickness. {NONE/AUTOMATIC/INPUT} NONE
The nodes of the shift are not required to lie in a disk.
AUTOMATIC
The central plane of the disk is determined automatically from the crack surface definition. The plane is taken to be perpendicular to the crack tip node for the generator line associated with parameter N3DSH.
INPUT
The normal vector to the central plane of the disk is input via NX, NY, NZ. The central plane of the disk passes through the crack tip node for the generator line associated with parameter N3DSH.
NX [0.0] NY [0.0] NZ [0.0] The global components of the normal to the central plane of the disk in which shift nodes must lie. THICKNESS [1.0E-5] The thickness of the disk containing the shift nodes. If NORMAL ≠ NONE, a positive value for THICKNESS must be given. RING-TYPE [POINT] The type of geometry on which the origin nodes lie. {POINT/LINE/SURFACE/NODE/ AUTOMATIC} POINT
The origin nodes are taken to be those at a set of points.
LINE
The origin nodes are taken to be those lying on a set of lines.
SURFACE
The origin nodes are taken to be those lying on a set of surfaces.
NODE
The origin nodes are directly specified in the data input lines.
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Sec. 7.6 Fracture mechanics
The origin nodes are automatically taken from all vertex nodes, see notes at the end of this command description. See the following note.
AUTOMATIC
Note:
When RING-TYPE=AUTOMATIC, the J-VIRTUAL-SHIFT RING command creates one virtual shift for each vertex node on the crack generator line. This generation is done by the ADINA command (creation of the .dat file).
RING-NUMBER Controls the number of rings of elements around the origin nodes. 0
Corresponds to a shift comprised of the origin nodes alone.
1
Includes the nodes of elements connected to the origin nodes.
[0]
Higher values of RING-NUMBER recursively define the shift such that RING-NUMBER = (n + 1) gives a shift including the nodes of elements containing any of the nodes defined in the shift given by RING-NUMBER = n. namei Label number of the geometry entries (point, line or surface) or nodes according to the parameter RING-TYPE. For 3-D material virtual shifts, if the geometry entities are points, these points must be vertices of elements, i.e. no points located at mid-side nodes should be specified. Auxiliary commands LIST J-VIRTUAL-SHIFT RING DELETE J-VIRTUAL-SHIFT RING
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R-CURVE
R-CURVE
Sec. 7.6 Fracture mechanics
NAME MPOINT
thetai x1i y1i x2i y2i . . . xmi ymi R-CURVE defines a resistance curve set which can be referenced by a crack growth analysis (see CRACK-GROWTH ). Note that (xji, yji) comprises a data point on the resistance curve associated with temperature “thetai”. The curve data is first sorted by increasing temperature “thetai”, then by increasing crack increment “xji”. If more than one data input line is entered, the values of “xji” must be the same for each data input line. NAME [(current highest R-CURVE label number) + 1] Label number of the resistance curve set to be defined. If the label number of an existing curve set is given, then the previous curve set definition is overwritten. MPOINT The maximum number of data points in any single resistance curve, defined in the subsequent data lines. thetai Reference temperature for resistance curve “i”. xji Crack increment value at data point “j” on resistance curve “i”. yji Resistance value at crack-increment “j” on resistance curve “i”. Auxiliary commands LIST R-CURVE DELETE R-CURVE
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SINGULAR POINT
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SINGULAR POINT
Q-POINT
pointi SINGULAR LINE
Q-POINT
linei SINGULAR defines a set of “singular” nodes on geometry points/lines. These are element vertex nodes whose adjacent non-vertex nodes are moved to the “1/4 point” giving a singularity at the required nodes.
node at ¼ point
singular node singular node
node at ¼ point
Singular vertex on TWODSOLID and THREEDSOLID elements
Q-POINT [QUARTER] Controls whether non-vertex nodes adjacent to the desired vertex nodes are moved to the “1/ 4 point”, or the opposite action is taken. QUARTER
Nodes are moved to the “1/4 point”.
MID
Nodes are moved from the “1/4 point” back to the relevant midside/face position.
pointi Label number of a singular geometry point.
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SINGULAR POINT
Sec. 7.6 Fracture mechanics
linei Label number of a geometry line defining a sequence of singular nodes, i.e., all element vertex nodes associated with the geometry line. Auxiliary commands LIST SINGULAR DELETE SINGULAR
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USER-RUPTURE
USER-RUPTURE reali
Sec. 7.6 Fracture mechanics
NAME NR NI
integeri
Specifies user-defined rupture data. NAME [(current highest USER-RUPTURE label number) + 1] USER-RUPTURE label name {> 0}. NR [0] Total number of user-defined real data. Note that NR + NI must be greater than zero. {≥ 0.0} NI [0] Total number of user-defined integer data. Note that NR + NI must be greater than zero. {≥ 0.0} reali User-defined real data.
[0]
integeri User-defined integer data.
[0]
Auxiliary commands LIST USER-RUPTURE DELETE USER-RUPTURE
slavenamei Specifies rigid links between pairs of nodes on entities. As the nodes move under model deformation, the “slave” node is constrained to translate and rotate such that the distance between the “master” node and the slave node remains constant and the rotations at the slave node are the same as the corresponding rotations at the master node. A rigid link can be specified only between nodes in the main structure, and the distance between the nodes must be greater than zero. The displacement degrees of freedom at the master node must all be independent, i.e., they cannot be constrained to other degrees of freedom. Fixity conditions may, however, be specified for the master node. Different skew degree-of-freedom systems may be assigned for the master and slave nodes. If either the master or slave node is a shell midsurface node, then six degrees of freedom is uesd for both nodes. Only the displacement degrees of freedom (translations and rotations) are constrained by a rigid link. Other degrees of freedom, e.g., pipe ovalization, warping, and fluid potential, are not constrained by a rigid link. NAME [(highest rigid link label number) + 1] The label number of the rigid link. SLAVETYPE [POINT] Indicates the type of entity used to specify slave nodes. {POINT/LINE/SURFACE/ EDGE/FACE/NODESET/VOLUME/BODY} SLAVENAME The label number of the slave entity (point, line, etc. as directed by parameter SLAVETYPE). MASTERTYPE [POINT] Indicates the type of the entity used to specify master nodes. {POINT/LINE/SURFACE/ EDGE/FACE/NODESET} MASTERNAME The label number of the master entity (point, line, etc. as directed by parameter MASTERTYPE).
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RIGIDLINK
Sec. 7.7 Boundary conditions
OPTION = 0 u
slave surface master line
v
u u
rigid links
rigid links v
u slave line
master surface u
OPTION = 1 u
slave line rigid links
u
u v
master line
u
rigid links v
slave surface
master surface
DISPLACEMENTS [DEFAULT] Specifies whether the constraint equations in ADINA are for kinematically linear (infinitesimal displacements), or large displacements. DISPLACEMENTS = DEFAULT indicates that displacements are controlled by the KINEMATICS command. {SMALL/LARGE/DEFAULT} OPTION [0] {0/1/2/3/4} When multiple nodes exist on both the slave and master geometry entities, OPTION indicates how the rigid link between nodes on each entity is defined.
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RIGIDLINK
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0
A rigid link is constructed between nodes at the corresponding parametric order on each entity. Parametric order is in the increasing u-parameter direction for lines, increasing u- then v-parameter for surfaces. In this case the number of nodes on the slave and master geometry entities must be the same.
1
A rigid link is constructed for each node on the slave geometry entity to the closest node on the master geometry entity. In this case, the number of nodes need not be the same for the slave and master geometry entities.
2
A rigid link is constructed between slave node to master node using reverse u parametric order. Applies to line/edge and surface/face.
3
A rigid link is constructed between slave node to master node using reverse v parametric order. Applies to surface/face.
4
A rigid link is constructed between slave node to master node using reverse u and v parametric order. Applies to surface/face.
SLAVEBODY [currently active BODY] Indicates the solid geometry body used to reference a slave edge or face when SLAVETYPE = EDGE or FACE, respectively. MASTERBODY [currently active BODY] Indicates the solid geometry body used to reference a master edge or face when MASTERTYPE = EDGE or FACE, respectively. Note:
Only the following SLAVETYPE, MASTERTYPE combinations are allowed:
SLAVETYPE POINT LINE LINE SURFACE SURFACE EDGE EDGE FACE FACE NODESET any
MASTERTYPE POINT POINT LINE POINT SURFACE POINT EDGE POINT FACE any NODESET
DOF Indicates whether all relevant slave DOFs are constrained to the master node. {ALL/MASTER} 7-336
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ALL
All relevant slave DOFs are constrained to the master node.
MASTER
The slave DOF is only constrained where the corresponding master DOF is not fixed. Note that DOF = MASTER is only used if DISPLACEMENTS = SMALL and all rotational degrees of freedom on the master node is fixed.
slavenamei Slave geometry label (TYPE = SLAVETYPE). If SLAVETYPE = EDGE or FACE , all Slave geometry belongs to SLAVEBODY. DOFSI [123456] Specifies the slave degrees of freedom (dof) to be constrained to the master node. DOFSI must contain 1 to 6 digits ranging from 1 to 6. Dofs 1, 2, 3 indicate X, Y, Z translations and 4, 5, 6 indicate X, Y, Z rotations. Auxiliary commands LIST RIGIDLINK DELETE RIGIDLINK
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CONSTRAINT
CONSTRAINT NAME SLAVETYPE SLAVENAME SLAVEDOF MASTERTYPE SBODY OPTION GENERALIZED-CONSTRAINT TRANSFORMATION masternamei masterdofi betai mbodyi Specifies a constraint set which expresses a slave (dependent) degree of freedom as a linear combination of a set of master (independent) degrees of freedom. The slave and master degrees of freedom are input by reference to geometry entities or node sets. A constraint equation can only reference nodes in the main structure. A constraint equation at a slave degree of freedom is unique. Therefore, if several constraint equations are input for the same slave degree of freedom, then only that for the highest label number will be used. A fluid potential slave degree of freedom can have only fluid potential master degrees of freedom, and a displacement (translation, rotation) slave degree of freedom can have only displacement master degrees of freedom. Constraint equations cannot refer to pipe ovalization or warping degrees of freedom. Note that constraint equations necessary to enforce a rigid link between two geometry entities can be defined using the RIGIDLINK command. NAME [(highest constraint set label number) + 1] The label number of the constraint set. SLAVETYPE [POINT] Indicates the type of entity used to specify slave nodes. {POINT/LINE/SURFACE/ VOLUME/EDGE/FACE/BODY/NODESET} SLAVENAME The label number of the slave entity as directed by SLAVETYPE. SLAVEDOF The degree of freedom associated with the slave geometry entity. {X-TRANSLATION/ YTRANSLATION/Z-TRANSLATION/X-ROTATION/Y-ROTATION/Z-ROTATION/ ALL-TRANSLATION/ALL-ROTATION/FLUID-POTENTIAL/TEMPERATURE} SLAVEDOF = TEMPERATURE is only available when MASTER TMC = YES. MASTERTYPE [POINT] Indicates the type of entity used to specify master nodes. {POINT/LINE/ SURFACE/
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CONSTRAINT
Sec. 7.7 Boundary conditions
EDGE/FACE/NODESET} Note:
Only the following SLAVETYPE, MASTERTYPE combinations are allowed:
SLAVETYPE POINT LINE SURFACE EDGE FACE NODESET VOLUME BODY
MASTERTYPE POINT,NODESET POINT,LINE,NODESET POINT,SURFACE,NODESET POINT,EDGE,NODESET POINT,FACE,NODESET any any any
SBODY [currently active body] The label number of the geometry slave body (used when SLAVETYPE=EDGE or FACE). OPTION [0] When multiple nodes exist on both the slave and master geometry entities, OPTION indicates how the constraint between nodes on each entity is defined. OPTION is only applicable when constraining line to line, edge to edge, surface to surface, and face to face. OPTION= 1 is used for all other cases. {0/1/2/3/4} 0
A constraint is constructed between nodes at the corresponding parametric order on each entity. Parametric order is in the increasing u-parameter direction for lines, increasing u- then v-parameter for surfaces. In this case the number of nodes on the slave and master geometry entities must be the same.
1
A constraint is constructed for each node on the slave entity to the closest node on the master entity. In this case, the number of nodes need not be the same for the slave and master entities.
2
Constrain slave node to master node using reverse u parametric order. Applies to line/edge and surface/face.
3
Constrain slave node to master node using reverse v parametric order. Applies to surface/face.
4
Constrain slave node to master node using reverse u and v parametric order.
GENERALIZED-CONSTRAINT Generate generalized constraints instead of standard constraints. {NO/YES}
[NO]
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CONSTRAINT
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TRANSFORMATION [0] Transformation label number which is applied to slave geometry entity when OPTION = 1. masternamei The label number of the master entity as directed by MASTERTYPE for the “i”th independent term of the constraint. masterdofi The degree of freedom of the master entity for the “i”th independent term of the constraint. Possible values are the same as for SLAVEDOF. betai [1.0] The coefficient of the “i”th independent term of the constraint. Note that this value remains constant throughout the time history of the response. A zero value is not accepted since it implies no contribution to the linear combination of independent master degrees of freedom. mbodyi [currently active body] The label number of the geometry master body (used when MASTERTYPE = EDGE or FACE). Note:
For a cyclic symmetric analysis, constraint equations may be applied to degrees of freedom within the fundamental part, but in this case similar constraint equations for corresponding degrees of freedom in all other cyclic parts of the structure will be applied.
Auxiliary commands LIST CONSTRAINT DELETE CONSTRAINT
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CONSTRAINT-MS
NAME MASTERTYPE MASTERNAME MASTERDOF SLAVETYPE MBODY OPTION GENERALIZED-CONSTRAINT
slavenamei slavedofi betai sbodyi This command is similar to the CONSTRAINT command. The difference between the CONSTRAINT-MS and CONSTRAINT commands is that CONSTRAINT-MS allows the specification of multiple slave entities for a single master entity. Note that constraint equations that are necessary to enforce a rigid link between two geometry entities can be defined using the RIGIDLINK command.
NAME [(highest constraint-ms set label number) + 1] The label number of the constraint-ms set. MASTERTYPE Indicates the type of the geometry entity used to specify master nodes. {POINT/LINE/SURFACE/VOLUME/EDGE/FACE/BODY/NODESET}
[POINT]
MASTERNAME The label number of the master entity as directed by MASTERTYPE. MASTERDOF The degree of freedom associated with the master entity. {X-TRANSLATION/Y-TRANSLATION/Z-TRANSLATION/X-ROTATION/ Y-ROTATION/Z-ROTATION/ALL-TRANSLATION/ALL-ROTATION/ FLUID-POTENTIAL/TEMPERATURE} SLAVEDOF = TEMPERATURE is only available when MASTER TMC = YES. SLAVETYPE Indicates the type of entity used to specify slave nodes. {POINT/LINE/SURFACE/VOLUME/EDGE/FACE/BODY/NODESET}
[POINT]
MBODY [currently active body] The label number of the geometry master body (used when MASTERTYPE=EDGE or FACE). OPTION [0] When multiple nodes exist on both the slave and master geometry entities, OPTION indicates how the constraint between nodes on each entity is defined.
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OPTION is only applicable when constraining line to line, edge to edge, surface to surface, and face to face. OPTION= 1 is used for all other cases.{0/1/2/3/4} 0
A constraint is constructed between nodes at the corresponding parametric order on each entity. Parametric order is in the increasing u-parameter direction for lines, increasing u- then v-parameter for surfaces. In this case the number of nodes on the slave and master geometry entities must be the same.
1
A constraint is constructed for each node on the slave geometry entity to the closest node on the master geometry entity. In this case, the number of nodes need not be the same for the slave and master entities.
2
Constrain slave node to master node using reverse u parametric order.
3
Constrain slave node to master node using reverse v parametric order. Applies to surface/face.
4
Constrain slave node to master node using reverse u and v parametric order. Applies to surface/face.
GENERALIZED-CONSTRAINT Generate generalized constraints instead of standard constraints. {NO/YES}
[NO]
slavenamei The label number of the slave entity as directed by SLAVETYPE for the “i”th independent term of the constraint. slavedofi The degree of freedom of the slave geometry entity for the “i”th independent term of the constraint. Possible values are the same as for MASTERDOF. betai [1.0] The coefficient of the “i”th independent term of the constraint. Note that this value remains constant throughout the time history of the response. A zero value is not accepted since it implies no contribution to the linear combination of independent master degrees of freedom. sbodyi [currently active body] The label number of the geometry slave body (used when SLAVETYPE = EDGE or FACE).
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Auxiliary commands LIST CONSTRAINT-MS FIRST LAST DELETE CONSTRAINT-MS FIRST LAST
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CONSTRAINT-G
CONSTRAINT-G
NAME
nodei dofi betai Defines a generalized linear constraint equation between specified degrees of freedom.
None of the degrees of freedom are made dependent (there are no slave degrees of freedom). The generalized constraints are imposed using Lagrange Multipliers, and can only be applied to nodes and not geometric entities. Note that GLUEMESH automatically creates generalized constraint equations that enforce glueing. NAME [(highest generalized constraint label number) + 1] Label number of the generalized constraint.
nodei Node label associated with the ith term (degree of freedom) in the generalized constraint equation. dofi Degree of freedom (global or skew direction) at nodei.{X-TRANSLATION / Y-TRANSLATION / Z-TRANSLATION / X-ROTATION / Y-ROTATION / Z-ROTATION} betai Coefficient for the ith term.
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FIXITY
Sec. 7.7 Boundary conditions
FIXITY
NAME
dofi FIXITY defines a fixity boundary condition which is referenced by FIXBOUNDARY, which assigns the fixity to a given geometry entity. All degrees of freedom are assumed free unless fixed by this command (subject to the overall control of active degrees of freedom as determined by MASTER ). NAME The identifying name of the fixity condition (1 to 30 alphanumeric characters). Note:
The following predefined fixities exist (and cannot be updated):
ALL
All degrees of freedom are fixed.
NONE
No degrees of freedom are fixed.
dofi Degree(s) of freedom to be fixed. {X-TRANSLATION/Y-TRANSLATION/ Z-TRANSLATION/X-ROTATION/Y-ROTATION/Z-ROTATION/OVALIZATION/ FLUID-POTENTIAL/PORE-FLUID-PRESSURE/BEAM-WARP} Note:
The fixity conditions will be applied to the nodes of the model, albeit indirectly, via the model geometry. The translations and rotations of the fixity thus refer to the degree-of-freedom system at each node, which may be the global coordinate system or a skewsystem. (See SKEWSYSTEM, DOF-SYSTEM ).
Auxiliary commands LIST FIXITY DELETE FIXITY
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FIXBOUNDARY POINTS
Chap. 7 Model definition
FIXBOUNDARY POINTS
FIXITY
pointi fixityi FIXBOUNDARY LINES
FIXITY
linei fixityi FIXBOUNDARY SURFACES
FIXITY
surfacei fixityi FIXBOUNDARY VOLUMES
FIXITY
volumei fixityi FIXBOUNDARYEDGES
FIXITY BODY
edgei fixityi FIXBOUNDARY FACES
FIXITY BODY
facei fixityi FIXBOUNDARY BODIES
FIXITY
bodyi fixityi FIXBOUNDARY NODE-SETS
FIXITY
node-seti fixityi FIXBOUNDARY assigns fixity conditions to a set of geometry entities. FIXITY [ALL] Default fixity condition (see command FIXITY ) for geometry entities given in the subsequent data lines. BODY Body label number.
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FIXBOUNDARY POINTS
Sec. 7.7 Boundary conditions
pointi Label number of a geometry point. linei Label number of a geometry line. surfacei Label number of a geometry surface. volumei Label number of a geometry volume. edgei Label number of a geometry edge (for BODY). facei Label number of a geometry face (for BODY). bodyi Label number of a geometry body. node-seti Label number of a node-set. fixityi Fixity condition to be applied at the geometry entity.
[FIXITY]
Auxiliary commands LIST FIXBOUNDARY POINTS DELETE FIXBOUNDARY POINTS
FIRST LAST FIRST LAST
LIST FIXBOUNDARY LINES DELETE FIXBOUNDARY LINES
FIRST LAST FIRST LAST
LIST FIXBOUNDARY SURFACES DELETE FIXBOUNDARY SURFACES
FIRST LAST FIRST LAST
LIST FIXBOUNDARY VOLUMES DELETE FIXBOUNDARY VOLUMES
FIRST LAST FIRST LAST
LIST FIXBOUNDARY EDGES DELETE FIXBOUNDARY EDGES
FIRST LAST FIRST LAST
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LIST FIXBOUNDARY FACES DELETE FIXBOUNDARY FACES
FIRST LAST FIRST LAST
LIST FIXBOUNDARY BODIES DELETE FIXBOUNDARY BODIES
FIRST LAST FIRST LAST
LIST FIXBOUNDARY NODE-SETS DELETE FIXBOUNDARY NODE-SETS
FIRST LAST FIRST LAST
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ZOOM-BOUNDARY
Sec. 7.7 Boundary conditions
ZOOM-BOUNDARY
NAME GTYPE
namei bodyi Specifies the boundary of a mesh overlay model that is inside (internal to) the coarse model (see Figure A). Note that if no zoom boundary is defined, all the boundary of the mesh overlay model will be treated as being inside the coarse model (see Figure B, next page).
This part of the boundary of the mesh overlay needs to be specified as internal boundary
Mesh overlay model
Coarse model
Figure A: Internal boundary must be defined
NAME [current highest ZOOM-BOUNDARY label number + 1] Label number of the ZOOM-BOUNDARY to be defined. GTYPE {TWO-D / THREE-D / NODESET}
[TWO-D]
The geometry type used to define ZOOM-BOUNDARY. TWO-D THREE-D NODESET
line or edge surface or face node set
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Chap. 7 Model definition
Since the mesh overlay model is completely inside the coarse model, there is no need to identify the internal boundary.
Mesh Overlay Model
Coarse Model
Figure B: No need to define internal boundary
namei List of geometry label numbers or node set numbers. bodyi Geometry body label of edges and faces. Auxiliary commands LIST ZOOM-BOUNDARY FIRST LAST DELETE ZOOM-BOUNDARY FIRST LAST
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Sec. 7.7 Boundary conditions
ENDRELEASE
ENDRELEASE
NAME MOMENT1 MOMENT2 MOMENT3 MOMENT4 MOMENT5 MOMENT6
Defines an “endrelease” condition for elements of type BEAM, which may be used to prescribe that selected end forces and/or moments of the elements are zero. The endrelease may be referenced (e.g. by LINE-ELEMDATA ) to assign the endrelease to the elements (on a given geometry line). node AUX lies in r-s plane
AUX
s
S8
r
S11
t
S7 S10
S2 S12
S5 S4 S1
S9
node 2 S6
S3
neutral axis
Z
node 1
X
Y
NAME [(current highest endrelease label number) + 1] The label number of the endrelease condition to be defined. MOMENTi [0] List of up to six identifiers (i = 1,...,6) indicating which of the element end forces on moments are prescribed to be zero. See Figure. 1
Force in r-direction at local node 1 = 0.0.
2
Force in s-direction at local node 1 = 0.0.
3
Force in t-direction at local node 1 = 0.0.
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ENDRELEASE
4
Moment about r-axis at local node 1 = 0.0.
5
Moment about s-axis at local node 1 = 0.0.
6
Moment about t-axis at local node 1 = 0.0.
7
Force in r-direction at local node 2 = 0.0.
8
Force in s-direction at local node 2 = 0.0.
9
Force in t-direction at local node 2 = 0.0.
10
Moment about r-axis at local node 2 = 0.0.
11
Moment about s-axis at local node 2 = 0.0.
12
Moment about t-axis at local node 2 = 0.0.
0
No selection.
Auxiliary commands LIST ENDRELEASE DELETE ENDRELEASE
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FSBOUNDARY
FSBOUNDARY LINES
Sec. 7.7 Boundary conditions
NAME
linei FSBOUNDARY SURFACES
NAME
surfacei FSBOUNDARY EDGES
NAME BODY
edgei FSBOUNDARY FACES
NAME BODY
facei Defines a fluid-structure-interaction boundary, as a set of geometry lines/edges (2-D analysis), or as a set of geometry surfaces/faces (3-D analysis), which establish those areas of the structure, which may interact with fluid flow. Note that the FSBOUNDARY defined is not referenced by another ADINA-IN for ADINA command, but may be referenced by the BOUNDARY-CONDITION FLUID-STRUCTURE command for ADINA-F. NAME [(current highest fsboundary label number) + 1] Label number of the fluid-structure-boundary to be defined. BODY Body label number. linei Geometry line label number. surfacei Geometry surface label number. edgei Geometry edge label number (for BODY). facei Geometry face label number (for BODY). Auxiliary commands LIST FSBOUNDARY DELETE FSBOUNDARY
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FSBOUNDARY TWO-D
FSBOUNDARY TWO-D
NAME
namei bodyi Defines a fluid-structure-interaction boundary, as a set of geometry lines/edges (2D analysis) that establish those areas of the structure to be analysed using ADINA. This boundary may interact with a fluid flow analysed by ADINA-F. Note that the FSBOUNDARY defined is not referenced by another ADINA-IN for ADINA command, but rather may be referenced by the BOUNDARY-CONDITION FLUID-STRUCTURE command for ADINA-F. NAME [(current highest fsboundary label number) + 1] Label number of the fluid-structure-boundary to be defined. namei Geometry line/edge label number. bodyi Geometry body label number. Auxiliary commands LIST FSBOUNDARY DELETE FSBOUNDARY
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FSBOUNDARY THREE-D
FSBOUNDARY THREE-D
Sec. 7.7 Boundary conditions
NAME
namei bodyi Defines a fluid-structure-interaction boundary, as a set of geometry surfaces/faces (3D analysis) that establish those areas of the structure to be analysed using ADINA. This boundary may interact with a fluid flow analysed by ADINA-F. Note that the FSBOUNDARY defined is not referenced by another ADINA-IN for ADINA command, but rather may be referenced by the BOUNDARY-CONDITION FLUID-STRUCTURE command for ADINA-F. NAME [(current highest fsboundary label number) + 1] Label number of the fluid-structure-boundary to be defined. namei Geometry line/edge label number. bodyi Geometry body label number. Auxiliary commands LIST FSBOUNDARY DELETE FSBOUNDARY
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POTENTIAL-INTERFACE
POTENTIAL-INTERFACE ADINA-F
NAME GTYPE BODY
POTENTIAL-INTERFACE FLUID-FLUID
NAME GTYPE BODY
POTENTIAL-INTERFACE FLUID-STRUCTUR
NAME GTYPE BODY
POTENTIAL-INTERFACE FREE-SURFACE
NAME GTYPE BODY
POTENTIAL-INTERFACE INLET-OUTLET
NAME GTYPE BODY
POTENTIAL-INTERFACE RIGID-WALL
NAME GTYPE BODY
namei bodyi Defines an interface between potential-based fluid elements and structural elements. NAME [(current potential-interface label number) + 1] Label number of the potential-interface to be defined. GTYPE The type of geometry used to define the potential-interface. {LINES/SURFACES/EDGES/FACES/THREE-D/NODES/NODESETS}
[LINES]
BODY [1] Label number of a solid geometry body. Must be specified when GTYPE=EDGES or FACES. namei Label number of a geometry entity or node. bodyi [0] Label number of a solid geometry body. Used when GTYPE=THREE-D and namei is a face. bodyi=0 means that namei is a surface.
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POTENTIAL-INTERFACE
Sec. 7.7 Boundary conditions
Auxiliary commands LIST POTENTIAL-INTERFACE DELETE POTENTIAL-INTERFACE
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POTENTIAL-INTERFACE INFINITE
Chap. 7 Model definition
POTENTIAL-INTERFACE INFINITE
NAME GTYPE BODY INFTYPE RADIUS PRESSURE VELOCITY ALL-EXT
namei bodyi Defines an interface between potential-based fluid elements and an infinite boundary. NAME [(current potential-interface label number) + 1] Label number of the potential-interface to be defined. GTYPE The type of geometry used to define the infinite potential-interface. {LINES/SURFACES/EDGES/FACES/THREE-D/NODESETS}
[LINES]
BODY [1] Label number of a solid geometry body. Must be specified when GTYPE=EDGES or FACES. INFTYPE The type of infinite boundary. {PLANAR/CYLINDRICAL/SPHERICAL} RADIUS The radius of cylinder or sphere.
[PLANAR]
[1.0]
PRESSURE [0.0] The pressure at infinity, used only for a planar infinite boundary in conjunction with the subsonic formulation for the potential-based fluid elements. VELOCITY [0.0] The velocity at infinity, used only for a planar infinite boundary in conjunction with the subsonic formulation for the potential-based fluid elements. The velocity is assumed to be normal to the planar boundary and is positive for flow out of the planar boundary. ALL-EXT namei Label number of a geometry entity or node. bodyi [0] Label number of a solid geometry body. Used when GTYPE=THREE-D and namei is a face. bodyi=0 means that namei is a surface.
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POTENTIAL-INTERFACE INFINITE
Sec. 7.7 Boundary conditions
Auxiliary commands LIST POTENTIAL-INTERFACE DELETE POTENTIAL-INTERFACE
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BOUNDARY-SURFACE SURFACE-TENSION
Chap. 7 Model definition
BOUNDARY-SURFACE SURFACE-TENSION
NAME GTYPE ALL-EXT NODES SUBTYPE SIGMAT
namei bodyi Defines a surface tension boundary for ADINA. NAME [(current highest surface-tension label number) + 1] Label number of the surface-tension to be defined. GTYPE The type of geometry used to define the surface boundary condition. {TWO-D/THREE-D/ELEMENT-EDGESET/ELEMENT-FACESET}
[TWO-D]
ALL-EXT (Currently not used) NODES Number of nodes for each element. Only used if the surface tension boundary is not attached to any finite elements. {0/2/3/4/8/9}
[0]
SUBTYPE [PLANE] The type of 2-D surface tension boundary. Only used if the boundary is not attached to any finite elements. If the boundary is attached to finite elements, the subtype of the 2-D finite elements will be used. {AXISYMMETRIC/PLANE} SIGMAT Surface tension value.
[0.0]
namei Label number of a geometry entity or element edge/face set. bodyi [0] Label number of a solid geometry body. Used when GTYPE=TWO-D/THREE-D and namei is a face or edge. bodyi=0 means that namei is a surface or line. Auxiliary commands LIST BOUNDARY-SURFACE DELETE BOUNDARY-SURFACE
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BOUNDARY-SURFACE SURFACE-TENSION
Sec. 7.7 Boundary conditions
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OVALIZATION-CONSTRAINT POINT
Chap. 7 Model definition
OVALIZATION-CONSTRAINT POINT
TYPE
pointi Enforces the zero-slope-of-skin in the longitudinal direction for pipe element nodes. TYPE FLANGE
The flange condition is applied at the specified points. Both ovalization and warping at these points are suppressed.
SYMMETRY
The symmetry condition is applied to the specified points. The ovalization at these points is left free but the warping suppressed.
pointi A point label number where the constraint of the ovalization derivative is enforced. Auxiliary commands LIST OVALIZATION-CONSTRAINT POINT DELETE OVALIZATION-CONSTRAINT POINT
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FREESURFACE
Sec. 7.7 Boundary conditions
FREESURFACE linei
(for FLUID2 element groups)
or surfacei
(for FLUID3 element groups)
Defines the free surface on the boundary lines (2-D) or surface (3-D) of previously-defined surfaces (2-D) or volumes (3-D) consisting of potential-based elements. linei Geometry line label number. surfacei Geometry surface label number.
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BCELL
BCELL
NAME REVERSE
celli n1i n2i n3i n4i Defines a boundary cell using 4-node or 3-node cells. A boundary cell must be defined by all 3-node cells or all 4-node cells. It cannot be defined by a mixture of 3-node and 4-node cells. NAME [(current highest bcell label number) + 1] Label number of the boundary cell to be defined. REVERSE {NO/YES} Normal direction reverse flag.
[NO]
celli Cell label number. n1i n2i n3i n4i Node labels for celli . Auxiliary commands LIST BCELL DELETE BCELL
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BCELL
Sec. 7.7 Boundary conditions
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LOAD CENTRIFUGAL
Chap. 7 Model definition
LOAD CENTRIFUGAL
NAME OMEGA FACTOR AX AY AZ BX BY BZ ALPHA
Defines a combination of a centrifugal load and a tangential load. The centrifugal load vector is calculated as (mass) × OMEGA2 × FACTOR × f(t) × (radius) and the tangential load vector is calculated as (mass) × ALPHA × FACTOR × f(t) × (radius) when ALPHA is non-zero.
ALPHA (a) OMEGA (w)
Z
tangential forces (// a x ri )
(BX, BY, BZ)
Y
centrifugal forces ri
X
(AX, AY, AZ)
structure
where “mass” is a concentrated nodal point mass or a differential mass element at a distance “radius” from the axis of revolution. The load may be applied to the model via APPLY-LOAD whereby it may also be assigned a time function, specifying how its magnitude varies in time. Only one centrifugal load may currently be applied to the model.
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LOAD CENTRIFUGAL
Sec. 7.8 Loading
NAME
[(current highest centrifugal load label number) + 1] Label number of the centrifugal load to be defined. OMEGA Angular velocity. FACTOR Multiplying factor. AX [0.0] AY [0.0] AZ [0.0] Position vector (in global coordinate system) of one end of axis of revolution, see Figure. BX [1.0] BY [0.0] BZ [0.0] Position vector (in global coordinate system) of other end of axis of revolution. See Figure. ALPHA Angular acceleration.
[0.0]
Auxiliary commands LIST LOAD CENTRIFUGAL DELETE LOAD CENTRIFUGAL
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LOAD CONTACT-SLIP
Chap. 7 Model definition
LOAD CONTACT-SLIP
NAME OMEGA FACTOR AX AY AZ BX BY BZ
Defines a contact-slip load. The actual tangential slip of a contact surface is calculated as OMEGA * FACTOR * (RADIUS) * F(t) The load may be applied to a contact surface via command APPLY-LOAD whereby it may also be assigned a time function F(t), specifying how its magnitude varies with time. NAME [(current highest contact-slip load label number) + 1] Label number of the contact-slip load to be defined. If the label number of an existing contactslip load is given, then the previous contact-slip load definition is overwritten. OMEGA Angular velocity. FACTOR Multiplying factor. AX AY AZ Position vector (in global coordinate system) of one end of axis of revolution.
[0.0] [0.0] [0.0]
BX BY BZ Position vector (in global coordinate system) of other end of axis of revolution.
[1.0] [0.0] [0.0]
Auxiliary commands LIST LOAD CONTACT-SLIP DELETE LOAD CONTACT-SLIP
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LOAD CONVECTION
LOAD CONVECTION
Sec. 7.8 Loading
NAME MAGNITUDE C-PROP
Defines a convection load, i.e., prescribed environmental temperatures for convection element nodes. Note that the command only defines a convection load, to apply it to the model you must use APPLY-LOAD. NAME [(current highest convection load label number) + 1] Label number of the convection load to be defined. MAGNITUDE Environmental temperature (in chosen units). C-PROP [0] The label number of convection property command C-PROP. It is only used for ADINA TMC analysis. In TMC analysis, if C-PROP = 0 means parameters TYPE = CONSTANT and H = 0.0 in the C-PROP command.
Auxiliary commands LIST LOAD CONVECTION FIRST LAST DELETE LOAD CONVECTION FIRST LAST
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LOAD DISPLACEMENT
LOAD DISPLACEMENT
Sec. 7.8 Loading
NAME DX DY DZ AX AY AZ
Defines a prescribed displacement load. This command defines prescribed displacements which may be assigned to certain degrees of freedom (global or skew) of the model. Note that this command only defines a displacement load, to apply it to the model you must use APPLY-LOAD. NAME [(current highest displacement load label number) + 1] Label number of the displacement load to be defined. DX [FREE] Prescribed value for the X-translation (or a-translation for a skew dof-system) degree of freedom. DY [FREE] Prescribed value for the Y-translation (or b-translation for a skew dof-system) degree of freedom. DZ [FREE] Prescribed value for the Z-translation (or c-translation for a skew dof-system) degree of freedom. AX [FREE] Prescribed value for the X-rotation (or a-rotation for a skew dof-system) degree of freedom, in radians. AY [FREE] Prescribed value for the Y-rotation (or b-rotation for a skew dof-system) degree of freedom, in radians. AZ [FREE] Prescribed value for the Z-rotation (or c-rotation for a skew dof-system) degree of freedom, in radians. Note:
For parameters DX, DY, DZ, AX, AY, AZ the value FREE may be specified, indicating that the corresponding degree of freedom is not prescribed.
Auxiliary commands LIST LOAD DISPLACEMENT DELETE LOAD DISPLACEMENT
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LOAD ELECTROMAGNETIC
Chap. 7 Model definition
LOAD ELECTROMAGNETIC
NAME
Defines an electromagnetic load. Note that the command only defines a electromagnetic load, to apply it to the model you must use APPLY-LOAD. NAME
[(current highest electromagnetic load label number)+ 1] Label number of the electromagnetic load to be defined. Note:
The magnitude of the load is governed by the currents specified by the timefunction parameter of APPLY-LOAD.
Auxiliary commands LIST LOAD ELECTROMAGNETIC DELETE LOAD ELECTROMAGNETIC
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LOAD FORCE
LOAD FORCE
Sec. 7.8 Loading
NAME MAGNITUDE FX FY FZ
Defines a force load. Note that the command only defines a force load, to apply it to the model you must use APPLY-LOAD. NAME
[(current highest force load label number) + 1]
Label number of the force load to be defined. MAGNITUDE Force magnitude. FX FY FZ Force direction. Note:
[1.0] [0.0] [0.0]
The vector (FX, FY, FZ) specifies only the direction of the force.
Auxiliary commands LIST LOAD FORCE DELETE LOAD FORCE
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LOAD LINE
Chap. 7 Model definition
LOAD LINE
NAME MAGNITUDE
Defines a line load, i.e., a distributed load in terms of force / unit length. Note that the command only defines a line load, to apply it to the model you must use APPLY-LOAD. Note that line loads may be applied to geometry lines or edges, in order to specify distributed loading to BEAM, ISOBEAM, and PIPE elements, and to edges of SHELL elements. NAME
[(current highest line load label number) + 1]
Label number of the line load to be defined. MAGNITUDE Distributed load magnitude [force / unit length]. Auxiliary commands LIST LOAD FORCE DELETE LOAD FORCE
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LOAD MASS-PROPORTIONAL
Sec. 7.8 Loading
LOAD MASS-PROPORTIONAL NAME MAGNITUDE AX AY AZ INTERPRETATION Defines a mass-proportional load. Such loads may be used to model gravity loading (including static analysis) or ground acceleration. The load acts uniformly on the entire structure. APPLY-LOAD is used to apply a mass-proportional load to the model, at which time it may be assigned a time function specifying how its magnitude varies in time. More than one mass-proportional load may be applied to the model. NAME
[(current highest mass-proportional load label number) + 1] Label number of the mass-proportional load to be defined. MAGNITUDE Magnitude of mass-proportional loading. AX [0.0] AY [0.0] AZ [-1.0] Vector giving direction of mass-proportional load. Note the components of the massproportional loading are: MAGNITUDE × AX MAGNITUDE × AY MAGNITUDE × AZ
i.e., the magnitude of vector (AX, AY, AZ) is used together with MAGNITUDE to give the total load vector. INTERPRETATION [BODY-FORCE] Flag indicating static or dynamic effect for potential-based fluid elements: BODY-FORCE
The load is interpreted as a physical body force
GROUND-ACCELERATION
The load is interpreted as a ground motion acceleration, and is numerically integrated to obtain ground motion velocities and displacements.
This parameter is used only by potential-based fluid elements and is not used by any of the other element types.
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LOAD MASS-PROPORTIONAL
Auxiliary commands LIST LOAD MASS-PROPORTIONAL DELETE LOAD MASS-PROPORTIONAL
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LOAD MOMENT
LOAD MOMENT
Sec. 7.8 Loading
NAME MAGNITUDE MX MY MZ
Defines a moment load. Note that the command only defines a moment load, to apply it to the model you must use APPLY-LOAD. NAME [(current highest moment load label number) + 1] Label number of the moment load to be defined. MAGNITUDE Moment magnitude. MX MY MZ Components of moment vector. Note:
[1.0] [0.0] [0.0]
The vector (MX, MY, MZ) specifies only the direction of the moment axis.
Auxiliary commands LIST LOAD MOMENT DELETE LOAD MOMENT
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LOAD NODAL-PHIFLUX
Chap. 7 Model definition
LOAD NODAL-PHIFLUX
NAME MAGNITUDE
Defines a nodal-phiflux load. This command defines a prescribed nodal-phiflux which may be assigned to certain degrees of freedom of the model. Note that this command only defines a nodal-phiflux load — to apply it to the model you must use command APPLY-LOAD.
NAME [(current highest nodal-phiflux load label number) + 1] Label number of the nodal-phiflux load to be defined. If the label number of an existing nodalphiflux load is given, then the previous nodal-phiflux load definition is overwritten. MAGNITUDE Prescribed value for the fluid potential degree of freedom.
Auxiliary commands LIST LOAD NODAL-PHIFLUX DELETE LOAD NODAL-PHIFLUX
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LOAD PHIFLUX
LOAD PHIFLUX
Sec. 7.8 Loading
NAME MAGNITUDE
Defines a phiflux load. Note that this command only defines a phiflux load — to apply it to the model you must use command APPLY-LOAD.
NAME [(current highest phiflux load label number) + 1] Label number of the phiflux load to be defined. If the label number of an existing phiflux load is given, then the previous phiflux load definition is overwritten. MAGNITUDE Prescribed value for the fluid potential degree of freedom.
Auxiliary commands LIST LOAD PHIFLUX DELETE LOAD PHIFLUX
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LOAD PIPE-INTERNAL-PRESSURE
LOAD PIPE-INTERNAL-PRESSURE
Sec. 7.8 Loading
NAME MAGNITUDE
Defines a pipe-internal-pressure load. Note that the command only defines a pipe-internalpressure load, to apply it to the model you must use APPLY-LOAD. NAME
[(current highest pipe-internal-pressure load label number) + 1] Label number of the pipe-internal-pressure load to be defined. MAGNITUDE Pipe internal pressure magnitude (force / unit area). Auxiliary commands LIST LOAD PIPE-INTERNAL-PRESSURE DELETE LOAD PIPE-INTERNAL-PRESSURE
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LOAD POREFLOW
Chap. 7 Model definition
LOAD POREFLOW
NAME MAGNITUDE
Defines a poreflow load. Poreflow loads may be applied ( command APPLY-LOAD ) to surfaces (element groups THREEDSOLID, TWODSOLID- subtype STRESS3 ) or lines ( TWODSOLID element edges ). NAME [(current highest poreflow load label number) + 1] Label number of the poreflow load to be defined. If the label number of an existing poreflow load is given, then the previous poreflow load definition is overwritten. MAGNITUDE Flux magnitude (velocity). Auxiliary commands LIST LOAD POREFLOW FIRST LAST The command LIST LOAD POREFLOW lists the loads of type POREFLOW with label numbers in a given range. If no range is specified, then a list of all the label numbers of loads of type POREFLOW is given. DELETE LOAD POREFLOW FIRST LAST The command DELETE LOAD POREFLOW deletes all loads of type POREFLOW with label numbers in a given range. Note:
A load will not be deleted if it is referenced by the command APPLY-LOAD (i.e. the load has been applied to the model).
Note:
For command DELETE LOAD POREFLOW, one of the parameters FIRST, LAST must be specified.
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LOAD PORE-PRESSURE
LOAD PORE-PRESSURE
Sec. 7.8 Loading
NAME MAGNITUDE
Defines a pore-pressure load, which may be assigned to certain degrees of freedom (global or skew) of the model. To apply a pore-pressure load to the model command APPLY-LOAD should be used. NAME
[(current highest pore-pressure load label number) + 1] Label number of the pore-pressure load to be defined. If the label number of an existing porepressure load is given, then the previous pore-pressure load definition is overwritten. MAGNITUDE Prescribed value for the pore pressure degree of freedom. Auxiliary commands LIST LOAD PORE-PRESSURE DELETE LOAD PORE-PRESSURE
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LOAD PRESSURE
Chap. 7 Model definition
LOAD PRESSURE
NAME MAGNITUDE BETA LINE
Defines a pressure load. Note that the command only defines a pressure load, to apply it to the model you must use APPLY-LOAD. Note:
To apply distributed loads to uni-dimensional elements (e.g., beams) or to edges of shell elements, command LOAD LINE should be used to define such a load in terms of force/unit length. Note that for potential-based elements, pressure loads may be applied only on the boundary of fluid-structure, free-surface, inlet-outlet or fluid-fluid interface elements. NAME
Label number of the pressure load to be defined. MAGNITUDE Pressure magnitude [force / unit area]. BETA [0.0] Specifies the angle to the reference line (LINE) that will determine the direction of the tangential traction. (in degrees) LINE [0] Reference line for tangential traction direction. If LINE=0, the reference direction for the tangential traction will be the parametric u-dir of the surface or face. Note:
The parameters BETA and LINE are only applicable when applying pressure loading on surface/face and the tangential pressure loading is specified (i.e. idirn=4 in command APPLY-LOAD).
Auxiliary commands LIST LOAD PRESSURE DELETE LOAD PRESSURE
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LOAD RADIATION
LOAD RADIATION
Sec. 7.8 Loading
NAME MAGNITUDE R-PROP
Defines a radiation load, i.e., prescribed radiative source/sink temperatures, at radiation element nodes. Note that the command only defines a radiation load, to apply it to the model you must use APPLY-LOAD. NAME [(current highest radiation load label number) + 1] Label number of the radiation load to be defined. MAGNITUDE Radiative source/sink temperature (in chosen units). R-PROP [0] The label number of convection property command R-PROP. It is only used for ADINA TMC analysis. In TMC analysis, if R-PROP = 0 means parameters TYPE = CONSTANT and E = 0.0 in the R-PROP command. Auxiliary commands LIST LOAD RADIATION FIRST LAST DELETE LOAD RADIATION FIRST LAST
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LOAD TEMPERATURE
LOAD TEMPERATURE
Sec. 7.8 Loading
NAME MAGNITUDE
Defines a prescribed temperature load. Note that the command only defines a temperature load, to apply it to the model you must use APPLY-LOAD. NAME
[(current highest temperature load label number) + 1] Label number of the temperature load to be defined. MAGNITUDE Temperature (in chosen units). Auxiliary commands LIST LOAD TEMPERATURE DELETE LOAD TEMPERATURE
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LOAD TGRADIENT
Chap. 7 Model definition
LOAD TGRADIENT
NAME MAGNITUDE
Defines a prescribed temperature gradient load to specify the temperature gradient in the thickness direction of a surface (when applied to shell elements). Note that the command only defines a temperature gradient load, to apply it to the model you must use APPLY-LOAD. NAME
[(current highest temperature gradient load label number) + 1] Label number of the temperature gradient load to be defined. MAGNITUDE Temperature gradient (degrees / unit length). Auxiliary commands LIST LOAD TGRADIENT DELETE LOAD TGRADIENT
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CPROP
Sec. 7.8 Loading
C-PROP NAME TYPE H ITHETA TBIRTH TDEATH ti hi Defines convection properties for convection loading. NAME The label number of the C-PROP to be defined.
[(Current highest label) + 1]
TYPE The type of convection property. {CONSTANT/TEMP-DEP/TIME-DEP} CONSTANT
Property is constant
TEMP-DEP
Property is temperature dependent
TIME-DEP
Property is time dependent
[CONSTANT]
H Convection coefficient. Used for TYPE = CONSTANT only. { ≥ 0.0}
[0.0]
ITHETA [TEMPERATURE] Indicates the dependence of the convection coefficient. Used for TYPE = TEMP-DEP only. {TEMPERATURE/DIFFERENCE} TEMPERATURE
Convection coefficient is a function of surface temperature
DIFFERENCE
Convection coefficient is a function of temperature difference
TBIRTH [0.0] Birth time for convection boundary, i.e., time at which the convection boundary becomes active. TDEATH [0.0] Death time for convection boundary, i.e. time at which the convection boundary becomes inactive. Note that TDEATH=0.0 has no effect. ti Temperature at data point i for ITHETA = TEMPERATURE Temperature difference at data point i for ITHETA = DIFFERENCE Time at data point i for TYPE = TIME-DEP hi Convection coefficient at ti
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RPROP
R-PROP NAME TYPE E ISIGMA SIGMA TBIRTH TDEATH t i ei Define radiation properties for radiation loading. NAME The label number of the R-PROP to be defined.
[(Current highest label) + 1]
TYPE The type of radiation property. {CONSTANT/TEMP-DEP} CONSTANT
Property is constant
TEMP-DEP
Property is temperature dependent
E Emissivity coefficient Used for TYPE = CONSTANT only. { ≥ 0.0}
[CONSTANT]
[0.0]
ISIGMA [FAHRENHEIT] Unit of temperature. {FAHRENHEIT/CENTIGRADE/KELVIN/RANKINE} SIGMA Stefan-Boltzmann constant. { ≥ 0.0}
[0.0]
TBIRTH [0.0] Birth time for radiation boundary, i.e., time at which the convection boundary becomes active. TDEATH [0.0] Death time for radiation boundary, i.e. time at which the convection boundary becomes inactive. Note that TDEATH=0.0 has no effect. ti temperature at data point i ei Emissivity coefficient at ti
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LOAD-CASE
LOAD-CASE
Sec. 7.8 Loading
NAME
LOAD-CASE may be used in a linear static analysis to identify the current load case. LOAD-CASE cannot be used in the analysis of a cyclic symmetric structure. If load cases are specified, no reference to, or specification of, time functions can be made. Therefore, use of the commands TIMEFUNCTION, TIMESTEP, or any timefunction reference by any APPLY-LOAD command, is not allowed. NAME
[(current highest load-case label number) + 1]
Label number of the load-case to be defined. Auxiliary commands LIST LOAD-CASE DELETE LOAD-CASE
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LCOMBINATION
Chap. 7 Model definition
LCOMBINATION
NAME
lcasei factori May be used in a linear static analysis to define a new load case as a linear combination of load cases previously defined by LOAD-CASE. The combination is performed so that (combined load-case results) =
Σ (results for lcase ) × factor i
i
i=1
NAME [(highest lcombination label number) + 1] The label number of the load-combination. lcasei The label number of a load case previously defined by command LOAD-CASE. factori The factor associated with lcasei.
[1.0]
Auxiliary commands LIST LCOMBINATION DELETE LCOMBINATION
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APPLY-LOAD
APPLY-LOAD
Sec. 7.8 Loading
BODY LCASE SHELLNODE
namei ltypei lnamei stypei snamei idvari ncuri artmi idirn iddli pfocusi bodyi psensei i unloadi timeui forceui ncurui cgroupi shellnodei (no load cases) or namei ltypei lnamei stypei snamei idvari lcasei idirni iddli pfocusi bodyi psensei unloadi timeui forceui ncurui cgroupi shellnodei (load cases) Command APPLY-LOAD specifies the loads applied to a model. This command is used to apply named loads (see commands LOAD FORCE, LOAD MOMENT, LOAD PRESSURE, etc.) to the model geometry. The spatial variation of the load may be specified by reference to a data-line, data-surface, or data-volume as appropriate (see command LINE-FUNCTION, SURFACE-FUNCTION, VOLUME-FUNCTION ). The time dependence of the load may be specified by reference to a time function (see command TIMEFUNCTION ). BODY Solid geometry body label number.
[currently active BODY]
LCASE Load-case number (see LOAD-CASE, LCOMBINATION ).
[1]
namei Label number of a load application. ltypei The type of load to be applied. {FORCE/MOMENT/PRESSURE/LINE/CENTRIFUGAL/ MASS-PROPORTIONAL/DISPLACEMENT/TEMPERATURE/TGRADIENT/PIPEINTERNAL-PRESSURE/ELECTROMAGETIC/POREFLOW/POREPRESSURE/CONTACT-SLIP/PHIFLUX/NODAL-PHIFLUX} In addition, for TMC analysis only, the following choices are available: CONVECTION RADIATION NODAL-HEATFLOW HEATFLUX INTERNALHEAT LATENT A table of load types and the corresponding allowed application site types is given below.
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APPLY-LOAD
lnamei Label number of the load (defined by LOAD FORCE, etc.). stypei The type of site where the load is to be applied. {POINT/LINE/SURFACE/VOLUME/ EDGE/FACE/BODY/MODEL/NODE-SET/ELEMENT-EDGE-SET/ELEMENT-FACESET/CONTACT-SURFACE} snamei The label number of the application site, e.g., point label number, line label number, etc. idvari [0] The label number of the spatial function (defined by LINE-FUNCTION, SURFACE- FUNCTION, VOLUME-FUNCTION as appropriate). Enter 0 for the load to be considered constant in space (but not necessarily in time). If load ltypei=PRESSURE and stypei=FACE, idvari is the surface spatial function for the reference surface (pfocusi). Note: The spatial variation along the reference line is used to determine the spatial variation of the load on the face. For a point on the face, the closest point on the line is determined and the spatial value at that point is used. ncuri The label number of a time function, as defined by command TIMEFUNCTION.
[1]
[0.0] artmi The “arrival time” associated with time dependent loads. The load is considered zero for t ≤ artmi, and is governed by the time function “ncuri” for t > artmi. The time function is effectively shifted along in the time direction. See the Theory and Modeling Guide. idirni Specifies the load direction for pressure load or distributed line load. {0/1/2/3/4/11/12/13} 0 1 2 3 4 11 12 13
[0]
total (normal) pressure load is applied. only the X-component of the load is applied. only the Y-component of the load is applied. only the Z-component of the load is applied. tangential traction. load acts in the global X-direction. load acts in the global Y-direction. load acts in the global Z-direction.
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APPLY-LOAD
Sec. 7.8 Loading
Table: Allowed load type / application site types Point
Line
Surface
Volume
Edge
Face
Body
Others
!
!
!
×
!
!
×
1
!
×
×
×
×
×
×
2
×
!
!
×
!
!
×
Line
×
!
×
×
!
×
×
Centrifugal
×
×
×
×
×
×
×
Model
Mass proportional
×
×
×
×
×
×
×
Model
Displacement1
!
!
!
!
!
!
!
Temperature1
!
!
!
!
!
!
!
Temperature gradient1
!
!
!
×
!
!
×
Pipe-Internal pressure1
!
!
×
×
!
×
×
Electromagnetic
×
!
×
×
!
×
×
Pore flow2
×
!
!
×
!
!
×
Pore pressure1
!
!
!
!
!
!
!
Phiflux2
×
!
!
×
!
!
×
Nodal phiflux1
!
×
×
×
×
×
×
Convection1,3
!
!
!
×
!
!
×
Radiation1,3
!
!
!
×
!
!
×
Nodal-heatflow1,3!
×
×
×
×
×
×
Heatflux2,3
×
!
!
×
!
!
×
Internalheat1,3
×
!
!
!
!
!
!
Group
Latent3
×
×
×
×
×
×
×
Group
Force1 Moment Pressure
Contact slip
Contact surface
Notes: 1. Can also be applied to Node Sets. 2. Can also be applied to Element-Edge Sets and Element-Face Sets. 3. Can only be applied in TMC analysis.
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APPLY-LOAD
iddli [-1] If ltypei={PRESSURE/LINE/CENTRIFUGAL/ELECTROMAGNETIC/PORE FLOW}, this specifies whether the load is deformation-dependent, i.e. the direction of the load changes in response to the (large displacement) deformation of the structure. {0/1/-1} 0 1 -1
the load is independent of structural deformation. the load is deformation-dependent. the load is deformation-dependent for large displacement or large strain formulation, otherwise the load is deformation independent.
iddli [0] If ltypei=DISPLACEMENT, this specifies whether the prescribed displacement is measured relative to the original configuration or to the deformed configuration {0/1}. The “deformed” configuration is the configuration at the arrival time of the prescribed displacement (if the arrival time is not equal to zero), or the configuration at the start time of the current analysis (which can be a restart analysis). 0 1
Original configuration Deformed configuration
pfocusi [0] Specifies a point which determines the plane of load application for loads of type LINE. It may also be used to specify a “follower” force or moment, in which case the direction of the load application is determined by the relative positions of the point of application and the focus point “pfocusi”. If point “pfocusi” is input, then a unique node must be defined at the same location as the focus point. If load ltypei=PRESSURE and stypei=FACE, pfocusi means the reference surface for spatial function of surface. bodyi Body label number, used when stypei = FACE or EDGE.
[BODY]
[0] psensei Qualifies the direction of the distributed line load controlled by the point “pfocusi”. If psensei=0 then the plane of action of the load is determined by the focal point and the end nodes of each element edge along the application line; in this case a single auxiliary node will be generated at the focal point. If psensei=1 the load will act perpendicular to the plane defined by the focal point and the element edge end nodes; in this case an auxiliary node will be generated for each element edge along the line (positioned “above” the plane defined by the vertex nodes and the focal point). Furthermore, for psensei=0 (in-plane) a positive load acts toward the element from the focal point. The convention for load direction when psensei=1 can be understood as follows: imagine walking along the line in its positive parametric direction (i.e. from the start point to the end point) such that the focal point is always above you - a positive load is then assumed to act from your left. 7-398
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APPLY-LOAD
Sec. 7.8 Loading
unloadi Specifies the type of unloadng for prescribed displacement. {TIME/FORCE/NO}
[NO]
[0.0] timeui If unloadi=TIME, this specifies the time at which unloading of prescribed displacement starts. forceui [0.0] If unloadi=TIME and forceui = 0.0, then the prescribed force for time > timeui is equal to the reaction force multiplied by the value of time function ncurui. If unloadi=TIME and forceui ≠ 0.0, then the prescribed force for time > timeui is equal to forceui multiplied by the value of time function ncurui. If unloadi=FORCE, then the prescribed displacement becomes a prescribed force for the solution step after the step in which the reaction force exceeds forceui. The value of the prescribed force is equal to forceui multiplied by the value of time function ncurui. forceui cannot equal 0.0 if unloadi=FORCE. ncurui Label number of a time function for the unloading of prescribed displacement.
[1]
cgroupi Contact group label number.
[0]
[MID] shellnodei Specifies whether the loads is applied to the top, bottom or both top and bottom of shell surface.{TOP/BOTTOM/MID}
.
TOP
The load is applied to top surface
BOTTOM
The load is applied to bottom surface
MID
The load is applied to shell midsurface. This option is only used for temperature loading. If no temperature gradient is applied at the shell node, the top and bottom shell surface will have the same temperature.
Note that this parameter is used only for temperature, heat flux, convection and radiation loading in TMC analysis Auxiliary commands LIST APPLY-LOAD DELETE APPLY-LOAD
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LOAD-PENETRATION
Sec. 7.8 Loading
LOAD-PENETRATION groupi Defines a region in terms of element groups where an initial pressure load can penetrate; i.e. if an element in the region, to which a pressure load is applied ruptures or “dies”, the pressure load is distributed to its neighboring element faces. This command is only active if MASTER LOAD-PENETRATION = YES. Note:
A pressure load must already be applied to the penetration region, see APPLY-LOAD or LOADS-ELEMENT.
groupi Element group label number. Auxiliary commands LIST LOAD-PENETRATION DELETE LOAD-PENETRATION
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INITIAL-CONDITION
Chap. 7 Model definition
INITIAL-CONDITION
NAME INITIALSTRESS
variablei valuei Defines an initial condition that can be referenced by SET-INITCONDITION to assign the initial condition to geometry entities. All variables are assumed initially zero unless set by this command in conjunction with SET-INITCONDITION. NAME The identifying name of the initial condition (1 to 30 alphanumeric characters). INITIALSTRESS Controls whether the initial strain input at nodes are to be interpreted initial stresses.
[NO]
NO
No change to nodal initial strain input.
YES
Nodal initial strains are to be interpreted as initial stresses.
DEFORMATION
Nodal initial strains are to be interpreted as initial stresses which result in deformations.
variablei Degree(s) of freedom or their time derivatives to be set initially. Possible values (strings) are: X-TRANSLATION Y-TRANSLATION Z-TRANSLATION X-ROTATION Y-ROTATION Z-ROTATION X-VELOCITY Y-VELOCITY Z-VELOCITY
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
INITIAL-CONDITION
Sec. 7.9 Initial conditions
valuei The value to be assigned to “variablei”. Note:
The initial conditions will be applied to the nodes of the model, albeit indirectly via the model geometry. The variables of the initial condition thus refer to the degree-offreedom system at each node, which may be the global coordinate system or a skewsystem. See SKEWSYSTEM, DOF-SYSTEM.
Auxiliary commands LIST INITIAL-CONDITION DELETE INITIAL-CONDITION
node-seti conditioni SET-INITCONDITION POINTS assigns initial conditions to a set of geometry points. SET-INITCONDITION LINES assigns initial conditions to a set of geometry lines. SET-INITCONDITION SURFACES assigns initial conditions to a set of geometry surfaces. SET-INITCONDITION VOLUMES assigns initial conditions to a set of geometry volumes.
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SET-INITCONDITION
Sec. 7.9 Initial conditions
SET-INITCONDITION EDGES assigns initial conditions to a set of solid geometry edges. SET-INITCONDITION FACES assigns initial conditions to a set of solid geometry faces. SET-INITCONDITION BODIES assigns initial conditions to a set of solid geometry bodies. SET-INITCONDITION NODE-SET assigns initial conditions to sets of nodes. CONDITION [lowest (alphabetically) INITIAL-CONDITION] Default initial condition ( see command INITIAL-CONDITION ) for subsequent data lines. BODY Label number of a solid geometry body.
[currently active body]
pointi Label number of a geometry point. linei Label number of a geometry line. surfacei Label number of a geometry surface. volumei Label number of a geometry volume. edgei Label number of a solid geometry edge (for BODY). facei Label number of a solid geometry face (for BODY). bodyi Label number of a solid geometry body. conditioni Initial condition to be applied at point “pointi”.
[CONDITION]
idvari [0] Label number of a spatial data variation, defined by LINE-FUNCTION, SURFACE-FUNCTION or VOLUME-FUNCTION, as appropriate. A 0 value indicates the initial condition is assumed constant over the geometry entity.
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SET-INITCONDITION
Chap. 7 Model definition
Auxiliary commands LIST SET-INITCONDITION POINTS DELETE SET-INITCONDITION POINTS
FIRST LAST FIRST LAST
LIST SET-INITCONDITION LINES DELETE SET-INITCONDITION LINES
FIRST LAST FIRST LAST
LIST SET-INITCONDITION SURFACES DELETE SET-INITCONDITION SURFACES
FIRST LAST FIRST LAST
LIST SET-INITCONDITION VOLUMES DELETE SET-INITCONDITION VOLUMES
FIRST LAST FIRST LAST
LIST SET-INITCONDITION EDGES DELETE SET-INITCONDITION EDGES
FIRST LAST FIRST LAST
LIST SET-INITCONDITION FACES DELETE SET-INITCONDITION FACES
FIRST LAST FIRST LAST
LIST SET-INITCONDITION BODIES DELETE SET-INITCONDITION BODIES
FIRST LAST FIRST LAST
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STRAIN-FIELD
STRAIN-FIELD
Sec. 7.9 Initial conditions
NAME A B C D E F
Defines an initial geological strain field which varies in the global z-direction for 2-D and 3-D solid elements. This strain-field may be referenced by element groups using commands EGROUP TWODSOLID and EGROUP THREEDSOLID (Section 8.1) in order to give initial element strains. NAME [(current highest strain-field label number) + 1] Label number of the strain-field to be defined. A B C D E F Parameters used to evaluate an initial strain field as follows:
[0.0] [0.0] [0.0] [0.0] [0.0] [0.0]
TWODSOLID elements: e 22 = A + B ⋅ z e11 = C ⋅ e 22 + D e 33 = E ⋅ e 22 + F (axisymmetric analysis only)
THREEDSOLID elements: e 33 = A + B ⋅ z e11 = C ⋅ e 33 + D e 22 = E ⋅ e 33 + F
where eij are the normal components of initial strain, and z is the global z-coordinate. Auxiliary commands LIST STRAIN-FIELD DELETE STRAIN-FIELD
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IMPERFECTION POINTS
IMPERFECTION POINTS bucklingmodei pointi directioni displacementi Specifies imperfections based on the buckling mode shapes, which have been calculated and stored in a previous run. The total imperfection applied is a superposition of the imperfections from each specified buckling mode. List of buckling modes has to be continous - all buckling modes between the first and last mode have to be specified. For modes which are not significant, displacementi should be set to 0. bucklingmodei The number of the buckling mode-shape. pointi Point label number where the magnitude of imperfection is specified. directioni Translational degree of freedom for displacementi. 1
X-translation (a-translation if skew system).
2
Y-translation (b-translation if skew system).
3
Z-translation (c-translation if skew system).
displacementi Magnitude of imperfection in the same length unit as the global coordinates. ADINA scales the buckling mode shape indicated by bucklingmodei to have this value for the node at the point and in the direction specified. Auxiliary commands LIST IMPERFECTION POINTS DELETE IMPERFECTION POINTS
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IMPERFECTION SHAPE
IMPERFECTION SHAPE
Sec. 7.9 Initial conditions
OPTION
Indicates when initial nodal displacements should be read for initial shape calculations (but not for initial load vector or stress calculations) (OPTION = READ), or when ADINA should write out all nodal displacements (OPTION = WRITE). OPTION The flag of initial imperfection input: READ
Read initial nodal displacements.
WRITE
Save nodal displacements.
[READ]
Auxiliary commands LIST IMPERFECTION SHAPE DELETE IMPERFECTION SHAPE
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INITIAL-MAPPING
Chap. 7 Model definition
INITIAL-MAPPING
FILENAME EXTERNAL-NODE DISTANCE TIME ORDER
variablei Loads an initial “mapping-file” and interpolates variable values at existing model nodes using variable values at another set of nodes for a mesh which is stored in the initial mapping file. FILENAME The mapping file to be loaded. {Any filename accepted by the computer system (up to 80 characters long)}. EXTERNAL-NODE [ALL] The option for the treatment of external nodes (i.e., outside the boundary of the mesh contained in the mapping-file). ALL
Interpolation for all external nodes.
NONE
No interpolation (extrapolation).
DISTANCE
Interpolation for nodes which are within a maximum specified distance from the mapping-file mesh.
DISTANCE [0.0] Maximum allowed distance from the mapping-file mesh (used when EXTERNAL-NODE = DISTANCE). variablei Degree(s) of freedom or their time derivatives to be interpolated for as nodal initial conditions. These include the following: X-TRANSLATION Y-TRANSLATION X-VELOCITY Y-VELOCITY X-ACCELERATION Y-ACCELERATION
Z-TRANSLATION Z-VELOCITY Z-ACCELERATION
X-ROTATION Y-ROTATION Z-ROTATION XROT-VELOCITY YROT-VELOCITY ZROT-VELOCITY XROT-ACCELERATION YROT-ACCELERATION ZROT-ACCELERATION TEMPERATURE
TGRADIENT
STRAIN-11 STRAIN-12
STRAIN-22 STRAIN-13
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INITIAL-MAPPING
Sec. 7.9 Initial conditions
OVALIZATION-1 OVALIZATION-4
OVALIZATION-2 OVALIZATION-5
OVALIZATION-3 OVALIZATION-6
WARPING-1 WARPING-4
WARPING-2 WARPING-5
WARPING-3 WARPING-6
FLUID-POTENTIAL
FPOT-VELOCITY
FPOT-ACCELERATION
PIPE-INTERNAL-PRESSURE TIME Selects the solution time to be mapped.
[0.0]
Note that this parameter is used when the mapping file is from ADINA-F. ORDER Order of interpolation. {2/1}
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THERMAL-MAPPING
THERMAL-MAPPING
Sec. 7.9 Initial conditions
FILENAME EXTERNAL-NODE DISTANCE TIME
Creates a nodal temperature and temperature gradient file for the current finite element model by interpolation from a “mapping-file” which contains a finite element mesh with nodal temperatures / gradients for a range of solution times. This command is useful for prescribing temperatures for the ADINA model from a temperature solution obtained from an independent mesh, e.g. from an ADINA-T model. FILENAME The mapping-file to be read. EXTERNAL-NODE [ALL] The option for the treatment of external nodes, i.e. those which lie outside the mesh contained within the mapping-file: ALL
Interpolation (extrapolation) for all external nodes.
NONE
No interpolation (zero value assigned).
DISTANCE
Interpolation for nodes which are within a maximum specified distance from the mapping-file mesh.
DISTANCE Maximum distance for external node interpolation.
[0.0]
TIME Selects the solution time to be mapped.
[0.0]
Note that this parameter is used when the mapping file is from ADINA-F.
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SKEWSYSTEMS CYLINDRICAL
Chap. 7 Model definition
SKEWSYSTEMS CYLINDRICAL ni xorigini yorigini zorigini xaxisi yaxisi zaxisi normali Command SKEWSYSTEMS CYLINDRICAL defines a “skew” Cartesian coordinate system in terms of a cylinder origin and axis direction. Skew systems can be referenced (via command DOF-SYSTEM ) by geometry and nodes to indicate the local orientation of the nodal degrees of freedom. Note that skew system definitions are distinct from coordinate systems defined via command SYSTEM, which are used to indicate point and node locations. ni Label number for the desired skew system. xorigini yorigini zorigini The global coordinates of the origin of the axis of the cylinder.
[0.0] [0.0] [0.0]
xaxisi yaxisi zaxisi Global system components of the direction axis of the cylinder.
[0.0] [1.0] [0.0]
normali [B] normali indicates which of the skew system axes is to be aligned with the er (radial) direction. Valid choices are ‘A’, ‘B’. If normal = A, skew system axis C is aligned with the ez (axis) direction of the cylinder. If normal = B, skew system axis A is aligned with the ez direction of the cylinder. Auxiliary commands LIST SKEWSYSTEM DELETE SKEWSYSTEM
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SKEWSYSTEMS EULERANGLES
Sec. 7.10 Systems
SKEWSYSTEMS EULERANGLES ni phii thetai xsii Defines “skew” Cartesian coordinate systems in terms of Euler angles. Skew systems can be referenced, via DOF-SYSTEM, to indicate the local orientation of the nodal degrees of freedom. Note that skew system definitions are distinct from coordinate systems defined via command SYSTEM, which are used to indicate point and node locations. ni Label number for the desired skew system. phii [0.0] thetai [0.0] xsii [0.0] Rotations, in degrees, about the global Cartesian system axes, required to orient the local directions of the skew system, see SYSTEM for Euler-angle definition. Auxiliary commands LIST SKEWSYSTEM DELETE SKEWSYSTEM
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SKEWSYSTEMS NORMAL
Chap. 7 Model definition
SKEWSYSTEMS NORMAL
NAME
Defines a skew Cartesian coordinate system to be such that one of its directions is normal to a given line or surface. Note that no other parameters are required to define this skewsystem. When assigned via DOF-SYSTEM, each node referenced has a skew system defined such that a selected local axis is normal to the underlying geometry. Note that skew system definitions are distinct from coordinate systems defined via command SYSTEM, which are used to indicate point and node locations. NAME Label number of the skew coordinate system, which may be referenced by commands DOFSYSTEM. Auxiliary commands LIST SKEWSYSTEM DELETE SKEWSYSTEM
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SKEWSYSTEMS POINTS
Sec. 7.10 Systems
SKEWSYSTEMS POINTS ni p1i p2i p3i Defines “skew” Cartesian coordinate systems in terms of geometry points. Skew systems can be referenced, via DOF-SYSTEM, to indicate the local orientation of the nodal degrees of freedom. Note that skew system definitions are distinct from coordinate systems defined via command SYSTEM, which are used to indicate point and node locations.
Zs
Ys
P1 Xs
P3
Z
Zs
P2
Ys
Y X
node
Xs
ni Label number for the desired skew system. p1i p2i p3i Geometry point label numbers. The vector from point p1i to point p2i defines the direction of the local X-axis of the skew system. The vector from p1i to p3i is taken to lie in the local XYplane of the skew system. Note that points p1i, p2i, p3i must not be collinear. Auxiliary commands LIST SKEWSYSTEM DELETE SKEWSYSTEM
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SKEWSYSTEMS SPHERICAL
Chap. 7 Model definition
SKEWSYSTEMS SPHERICAL ni xorigini yorigini zorigini Command SKEWSYSTEMS SPHERICAL defines a “skew” Cartesian coordinate system in terms of a sphere origin. Skew systems can be referenced (via command DOF-SYSTEM ) by geometry and nodes to indicate the local orientation of the nodal degrees of freedom. Note that skew system definitions are distinct from coordinate systems defined via command SYSTEM, which are used to indicate point and node locations. The skew system axis A is aligned with the er direction of the sphere, axis B is aligned with the eΘ direction and axis C is chosen to create a right-handed orthogonal coordinate system. ni Label number for the desired skew system. xorigini yorigini zorigini The global coordinates of the origin of the sphere.
[0.0] [0.0] [0.0]
Auxiliary commands LIST SKEWSYSTEM DELETE SKEWSYSTEM
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SKEWSYSTEMS VECTORS
Sec. 7.10 Systems
SKEWSYSTEMS VECTORS ni axi ayi azi bxi byi bzi Defines “skew” Cartesian coordinate systems in terms of direction vectors. Skew systems can be referenced, via DOF-SYSTEM, to indicate the local orientation of the nodal degrees of freedom. Note that skew system definitions are distinct from coordinate systems defined via command SYSTEM, which are used to indicate point and node locations.
Zs Ys (bx,by,bz)
Z node Xs Y
(ax,ay,az)
X ni Label number for the desired skew system. [1.0] axi ayi [0.0] azi [0.0] Vector aligned with the local X-axis of the skew system, defined with respect to the global Cartesian system. Note that for two-dimensional problems vector (axi,ayi,azi) must be parallel to the global Cartesian X-axis. [0.0] bxi byi [1.0] bzi [0.0] Vector lying in the local XY-plane of the skew system, defined with respect to the global Cartesian system. Note that vector (bxi,byi,bzi) must not be parallel to vector (axi,ayi,azi). Auxiliary commands LIST SKEWSYSTEM DELETE SKEWSYSTEM
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namei skewsystemi normali tangenti pfocusi nsensei tsensei DOF-SYSTEM VOLUMES namei skewsystemi DOF-SYSTEM BODIES namei skewsystemi DOF-SYSTEM NODESETS namei skewsystemi DOF-SYSTEM POINTS assigns skew coordinate systems to the degrees of freedom associated with a set of geometry points. DOF-SYSTEM LINES assigns skew coordinate systems to the degrees of freedom associated with a set of geometry lines. Furthermore, for skew coordinate systems defined to be of type NORMAL, the local skew system axes to be aligned with the normal and tangent directions to the line are specified. The normal vector may also be directed such that it points toward or
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Chap. 7 Model definition
DOF-SYSTEM
away from a given “focal” point, and the sense of the tangent vector may be similarly assigned. DOF-SYSTEM EDGES assigns skew coordinate systems to the degrees of freedom associated with a set of solid geometry edges. Furthermore, for skew coordinate systems defined to be of type NORMAL, the local skew system axes to be aligned with the normal and tangent directions to the edge are specified. The normal vector may also be directed such that it points toward or away from a given “focal” point, and the sense of the tangent vector may be similarly assigned. DOF-SYSTEM SURFACES assigns skew coordinate systems to the degrees of freedom associated with a set of geometry surfaces. Furthermore, for skew coordinate systems defined to be of type NORMAL, the local skew system axis to be aligned with the normal direction to the surface is specified along with the axis to be aligned with the surface tangent parallel to the local surface parametric u-coordinate direction. The normal vector may also be directed such that it points toward or away from a given “focal” point, and the sense of the tangent vector may be similarly assigned. DOF-SYSTEM FACES assigns skew coordinate systems to the degrees of freedom associated with a set of solid geometry faces. Furthermore, for skew coordinate systems defined to be of type NORMAL, the local skew system axis to be aligned with the normal direction to the face is specified along with the axis to be aligned with the face tangent parallel to the local face parametric u-coordinate direction. The normal vector may also be directed such that it points toward or away from a given “focal” point, and the sense of the tangent vector may be similarly assigned. DOF-SYSTEM VOLUMES assigns skew coordinate systems to the degrees of freedom associated with a set of geometry volumes. DOF-SYSTEM BODIES assigns skew coordinate systems to the degrees of freedom associated with a set of geometry bodies. DOF-SYSTEM NODESETS assigns skew coordinate systems to the degrees of freedom associated with a node set. BODY Label number of a solid geometry body.
[currently active body]
namei / linei / edgei Label number of a geometry entity or nodeset. All nodes associated with the geometry or contained in the nodeset are assigned the specified skew system.
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DOF-SYSTEM
Sec. 7.10 Systems
skewsystemi Label number of a skew coordinate system, as defined by SKEWSYSTEM. Setting skewsystemi = 0 assigns the global Cartesian system to the nodal degrees of freedom. The following parameters are applicable only to skew systems of type NORMAL applied to geometry lines, edges, surfaces and faces. normali Indicates which of the skew system axes is to be aligned with the normal direction of the geometry. The default is C when applied to lines or edges, and A when applied to surfaces or faces. {A/B/C} tangenti [B] Indicates which of the skew system axes is to be aligned with the tangential direction of the geometry. {A/B/C} pfocusi Label number of a geometry point which is the “focal” point for directing the normal vector, when skewsystemi is of type NORMAL. The principal normal vector at a point on the line is determined to point away from the local center of curvature. The opposite direction is also normal to the line, and thus a “focal point” may be used so that the actual normal direction used points toward or away from this point, the selection of which is made by nsensei. If input as 0, then no focus is specified, and the principal normal direction is used. Note: For straight lines, straight line segments, or points of inflection on a curve, for which the curvature is zero, the normal vector is taken to be either: (a) when pfocusi = 0, or when pfocusi >0 and the tangent points directly toward or away from point pfocusi; the cross product of the tangential direction with the global Xdirection (or Y-direction if the tangent is parallel to the X-direction) (b) otherwise, a binormal vector is calculated as the cross product of the tangent vector and the vector directed from the point on the curve to the focal point (the “focal vector”). The normal vector is then taken as the cross product of the binormal and the tangent vectors. In this way the normal vector lies in the plane formed by the tangent and focal vectors, and is directed toward the focal point (or away from the focal point, as controlled by nsensei).
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DOF-SYSTEM
Chap. 7 Model definition
nsensei [+1] Indicates the direction of the normal vector with reference to the focal point. It is used in conjunction with the pfocusi to orient the normal direction. +1
Normal direction points toward point pfocusi.
-1
Normal direction points away from point pfocusi.
tsensei [+1] Indicates the direction of the tangent vector. It is used in conjunction with tangenti to orient the skew system tangent direction. +1
Follow tangent direction of the geometry.
-1
Opposite to tangent direction of the geometry.
Auxiliary commands LIST DOF-SYSTEM POINTS DELETE DOF-SYSTEM POINTS
FIRST LAST FIRST LAST
LIST DOF-SYSTEM LINES DELETE DOF-SYSTEM LINES
FIRST LAST FIRST LAST
LIST DOF-SYSTEM EDGES DELETE DOF-SYSTEM EDGES
FIRST LAST FIRST LAST
LIST DOF-SYSTEM SURFACES DELETE DOF-SYSTEM SURFACES
FIRST LAST FIRST LAST
LIST DOF-SYSTEM FACES DELETE DOF-SYSTEM FACES
FIRST LAST FIRST LAST
LIST DOF-SYSTEM VOLUMES DELETE DOF-SYSTEM VOLUMES
FIRST LAST FIRST LAST
LIST DOF-SYSTEM NODESETS DELETE DOF-SYSTEM NODESETS
FIRST LAST FIRST LAST
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facei nsdofi SHELLNODESDOF POINTS specifies the number of degrees of freedom for shell midsurface nodes associated with a set of geometry points. SHELLNODESDOF LINES specifies the number of degrees of freedom for shell midsurface nodes associated with a set of geometry lines. SHELLNODESDOF SURFACES specifies the number of degrees of freedom for shell midsurface nodes associated with a set of geometry surfaces. SHELLNODESDOF NODESETS specifies the number of degrees of freedom for shell midsurface nodes associated with a node set. SHELLNODESDOF EDGES specifies the number of degrees of freedom for shell midsurface nodes associated with a set of solid geometry edges.
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SHELLNODESDOF
Sec. 7.10 Systems
SHELLNODESDOF FACES specifies the number of degrees of freedom for shell midsurface nodes associated with a set of solid geometry faces.
BODY Solid geometry body label number.
[currently active body]
pointi Geometry point label number. linei Line label number. surfacei Surface label number. nodeseti Nodeset label number. edgei Edge label number (for BODY). facei Face label number (for BODY). nsdofi [AUTOMATIC] Number of degrees of freedom for shell midsurface nodes at the geometry entity. FIVE
Three translation, and two rotation degrees of freedom (in local midsurface system). See the Theory and Modeling Guide.
SIX
Three translation and three rotation (global or skew) degrees of freedom.
AUTOMATIC
The program automatically decides on the number of degrees of freedom to be assigned to shell nodes based on certain modeling considerations. See the Theory and Modeling Guide.
Auxiliary commands LIST SHELLNODESDOF POINTS/LINES/SURFACES/NODESETS/EDGES/FACES
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
AXES CONSTANT
AXES CONSTANT
Sec. 7.10 Systems
NAME AX AY AZ BX BY BZ
Defines an “axes-system” in terms of constant direction vectors. Axes-systems can be referenced by SET-AXES-MATERIAL, SET-AXES-STRAIN to indicate the local orien-tation of the orthotropic material properties and/or initial strain, respectively. NAME Label number for the axes-system to be defined. AX [1.0] AY [0.0] AZ [0.0] Vector aligned with the local x-axis of the axes-system, defined with respect to the global Cartesian coordinate system. BX [0.0] BY [1.0] BZ [0.0] Vector lying in the local xy-plane of the axes-system, defined with respect to the global Cartesian coordinate system. Note that vector (BX, BY, BZ) must not be parallel to vector (AX, AY, AZ). Auxiliary commands LIST AXES DELETEAXES
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AXES LINE1
Chap. 7 Model definition
AXES LINE1
NAME LINE
Defines an “axes-system” via a geometry line. Axes-systems can be referenced by SET-AXES-MATERIAL, SET-AXES-STRAIN to indicate the local orientation of the orthotropic material properties and/or initial strain, respectively. LINE P z
t y
element
x (|| t)
C centroid
NAME Label number for the axes-system to be defined. LINE Label number of the geometry line defining the axes-system. Note:
The axes-system at an element centroid C is determined by calculating the tangent vector at the nearest point P on the geometry line. This gives the local x-direction of the axes-system. The local xy-plane of the axes-system is calculated to include both the tangent vector to the line and the vector from the element centroid to the nearest point on the line. See Figure.
Auxiliary commands LIST AXES DELETEAXES
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AXES LINE2
Sec. 7.10 Systems
AXES LINE2
NAME LINE1 LINE2
Defines an “axes-system” via two geometry lines. Axes-systems can be referenced by SET-AXES-MATERIAL, SET-AXES-STRAIN to indicate the local orientation of the orthotropic material properties and/or initial strain, respectively. LINE 1
P1
z ( || t1 x t2)
t1 y (t2)
element C
x ( || t1)
centroid t2 LINE 2 P2
NAME Label number for the axes-system to be defined. LINE1 Label number of the first geometry line defining the axes-system. LINE2 Label number of the second geometry line defining the axes-system. Note:
The axes-system at an element centroid C is determined by calculating the tangent vector at the nearest point P1 on the first geometry line. This gives the local xdirection of the axes-system. The local xy-plane of the axes-system is determined to include this tangent vector and the tangent vector at the nearest point P2 on the second geometry line. See Figure.
Auxiliary commands LIST AXES DELETEAXES
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AXES NODES
AXES NODES
NAME NODE1 NODE2 NODE3
Defines an “axes-system” using three nodes. Axes-systems can be referenced by commands SET-AXES-MATERIAL, SET-AXES-STRAIN, by elements to indicate the local orientation of the orthotropic material properties and/or initial strain, respectively. NAME Label number for the desired axes-system. NODE1 Label number of the first axes-system defining node.
z (a x b)
y (a x b) x a
(a x b ) NODE3 b
element C
x (a ) NODE1
a
NODE2
centroid
NODE2 Label number of the second axes-system defining node. NODE3 Label number of the third axes-system defining node. Note: The local x-direction of the axes-system is determined by the vector from the first node “NODE1” to the second node NODE2. The local z-direction of the axes-system is determined as the normal to the plane defined by the three nodes NODE1, NODE2, and NODE3. The local y-direction of the axes-system is then given by the right-hand rule. See figure.
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Sec. 7.10 Systems
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AXES POINT2
Chap. 7 Model definition
AXES POINT2
NAME POINT1 POINT2
Defines an “axes-system” via two geometry points. Axes-systems can be referenced by SET-AXES-MATERIAL, SET-AXES-STRAIN, to indicate the local orientation of the orthotropic material properties and/or initial strain, respectively. POINT2 y
z ( a x b)
b
POINT1
element
x
C
a
centroid
NAME Label number for the axes-system to be defined. POINT1 Label number of the first geometry point defining the axes-system. POINT2 Label number of the second geometry point defining the axes-system, which must not be coincident with point “POINT1”. Note
The local x-direction of the axes-system at an element centroid C is determined by the vector from the centroid to POINT1. The local z-direction of the axes-system is determined as the normal to the plane defined by the centroid, POINT1 and POINT2. The local y-direction of the axes-system is then given by the right-hand rule. See Figure.
Auxiliary commands LIST AXES DELETEAXES
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AXES POINT3
Sec. 7.10 Systems
AXES POINT3
NAME POINT1 POINT2 POINT3
Defines an “axes-system” via three geometry points. Axes-systems can be referenced by SET-AXES-MATERIAL, SET-AXES-STRAIN, to indicate the local orientation of the orthotropic material properties and/or initial strain, respectively.
z (a x b)
y ( a x b) x a ( a x b)
element
C
POINT3 b
x ( a)
a
POINT2
POINT1 centroid
NAME Label number for the axes-system to be defined. POINT1 Label number of the first geometry point defining the axes-system. POINT2 Label number of the second geometry point defining the axes-system. POINT3 Label number of the third geometry point defining the axes-system. Note: The local x-direction of the axes-system is determined by the vector from POINT1 to POINT2. The local z-direction of the axes-system is determined as the normal to the plane defined by the three points POINT1, POINT2, and POINT3. The local y-direction of the axes-system is then given by the right-hand rule. See Figure. Auxiliary commands LIST AXES DELETEAXES
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AXES POINT-LINE
Chap. 7 Model definition
AXES POINT-LINE
NAME LINE POINT
Defines an “axes-system” via a geometry line and a geometry point. Axes-systems can be referenced by SET-AXES-MATERIAL, SET-AXES-STRAIN, to indicate the local orientation of the orthotropic material properties and/or initial strain, respectively.
axb
POINT
b
LINE
u P1
P
z (|| a x b)
t
a
P2
y centroid
element C
x(||t)
NAME Label number for the axes-system to be defined. LINE Label number of the geometry line defining the axes-system. Note that the line must not be closed, i.e., it must have non-coincident end-points. POINT Label number of the geometry point defining the axes-system. The point must not be collinear with the end-points of line LINE. Note:
The axes-system at an element centroid C is determined by calculating the tangent vector at the nearest point P on the geometry line. This gives the local x-direction of the axes-system. The local xy-plane of the axes-system is defined by the end-points of the geometry line “LINE”, and the given geometry point “POINT”. Thus, in order to determine this plane, the line must have distinct end-points P1 and P2, i.e., it cannot be closed or degenerate, and the geometry point must not be collinear with those end-points. See Figure.
Auxiliary commands LIST AXES DELETEAXES
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AXES SURFACE
Sec. 7.10 Systems
AXES SURFACE
NAME SURFACE
Defines an “axes-system” via a geometry surface. Axes-systems can be referenced by SET-AXES-MATERIAL, SET-AXES-STRAIN, to indicate the local orientation of the orthotropic material properties and/or initial strain, respectively.
z (||n)
y (||n x u)
element
x (||u) C
n
centroid
v
P
u
NAME Label number for the axes-system to be defined. SURFACE Label number of the geometry surface defining the axes-system. Note:
The axes-system at an element centroid C is determined by calculating the surface tangent and normal vectors at the nearest point P on the geometry surface. The local x-direction of the axes-system is given by the tangent vector in the local parametric u-direction of the surface. The local z-direction of the axes-system is given by the surface normal direction and the local y-direction of the axes-system is then given by the right-hand rule. See Figure.
Auxiliary commands LIST AXES DELETEAXES
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AXES EDGE
Chap. 7 Model definition
AXES EDGE
NAME EDGE BODY
Defines an “axes-system” via a geometry edge. Axes-systems can be referenced by SET-AXES-MATERIAL, SET-AXES-STRAIN, to indicate the local orientation of the orthotropic material properties and/or initial strain, respectively. n u t
P z
EDGE
y
element C
x (||t)
centroid NAME Label number for the axes-system to be defined. EDGE Label number of the geometry edge defining the axes-system. BODY [currently active body] Label number of the geometry body containing the edge. Note:
The axes-system at an element centroid C is determined by calculating the edge tangent and normal vectors at the nearest point P on the geometry edge. The local xdirection of the axes-system is given by the edge tangent vector (in the local parametric u-direction of the edge). The local z-direction of the axes-system is given by the edge normal direction and the local y-direction of the axes-system is then given by the right-hand rule. See Figure.
Auxiliary commands LIST AXES DELETEAXES
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AXES FACE
AXES FACE
Sec. 7.10 Systems
NAME FACE BODY
Defines an “axes-system” via a geometry face. Axes-systems can be referenced by SET-AXES-MATERIAL, SET-AXES-STRAIN, to indicate the local orientation of the orthotropic material properties and/or initial strain, respectively. NAME Label number for the axes-system to be defined. FACE Label number of the geometry face defining the axes-system. BODY Label number of the geometry body containing the face. Note:
[currently active body]
The axes-system at an element centroid is determined by calculating the face tangent and normal vectors at the nearest point on the geometry face. The local xdirection of the axes-system is given by the tangent vector in the local parametric u-direction of the face. The local z-direction of the axes-system is given by the face normal direction and the local y-direction of the axes-system is then given by the right-hand rule. See Figure for AXES SURFACE.
Auxiliary commands LIST AXES DELETEAXES
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AXES-CYLINDRICAL
Chap. 7 Model definition
AXES CYLINDRICAL
NAME XORIGIN YORIGIN ZORIGIN XAXIS YAXIS ZAXIS
Defines a cylindrical axes system in terms of an origin and an axis direction. This axes system can be referenced by SET-AXES-MATERIAL and SET-AXES-STRAIN to indicate the local orientation of the orthotropic material properties and/or initial strain, respectively. In this axes system, the local x direction is aligned with the er (radial) direction, the local y direction is aligned with the eθ direction, and the local z direction is aligned with the eh (cylindrical axis) direction. Z
eh ZL
YL XL
eθ
er
h
Y r
θ X
NAME Label number for the axes system to be defined. XORIGIN, YORIGIN, ZORIGIN The global coordinates of the origin of the cylindrical axis.
[0.0,0.0,0.0]
XAXIS, YAXIS, ZAXIS The global components of the direction vector of the cylindrical axis.
[0.0,0.0,1.0]
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AXES-SPHERICAL
AXES SPHERICAL
Sec. 7.10 Systems
NAME XORIGIN YORIGIN ZORIGIN XAXIS YAXIS ZAXIS
Defines a spherical axes system in terms of an origin. This axes system can be referenced by SET-AXES-MATERIAL and SET-AXES-STRAIN to indicate the local orientation of the orthotropic material properties and/or initial strain, respectively. In this axes system, the local x direction is aligned with the er (radial) direction of the sphere, the local y direction is aligned with the eφ direction, and the local z direction is aligned with the eθ direction. Z
er XL
eθ ZL
YL φ
eφ
θ Y X
NAME Label number for the axes system to be defined. XORIGIN, YORIGIN, ZORIGIN The global coordinates of the origin of the spherical axis.
[0.0,0.0,0.0]
XAXIS, YAXIS, ZAXIS The global components of the direction vector of the spherical axis.
facei axesi adiri bdiri SET-AXES-MATERIAL BODIES bodyi axesi adiri bdiri SET-AXES-MATERIALELEMENTSETS elementseti axesi adiri bdiri SET-AXES-MATERIAL SURFACES assigns axes-systems, as defined by AXES, to a set of geometry surfaces. SET-AXES-MATERIAL VOLUMES assigns axes-systems, as defined by AXES, to a set of geometry volumes. SET-AXES-MATERIAL FACES assigns axes-systems, as defined by AXES, to a set of solid geometry faces. SET-AXES-MATERIAL BODIES assigns axes-systems, as defined by AXES, to a set of solid geometry bodies. SET-AXES-MATERIAL ELEMENTSETS assigns axes-systems, defined by command AXES, to a set of element sets. BODY Label number of a solid geometry body.
[currently active body]
surfacei Label number of a geometry surface.
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SET-AXES-MATERIAL
Sec. 7.10 Systems
volumei Label number of a geometry volume. facei Label number of a solid geometry face (for BODY). bodyi Label number for a solid geometry body. Note:
Any elements generated for the referenced geometry will adopt orthotropic material directories as calculated by the assigned axes-system.
elementseti Label number of a element set. Any elements generated in this element set will calculate orthotropic material directions from the assigned the axes-system “axesi”. axesi Label number of an axes-system defined by AXES. adiri [1] The material a-direction is selected to be determined from one of the calculated local x-, y-, or z-directions of the axes-system. 1
a-direction coincides with local x-direction of axis-system.
2
a-direction coincides with local y-direction of axis-system.
3
a-direction coincides with local z-direction of axis-system.
-1
a-direction coincides with local negative x-direction of axis-system.
-2
a-direction coincides with local negative y-direction of axis-system.
-3
a-direction coincides with local negative z-direction of axis-system.
bdiri [2] The material b-direction is selected to be determined from one of the calculated local x-, y-, or z-directions of the axes-system. 1
b-direction coincides with local x-direction of axis-system.
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SET-AXES-MATERIAL
Chap. 7 Model definition
2
b-direction coincides with local y-direction of axis-system.
3
b-direction coincides with local z-direction of axis-system.
-1
b-direction coincides with local negative x-direction of axis-system.
-2
b-direction coincides with local negative y-direction of axis-system.
-3
b-direction coincides with local negative z-direction of axis-system.
Note: abs(adiri) must differ from abs(bdiri). Auxiliary commands LIST SET-AXES-MATERIAL SURFACES DELETE SET-AXES-MATERIAL SURFACES
FIRST LAST FIRST LAST
LIST SET-AXES-MATERIALVOLUMES DELETE SET-AXES-MATERIALVOLUMES
FIRST LAST FIRST LAST
LIST SET-AXES-MATERIAL FACES DELETE SET-AXES-MATERIALFACES
FIRST LAST FIRST LAST
LIST SET-AXES-MATERIAL BODIES DELETE SET-AXES-MATERIALBODIES
FIRST LAST FIRST LAST
LIST SET-AXES-MATERIALELEMENTSETS DELETE S ET-AXES-MATERIALELEMENTSETS
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facei axesi adiri bdiri SET-AXES-STRAIN BODIES bodyi axesi adiri bdiri SET-AXES-STRAIN ELEMENTSETS elementseti axesi adiri bdiri SET-AXES-STRAIN SURFACES assigns axes-systems, defined by AXES, to a set of geometry surfaces. SET-AXES-STRAIN VOLUMES assigns axes-systems, defined by AXES, to a set of geometry volumes. SET-AXES-STRAIN FACES assigns axes-systems, defined by AXES, to a set of solid geometry faces. SET-AXES-STRAIN BODIES assigns axes-system, defined by AXES, to a set of solid geometry bodies. SET-AXES-STRAIN ELEMENTSETS assigns axes-systems, defined by command AXES, to a set of element sets. BODY Label number of a solid geometry body.
[currently active body]
surfacei Label number of a geometry surface.
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SET-AXES-STRAIN
volumei Label number of a geometry volume. facei Label number of a solid geometry face (for BODY). bodyi Label number of a solid geometry body. Note:
Any elements generated for the referenced geometry will adopt initial-strain directions as calculated by the assigned axes-system.
elementseti Label number of a element set. Any elements generated in this element set will calculate orthotropic strain directions from the assigned the axes-system “axesi”. axesi Label number of an axes-system defined by AXES. adiri [1] The strain a-direction is selected to be determined from one of the calculated local x-, y- or zdirections of the axes-system. 1
a-direction coincides with local x-direction of axis-system.
2
a-direction coincides with local y-direction of axis-system.
3
a-direction coincides with local z-direction of axis-system.
-1
a-direction coincides with local negative x-direction of axis-system.
-2
a-direction coincides with local negative y-direction of axis-system.
-3
a-direction coincides with local negative z-direction of axis-system.
bdiri [2] The strain b-direction is selected to be determined from one of the calculated local x-, y- or zdirections of the axes-system. 1
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SET-AXES-STRAIN
Sec. 7.10 Systems
2
b-direction coincides with local y-direction of axis-system.
3
b-direction coincides with local z-direction of axis-system.
-1
b-direction coincides with local negative x-direction of axis-system.
-2
b-direction coincides with local negative y-direction of axis-system.
-3
b-direction coincides with local negative z-direction of axis-system.
Note: abs(adiri) must differ from abs(bdiri). Auxiliary commands LIST SET-AXES-STRAIN SURFACES DELETE SET-AXES-STRAIN SURFACES
FIRST LAST FIRST LAST
LIST SET-AXES-STRAIN VOLUMES DELETE SET-AXES-STRAIN VOLUMES
FIRST LAST FIRST LAST
LIST SET-AXES-STRAIN FACES DELETE SET-AXES-STRAIN FACES
FIRST LAST FIRST LAST
LIST SET-AXES-STRAIN BODIES DELETE SET-AXES-STRAIN BODIES
FIRST LAST FIRST LAST
LIST SET-AXES-STRAIN ELEMENTSETS FIRST LAST DELETE SET-AXES-STRAIN ELEMENTSETS FIRST LAST
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Chapter 8 Finite element representation
EGROUP TRUSS
EGROUPTRUSS
Sec. 8.1 Element groups
NAME SUBTYPE DISPLACEMENTS MATERIAL INT GAPS INITIALSTRAIN CMASS TIME-OFFSET OPTION RB-LINE AREA PRINT SAVE TBIRTH TDEATH TMC-MATERIAL GAPWIDTH
Defines an element group consisting of truss elements. NAME [(current highest element group label number) + 1] Label number of the element group to be defined. The label number of an existing element group can only be given if it is of type TRUSS. Hence, to re-define the type of a named element group you must first delete that group using command DELETE EGROUP TRUSS. SUBTYPE Indicates the type of TRUSS element.
[GENERAL]
GENERAL
General 3-D truss elements with 2-4 nodes.
AXISYMMETRIC
Axisymmetric truss (ring) elements with 1 node in the global YZ plane. Z is the axis of rotational symmetry and Y is the radial direction (Y ≥ 0).
DISPLACEMENTS [DEFAULT] Indicates whether large displacements are assumed for the kinematic formulation for the element group. SMALL
Small displacements only.
LARGE
Effects of large displacements are included.
DEFAULT
Formulation for element group defaults to that specified by KINEMATICS.
MATERIAL [1] The label number of the default material for an element group. Elements within the group may use a different material as specified by an element data command, but each material specified must be of the same model type as that of the material given by this parameter. Note:
Elements of type TRUSS can use materials of the following types: ELASTIC THERMO-ISOTROPIC PLASTIC-BILINEAR PLASTIC-MULTILINEAR
INT Numerical integration order. {1 ≤ INT ≤ 4} DEFAULT =1 2 3
[DEFAULT]
when SUBTYPE = AXISYMMETRIC, or maximum number of element nodes is 2. when maximum number of nodes per element is 3. when maximum number of nodes per element is 4.
GAPS
[NO]
YES
All elements in this (nonlinear) group have gaps, i.e., no element in the group can resist tensile force. The gap width for elements may be specified via the element data commands. This option may only be used when material models PLASTIC- BILINEAR or PLASTIC-MULTILINEAR are employed, in conjunction with 2-node general truss elements.
NO
The gap element option is inactive for this element group, and all elements can resist tensile as well as compressive forces.
INITIALSTRAIN Indicates whether initial strains are to be applied to this element group.
[NONE]
NONE
No initial strains for elements of this group.
NODAL
Only the nodal strains input via INITIAL-CONDITION are accounted for.
ELEMENT
Only the element strains input via the element data commands are accounted for.
BOTH
Both nodal and element strains are taken into consideration.
CMASS [MASTER CMASS] Requests the calculation of the following mass properties for the element group: total mass, total volume, moments and products of inertia, centroid, and center of mass. {YES/NO} TIME-OFFSET [0.0] With this parameter, a creep law can be modified as follows (example given for creep law number 1) : e c = a 0 ⋅ σ a1 ⋅ ( t − t 0 )
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EGROUP TRUSS
Sec. 8.1 Element groups
where t is the absolute time and t0=TIME-OFFSET represents a shift in the time scale. Note:
When TIME-OFFSET is used, the same shift is applied to all time dependent terms. The TIME-OFFSET value can be negative or positive and can be modified for a restart run.
OPTION Special option for this element group. NONE REBAR -
[NONE]
No special option. Elements are regular truss elements. Elements are used as rebar elements.
RB-LINE [1] Rebar label number as defined by the command REBAR-LINE. Only used if OPTION=REBAR. AREA Specifies the default cross-section area for elements in the group.
[1.0]
PRINT [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the PRINTDEFAULT parameter of the PRINTOUT command. {DEFAULT/NO/YES} SAVE [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the SAVEDEFAULT parameter of the PORTHOLE command. {DEFAULT/NO/YES} TBIRTH Default element birth time.
[0.0]
TDEATH Default element birth time.
[0.0]
TMC-MATERIAL Label number of ADINA-T material used for thermal coupling. GAPWIDTH Specifies the default gap width for truss element.
[1] [0.0]
Auxiliary commands LIST EGROUP TRUSS DELETE EGROUPTRUSS
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Chap. 8 Finite element representation
EGROUP TWODSOLID
EGROUP TWODSOLID NAME SUBTYPE DISPLACEMENTS STRAINS MATERIAL INT RESULTS DEGEN FORMULATION STRESSREFERENCE INITIALSTRAIN FRACTURE CMASS STRAIN-FIELD PNTGPS NODGPS LVUS1 LVUS2 SED RUPTURE INCOMPATIBLE-MODES TIME-OFFSET POROUS WTMC OPTION THICKNESS PRINT SAVE TBIRTH TDEATH TMC-MATERIAL RUPTURE-LABEL Defines an element group consisting of planar or axisymmetric elements. NAME [(current highest element group label number) + 1] Label number of the element group to be defined. The label number on an existing element group can only be given if it is of type TWODSOLID. Hence, to re-define the type of a named element group, you must first delete that group using command DELETE EGROUP TWODSOLID. SUBTYPE Indicates the type of TWODSOLID element. (See the Theory and Modeling Guide). AXISYMMETRIC
Axisymmetric elements in the global YZ plane. Z is the axis of rotational symmetry and Y is the radial direction (Y≥0).
STRAIN
Plane strain elements in the global YZ plane.
STRESS2
Plane stress elements in the global YZ plane.
STRESS3
3-D plane stress (membrane) elements.
STRAIN3
Generalized plane strain in the global YZ plane.
DISPLACEMENTS [DEFAULT] Indicates whether large displacements are assumed for the kinematic formulation for the element group. SMALL
Small displacements only.
LARGE
Effects of large displacements are included.
DEFAULT
Formulation for element group defaults to that specified by KINEMATICS.
STRAINS [DEFAULT] Indicates whether large strains are assumed for the kinematic formulation for the element group. 8-6
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EGROUP TWODSOLID
Sec. 8.1 Element groups
SMALL
Small strains only.
LARGE
Effects of large strains are included.
DEFAULT
Formulation for element group defaults to that specified by KINEMATICS.
Note: DISPLACEMENTS = LARGE is automatically set if STRAINS = LARGE is input. MATERIAL [1] The label number of the default material for an element group. Elements within the group may use a different material as specified by an element data command, but each material specified must be of the same model type as that of the material given by this parameter. Note:
Elements of type TWODSOLID can use materials of the following types. Only elements marked with an asterisk (*) can be used with large strains. ELASTIC ORTHOTROPIC *PLASTIC-BILINEAR *THERMO-PLASTIC DRUCKER-PRAGER GURSON *CREEP-VARIABLE *PLASTIC-CREEP CURVE-DESCRIPTION CONCRETE *ARRUDA-BOYCE *OGDEN *USER-SUPPLIED
INT Numerical integration order. {1 ≤ INT ≤ 6} DEFAULT
Full Gauss integration order, dependent on the polynomial order of the elements, i.e., the number of nodes per element side.
RESULTS The calculated element response from the ADINA analysis. FORCES
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[DEFAULT]
[STRESSES]
Element nodal forces are calculated, but stresses are not. These forces are equivalent, in the virtual work sense, to the internal element stresses. The reference system is that of the degree-offreedom system associated with the node (global or skew). 8-7
Chap. 8 Finite element representation
STRESSES
EGROUP TWODSOLID
Element stresses and strains are calculated at all integration points, but forces are not.
DEGEN [DEFAULT] Indicator for spatial isotropy correction for degenerate (triangular) 8-node elements. When true 6-node triangular elements are defined in this element group through ENODES command, DEGEN = UNUSED should be specified. The DEFAULT option means that the default is taken from the parameter DEGEN of the MASTER command. {DEFAULT/NO/YES/UNUSED} FORMULATION Indicates use of displacement or mixed interpolation formulation.
[DEFAULT]
DISPLACEMENT [1]
Displacement interpolation only.
MIXED [2]
Mixed pressure-displacement interpolation.
DEFAULT [0]
See note below.
-N
N is the number of pressure degrees of freedom for each element.
Note:
The mixed formulation cannot be used for material models CAM-CLAY, GURSON, CURVE-DESCRIPTION, CONCRETE, DRUCKER-PRAGER, MOHR-COULOMB and HYPER-FOAM. Furthermore, it is only applicable for plane strain, generalized plane strain and axisymmetric analyses.
Note:
The value DEFAULT assumes a MIXED formulation for element groups with material models OGDEN, MOONEY-RIVLIN, ARRUDA-BOYCE and SUSSMANBATHE. For all other material models the value assumed for DEFAULT is that of DISPLACEMENT formulation.
Note:
When using the mixed formulation, 1 pressure degree of freedom is used for elements with 8 or fewer nodes, and 3 pressure degrees of freedom are used for the 9-node element. In general, the 9-node element is the most effective, and is thus recommended. To explicitly set the number of pressure degrees of freedom, input FORMULATION = -N, where N is the desired number of pressure degrees of freedom within each element.
STRESSREFERENCE Indicates the reference system for calculated stresses.
8-8
[GLOBAL]
GLOBAL
The global Cartesian coordinate system (X, Y, Z).
MATERIAL
The element material system, for orthotropic materials.
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EGROUP TWODSOLID
Sec. 8.1 Element groups
INITIALSTRAIN Indicates whether initial strains are to be applied to this element group.
[NONE]
NONE
No initial strains for elements of this group.
NODAL
Only the nodal strains input via INITIAL-CONDITION are accounted for.
ELEMENT
Only the element strains input via the STRAIN-FIELD parameter are accounted for.
BOTH
Both nodal and element strains are taken into consideration.
FRACTURE This parameter is obsolete.
[NO]
CMASS [MASTER CMASS] Requests the calculation of the following mass properties for the element group: total mass, total volume, moments and products of inertia, centroid, and center of mass. {YES/NO} STRAIN-FIELD [0] Label number of a “strain-field” defined by STRAIN-FIELD command (Section7.9). A 0 value indicates no initial element strains, and any initial element strains selected by input of STRAIN-FIELD > 0 will only be considered if INITIALSTRAIN = ELEMENT or BOTH. PNTGPS [0] Label number of a geometry point at which the auxiliary node for generalized plane strain elements (SUBTYPE = STRAIN3) is located. NODGPS Label number of the auxiliary node for generalized plane strain elements. Note:
[0]
For SUBTYPE = STRAIN3, PNTGPS = NODGPS = 0 is not allowed (an auxiliary node must be specified). If PNTGPS and NODGPS are both > 0, then the input for PNTGPS is used.
LVUS1 This parameter is obsolete.
[0]
LVUS2 This parameter is obsolete.
[0]
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Chap. 8 Finite element representation
EGROUP TWODSOLID
SED [NO] Indicate whether or not to compute, and output, the strain energy density at all integration points of elements within the group. {NO/YES} RUPTURE [ADINA] Indicates whether the program rupture criteria or user-supplied rupture criteria to be applied to the material used in this element group. ADINA
Use the program criteria.
USER
User must provide fortran-coded subroutine CURUP2 to decide the element rupture.
Note that material models available for this option are: PLASTIC-BILINEAR, PLASTIC-MULTILINEAR, MROZ-BILINEAR, PLASTIC-ORTHOTROPIC, THERMO-PLASTIC, CREEP, PLASTIC-CREEP, MULTILINEAR-PLASTIC-CREEP, USER-SUPPLIED INCOMPATIBLE-MODES [DEFAULT] Specifies whether incompatible modes are included in the formulation of 4-node 2D solid elements. NO
Incompatible modes are not included.
YES
Incompatible modes are included.
DEFAULT
Choice of formulation is controled by the KINEMATICS command.
TIME-OFFSET [0.0] With this parameter, a creep law can be modified as follows (example given for creep law number 1) : e c = a 0 ⋅ σ a1 ⋅ ( t − t 0 )
a2
where t is the absolute time and t0=TIME-OFFSET represents a shift in the time scale. Note:
When TIME-OFFSET is used, the same shift is applied to all time dependent terms. The TIME-OFFSET value can be negative or positive and can be modified for a restart run.
POROUS This parameter is now obsolete. It is replaced by the parameter OPTION.
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EGROUP TWODSOLID
Sec. 8.1 Element groups
WTMC [1.0] Plastic work to heat factor for thermo-mechanical coupling. Must be in the range<0.0,1.0> OPTION {NONE/POROUS/USER-CODED/GASKET-SIMPLE/GASKET-GENERAL} NONE
No special option.
POROUS
This element group is used with porous media properties.
USER-CODED
User-supplied code is used for this element group.
GASKET-SIMPLE
This element group is used with a simple gasket material.
GASKET-GENERAL
This element group is used with a general gasket material.
THICKNESS Defines the default element thickness.
[NONE]
[1.0]
PRINT [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the PRINTDEFAULT parameter of the PRINTOUT command. {DEFAULT/NO/YES} SAVE [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the SAVEDEFAULT parameter of the PORTHOLE command. {DEFAULT/NO/YES} TBIRTH Default element birth time.
[0.0]
TDEATH Default element birth time.
[0.0]
TMC-MATERIAL Label number of ADINA-T material used for thermal coupling.
[1]
RUPTURE-LABEL User-rupture label number which is defined by the USER-RUPTURE command. Used only for RUPTURE = USER.
[0]
Auxiliary commands LIST EGROUP TWODSOLID DELETE EGROUP TWODSOLID ADINA R & D, Inc.
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Chap. 8 Finite element representation
EGROUP THREEDSOLID
EGROUP THREEDSOLID
NAME DISPLACEMENTS STRAINS MATERIAL RSINT TINT RESULTS DEGEN FORMULATION STRESSREFERENCE INITIALSTRAIN FRACTURE CMASS STRAIN-FIELD LVUS1 LVUS2 SED RUPTURE INCOMPATIBLE-MODES TIME-OFFSET POROUS WTMC OPTION PRINT SAVE TBIRTH TDEATH TMC-MATERIAL RUPTURE-LABEL
Defines an element group consisting of three-dimensional solid elements. NAME [(current highest element group label number )+ 1] Label number of the element group to be defined. The label number of an existing element group can only be given if it is of type THREEDSOLID. Hence, to re-define the type of a named element group you must first delete that group using command DELETE EGROUP THREEDSOLID. DISPLACEMENTS [DEFAULT] Indicates whether large displacements are assumed for the kinematic formulation for the element group. SMALL
Small displacements only.
LARGE
Effects of large displacements are included.
DEFAULT
Formulation for element group defaults to that specified by KINEMATICS.
STRAINS [DEFAULT] Indicates whether large strains are assumed for the kinematic formulation for the element group. SMALL
Small strains only.
LARGE
Effects of large strains are included.
DEFAULT
Formulation for element group defaults to that specified by KINEMATICS.
Note: DISPLACEMENTS = LARGE is automatically set if STRAINS = LARGE is input. MATERIAL [1] The label number of the default material for an element group. Elements within the group may use a different material, as specified by an element data command, but each material specified must be of the same model type as that of the material given by this parameter. 8-12
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EGROUP THREEDSOLID
Note:
Sec. 8.1 Element groups
Elements of type THREEDSOLID can use materials of the following types. Only elements marked with an asterisk (*) can be used with large strains. ELASTIC ORTHOTROPIC *PLASTIC-BILINEAR *THERMO-PLASTIC DRUCKER-PRAGER GURSON *CREEP-VARIABLE *PLASTIC-CREEP CURVE-DESCRIPTION CONCRETE *ARRUDA-BOYCE *OGDEN *USER-SUPPLIED
RSINT [DEFAULT] Numerical integration order for the r- and s- element coordinate directions. {2 ≤ RSINT ≤ 6} DEFAULT
Full Gauss integration order, dependent on the polynomial order of the elements, i.e., the number of nodes per element side.
TINT [DEFAULT] Numerical integration order for the t-element coordinate direction. {2 ≤ TINT ≤ 6} DEFAULT
Full Gauss integration order, dependent on the polynomial order of the elements, i.e., the number of nodes per element side.
RESULTS The calculated element response from the ADINA analysis.
[STRESSES]
FORCES
Element nodal forces are calculated, but stresses are not. These forces are equivalent, in the virtual work sense, to the internal element stresses. The reference system is that of the degree-offreedom system associated with the node (global or skew).
STRESSES
Element stresses and strains are calculated at all integration points, but forces are not.
DEGEN [DEFAULT] Indicator for spatial isotropy correction of degenerate 20-node elements. When true 10-node tetrahedral elments are defined in this element group through ENODES command, DEGEN = UNUSED should be specified. The DEFAULT option means that the default is taken from the parameter DEGEN of the MASTER command.{DEFAULT/NO/YES/UNUSED} ADINA R & D, Inc.
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Chap. 8 Finite element representation
EGROUP THREEDSOLID
FORMULATION Indicates use of displacement or mixed interpolation formulation. DISPLACEMENT [1] Displacement interpolation only.
[DEFAULT]
MIXED [2]
Mixed pressure-displacement interpolation.
DEFAULT [0]
See note below.
-N
N is the number of pressure degrees of freedom for each element.
Note:
The mixed formulation cannot be used for material models CAM-CLAY, GURSON, CURVE-DESCRIPTION, CONCRETE, DRUCKER-PRAGER, MOHR-COULOMB, and HYPER-FOAM.
Note:
The value DEFAULT assumes a MIXED formulation for element groups with material models OGDEN, MOONEY-RIVLIN, ARRUDA-BOYCE and SUSSMANBATHE. For all other material models the value assumed for DEFAULT is that of DISPLACEMENT formulation.
Note:
When using the mixed formulation, 1 pressure degree of freedom is used for elements with 8 to 21 nodes, and 4 pressure degrees of freedom are used for the 27-node element. In general, the 27-node element is the most effective, and is thus recommended. To explicitly set the number of pressure degrees of freedom, input FORMULATION = -N, where N is the desired number of pressure degrees of freedom within each element.
STRESSREFERENCE Indicates the reference system for calculated stresses.
[GLOBAL]
GLOBAL
The global Cartesian coordinate system (X, Y, Z).
MATERIAL
The element material system, for orthotropic materials.
INITIALSTRAIN Indicates initial strains applied to this element group.
[NONE]
NONE
No initial strains for elements of this group.
NODAL
Only the nodal strains input via INITIAL-CONDITION are accounted for.
ELEMENT
Only the element strains input via the STRAIN-FIELD parameter are accounted for.
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EGROUP THREEDSOLID
Sec. 8.1 Element groups
Nodal and element strains are taken into consideration.
BOTH FRACTURE This parameter is obsolete.
[NO]
CMASS [MASTER CMASS] Requests the calculation of the following mass properties for the element group: total mass, total volume, moments and products of inertia, centroid, and center of mass. {YES/NO} STRAIN-FIELD [0] Label number of a “strain-field” defined by STRAIN-FIELD command (Section7.9). A 0 value indicates no initial element strains, and any initial element strains selected by input of STRAIN-FIELD > 0 will only be considered if INITIALSTRAIN = ELEMENT or BOTH. LVUS1 This parameter is obsolete.
[0]
LVUS2 This parameter is obsolete.
[0]
SED [NO] Indicate whether or not to compute, and output, the strain energy density at all integration points of elements within the group. {YES/NO} RUPTURE [ADINA] Indicates whether the program rupture criteria or user-supplied rupture criteria to be applied to the material used in this element group. ADINA
Use the program criteria.
USER
User must provide fortran-coded subroutine CURUP3 to decide the element rupture.
Note:
Material models available for this option are: PLASTIC-BILINEAR, PLASTIC-MULTILINEAR, MROZ-BILINEAR, PLASTIC-ORTHOTROPIC, THERMO-PLASTIC, CREEP, PLASTIC-CREEP, MULTILINEAR-PLASTIC-CREEP, USER-SUPPLIED
INCOMPATIBLE-MODES [DEFAULT] Specifies whether incompatible modes are included in the formulation of 8-node 3D solid elements. NO
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Incompatible modes are not included.
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Chap. 8 Finite element representation
YES DEFAULT
EGROUP THREEDSOLID
Incompatible modes are included. Choice of formulation is controled by the KINEMATICS command
TIME-OFFSET [0.0] With this parameter, a creep law can be modified as follows (example given for creep law number 1) :
e c = a 0 ⋅ σ a1 ⋅ ( t − t 0 )
a2
where t is the absolute time and t0=TIME-OFFSET represents a shift in the time scale. Note:
When TIME-OFFSET is used, the same shift is applied to all time dependent terms. The TIME-OFFSET value can be negative or positive and can be modified for a restart run.
POROUS [NO] Indicates whether porous media properties are used for elements in this group. {NO/YES} WTMC [1.0] Plastic work to heat fator for thermo-mechanical coupling. Must be in the range <0.0,1.0> OPTION {NONE,POROUS,USER-CODED, GASKET-SIMPLE,GASKET-GENERAL} NONE
No special option.
USER-CODED
User-supplied code is used for this element group.
GASKET-SIMPLE
This element group is used with a simple gasket material.
GASKET-GENERAL
This element group is used with a general gasket material.
[NONE]
PRINT [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the PRINTDEFAULT parameter of the PRINTOUT command. {DEFAULT/NO/YES} SAVE [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the SAVEDEFAULT parameter of the PORTHOLE command. {DEFAULT/NO/YES} TBIRTH Default element birth time.
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EGROUP THREEDSOLID
Sec. 8.1 Element groups
TDEATH Default element birth time.
[0.0]
TMC-MATERIAL Label number of ADINA-T material used for thermal coupling.
[1]
RUPTURE-LABEL User-rupture label number which is defined by the USER-RUPTURE command. Used only for RUPTURE = USER.
[0]
Auxiliary commands LIST GROUP THREEDSOLID DELETE EGROUP THREEDSOLID
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EGROUP BEAM
Sec. 8.1 Element groups
EGROUP BEAM
NAME SUBTYPE DISPLACEMENTS MATERIAL RINT SINT TINT RESULTS INITIALSTRAIN CMASS RIGIDENDTYPE MOMENT-CURVATURE RIGIDITY MULTIPLY BOLT RUPTURE OPTION BOLT-TOL SECTION PRINT SAVE TBIRTH TDEATH SPOINT BOLTFORCE BOLTNCUR TMC-MATERIAL BOLT-NUMBER BOLT-LOAD WARP
Defines an element group consisting of Hermitian beam elements. NAME [(current highest element group label number) + 1] Label number of the element group to be defined. The label number of an existing element group can be given only if it is of type BEAM. Hence, to re-define the type of a named element group, you must first delete that group using DELETE EGROUP BEAM. SUBTYPE Indicates the type of BEAM element.
[THREE-D]
TWO-D
Two-dimensional action beam elements, defined parallel to one of the X-Y, Y-Z, or X-Z global coordinate planes.
THREE-D
Three-dimensional action beam elements.
DISPLACEMENTS [DEFAULT] Indicates whether large displacements are assumed for the kinematic formulation for the element group. SMALL
Small displacements only.
LARGE
Effects of large displacements are included.
DEFAULT
Formulation for element group defaults to that specified by KINEMATICS.
MATERIAL [1] The label number of the default material for an element group. Elements within the group may use a different material, as specified by an element data command, but each material specified must be of the same model type as that of the material given by this parameter. Note:
Elements of type BEAM can use materials of the following types: ELASTIC PLASTIC-BILINEAR
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Chap. 8 Finite element representation
EGROUP BEAM
RINT [5] Numerical integration order along the centroidal axis of each element, the local element rdirection. {1 ≤ RINT ≤ 7} SINT [DEFAULT] Numerical integration order for the local s-direction of each element, which lies in the element plane defined by the element nodes including the auxiliary node. {1 ≤ SINT ≤ 7} DEFAULT = 7
for 3-D action elements of rectangular cross-section, 3 otherwise.
TINT [DEFAULT] Numerical integration order for the local t-direction of each general 3-D beam element, normal to the plane of the element. {1 ≤ TINT ≤ 8} DEFAULT = 1 7 5 8 Note:
for 2-D action elements of rectangular cross-section. for 3-D action elements of rectangular cross-section. for 2-D action elements of pipe cross-section. for 3-D action elements of pipe cross-section.
The element matrices are integrated exactly when used in conjunction with a linear elastic material, and, therefore, parameters RINT, SINT, TINT are not considered.
RESULTS [STRESSES] The calculated element response from the ADINA analysis. {STRESSES/FORCES/ SFORCES} FORCES
Element nodal forces are calculated, but stresses are not. These forces are equivalent, in the virtual work sense, to the internal element stresses.
STRESSES
Element stresses and strains are calculated at all integration points, but forces are not.
SFORCES
Element forces and moments are calculated at equidistant section points along the length of the element. The number of section points is set by the parameter SPOINT. This option is only available for static, linear analysis.
Note:
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When an elastic material model is used, the choice STRESSES is not considered since no integration point data are available. In this case, the default ouput choice is FORCES.
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
EGROUP BEAM
Sec. 8.1 Element groups
INITIALSTRAIN Indicates initial strains applied to this element group.
[NONE]
NONE
No initial strains for elements of this group.
NODAL
Only the nodal strains input via INITIAL-CONDITION are accounted for.
ELEMENT
Only the element strains input via the EDATA command are accounted for.
BOTH
Both nodal and element strains are taken into consideration.
CMASS [MASTER CMASS] Requests the calculation of the following mass properties for the element group: total mass, total volume, moments and products of inertia, centroid, and center of mass. {YES/NO} RIGIDENDTYPE [NONE] Specifies whether rigid end-zones exist for elements of the group. See the Theory and Modeling Guide. NONE
No rigid end-zones are defined.
ABSOLUTE
Rigid end-zones are defined in terms of dimensions in length units.
INFINITE
Rigid end-zones with infinite stiffness are defined in terms of dimensions in length units.
MOMENT-CURVATURE [NO] Specifies whether or not moment-curvature properties are to be utilized by elements in the group. {YES/NO} RIGIDITY [0] Label number of a rigidity moment-curvature property set to be used for elements of the group. See RIGIDITY-MOMENT-CURVATURE. Used when MOMENT-CURVATURE = YES. MULTIPLY [1.0E6] This parameter is only applicable if RIGIDENDTYPE=ABSOLUTE. It specifies a multiplier to the stiffness properties of the element in case of rigid ends. The multiplier is used to compute the stiffness of the rigid ends. {>=0.0} BOLT This parameter in now obsolete. It is replaced by the parameter OPTION.
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[NO]
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Chap. 8 Finite element representation
EGROUP BEAM
RUPTURE [ADINA] Indicates whether the program rupture criteria or user-supplied rupture criteria to be applied to the material used in this element group. ADINA
Use the program criteria.
USER
User must provide fortran-coded subroutine CURUP4 to decide the element rupture.
Note that the only material model available for this option is: RIGIDITY-MOMENT-CURVATURE PLASTIC-MULTILINEAR OPTION Option for the behaviour of beam elements in this group. {NONE/BOLT}
[NONE]
BOLT-TOL [0.0] Bolt force tolerance used to determine convergence. During solution iterations, the element internal force is compared with the preload force. If the difference is within the tolerance, the converged solution is obtained. BOLT-TOL=0.0 means the default bolt tolerance specified in BOLT-OPTIONS command will be used. SECTION Specifies the default cross section label for elements in the group.
[1]
PRINT [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the PRINTDEFAULT parameter of the PRINTOUT command. {DEFAULT/NO/YES} SAVE [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the SAVEDEFAULT parameter of the PORTHOLE command. {DEFAULT/NO/YES} TBIRTH Default element birth time.
[0.0]
TDEATH Default element birth time.
[0.0]
SPOINT Specifies the number of section points for output of section forces when RESULTS=SFORCES. The points are located equidistant along length of the element. { 2 ≤ SPOINT ≤ 7 }
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EGROUP BEAM
Sec. 8.1 Element groups
Note: SPOINT is only considered when the option SFORCES is used in the parameter RESULTS. BOLTFORCE This parameter is obsolete.
[0.0]
BOLTNCUR This parameter is obsolete.
[0]
TMC-MATERIAL Label number of ADINA-T material used for thermal coupling.
[1]
BOLT-NUMBER [0] Specifies the bolt number for the current group. It can be used in the command BOLT-TABLE. BOLT-LOAD [0.0] The parameter BOLTFORCE is obsolete. BOLT-LOAD takes it place, and specifies the default bold load for each element. A bolt can be either be of the type force-tensioning or lengthreducing. WARP Specifies whether warping degress of freedom are active. {NO/YES} NO
No warping DOF
YES
Warping DOF is active.
[NO]
Auxiliary commands LIST EGROUP BEAM DELETE EGROUP BEAM
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Chap. 8 Finite element representation
EGROUP ISOBEAM
EGROUP ISOBEAM
NAME SUBTYPE DISPLACEMENTS MATERIAL RINT SINT TINT RESULTS INITIALSTRAIN CMASS RUPTURE TIME-OFFSET OPTION SECTION THICKNESS PRINT SAVE TBIRTH TDEATH TMC-MATERIAL
Defines an element group consisting of isoparametric beam elements. NAME [(current highest element group label number) + 1] Label number of the element group to be defined. The label number of an existing element group can be given only if it is of type ISOBEAM. Hence, to re-define the type of a named element group, you must first delete that group using DELETE EGROUP ISOBEAM. SUBTYPE Indicates the type of ISOBEAM element.
[GENERAL]
GENERAL
General three-dimensional beam elements.
PLSTRAIN
Plane strain elements in the global YZ plane.
PLSTRESS
Plane stress elements in the global YZ plane.
AXISYMMETRIC
Axisymmetric elements in the global YZ plane. Z is the axis of rotational symmetry and Y is the radial direction (Y ≥ 0).
DISPLACEMENTS [DEFAULT] Indicates whether large displacements are assumed for the kinematic formulation for the element group. SMALL
Small displacements only.
LARGE
Effects of large displacements are included.
DEFAULT
Formulation for element group defaults to that specified by KINEMATICS.
MATERIAL [1] The label number of the default material for an element group. Elements within the group may use a different material as specified by an element data command, but each material specified must be of the same model type as that of the material given by this parameter. Note:
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Elements of type ISOBEAM can use materials of the following types:
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
EGROUP ISOBEAM
Sec. 8.1 Element groups
ELASTIC THERMO-ISOTROPIC PLASTIC-BILINEAR PLASTIC-MULTILINEAR THERMO-PLASTIC CREEP PLASTIC-CREEP MULTILINEAR-PLASTIC-CREEP CREEP-VARIABLE PLASTIC-CREEP-VARIABLE MULTILINEAR-PLASTIC-CREEP-VARIABLE RINT [DEFAULT] Numerical integration order along the centroidal axis of each element (the local element rdirection). Negative values imply the closed Newton-Cotes integration method, and zero or positive values the Gauss integration method. Possible values/orders include: RINT
The Gauss integration order such that the element matrix obtained is equivalent to the mixed formulation for this element. With this integration order, the elements do not contain any spurious zero energy modes, do not lock and are efficient in general nonlinear analysis.
SINT [DEFAULT] Numerical integration order for the local s-direction of each element, which lies in the element plane defined by the element nodes (including the auxiliary node). The same input convention for RINT is assumed. (Note, however, that ADINA will currently employ the 4-point Gauss or the 7-point Newton-Cotes method for general 3-D isobeam elements, overriding your input value). For plane stress/strain beams or axisymmetric shell elements, we have: 2
≤ SINT ≤
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4
Gauss method.
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Chap. 8 Finite element representation
-7
≤ SINT ≤ -3
DEFAULT =
4 2
EGROUP ISOBEAM
Newton-Cotes method. for general 3-D elements. for plane stress/strain, axisymmetric elements.
TINT [4] Numerical integration order for the local t-direction of each general 3-D beam element, normal to the plane of the element. The same input convention for RINT, SINT is used, but note that ADINA employs either the 4-point Gauss or the 7-point Newton-Cotes method, overriding the input value. RESULTS The calculated element response from the ADINA analysis.
[STRESSES]
FORCES
Element nodal forces are calculated, but stresses are not. These forces are equivalent, in the virtual work sense, to the internal element stresses.
STRESSES
Element stresses and strains are calculated at all integration points, but forces are not.
INITIALSTRAIN Indicates initial strains applied to this element group.
[NONE]
NONE
No initial strains for elements of this group.
NODAL
Only the nodal strains are accounted for; these can be input with the INITIAL-CONDITION or ELEMENT-DATA commands.
ELEMENT
Only the element strains are accounted for; these can be input with the INITIAL-CONDITION or ELEMENT-DATA commands.
BOTH
Both nodal and element strains are taken into consideration.
CMASS [MASTER CMASS] Requests the calculation of the following mass properties for the element group: total mass, total volume, moments and products of inertia, centroid, and center of mass. {YES/NO} RUPTURE [ADINA] Indicates whether the program rupture criteria or user-supplied rupture criteria to be applied to the material used in this element group. ADINA
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Use the program criteria.
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
EGROUP ISOBEAM
USER
Sec. 8.1 Element groups
User must provide fortran-coded subroutine CURUP5 to decide the element rupture.
Note that material models available for this option are: PLASTIC-BILINEAR, PLASTIC-MULTILINEAR, THERMO-PLASTIC, CREEP, PLASTIC-CREEP, MULTILINEAR-PLASTIC-CREEP TIME-OFFSET [0.0] With this parameter, a creep law can be modified as follows (example given for creep law number 1) :
e c = a 0 ⋅ σ a1 ⋅ ( t − t 0 )
a2
where t is the absolute time and t0=TIME-OFFSET represents a shift in the time scale. Note:
When TIME-OFFSET is used, the same shift is applied to all time dependent terms. The TIME-OFFSET value can be negative or positive and can be modified for a restart run.
OPTION Indicates whether user-supplied code is used for this element group. {NONE / USER-CODED}
[NONE]
If OPTION = USER-CODED, then {SUBTYPE, INITIALSTRAIN, CMASS, RUPTURE} are not applicable SECTION [1] Specifies the default cross-section label for elements (excluding axisymmetric shell) in the group. THICKNESS Specifies the default thickness of axisymmetric shell elements in the group.
[1.0]
PRINT [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the PRINTDEFAULT parameter of the PRINTOUT command. {DEFAULT/NO/YES} SAVE [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the SAVEDEFAULT parameter of the PORTHOLE command. {DEFAULT/NO/YES} TBIRTH Default element birth time.
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[0.0]
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Chap. 8 Finite element representation
EGROUP ISOBEAM
TDEATH Default element birth time.
[0.0]
TMC-MATERIAL Label number of ADINA-T material used for thermal coupling.
[1]
Auxiliary commands LIST EGROUP ISOBEAM DELETE EGROUP ISOBEAM
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EGROUP PLATE
EGROUP PLATE
Sec. 8.1 Element groups
NAME DISPLACEMENTS MATERIAL INT RESULTS INITIALSTRAIN CMASS THICKNESS PRINT SAVE TBIRTH TDEATH
Defines an element group consisting of plate elements. NAME [(current highest element group label number) + 1] Label number of the element group to be defined. The label number of an existing element group can be given only if it is of type PLATE. Hence, to re-define the type of a named element group, you must first delete that group using DELETE EGROUP PLATE. DISPLACEMENTS [DEFAULT] Indicates whether large displacements are assumed for the kinematic formulation for the element group. SMALL
Small displacements only.
LARGE
Effects of large displacements are included.
DEFAULT
Formulation for element group defaults to that specified by KINEMATICS.
MATERIAL [1] The label number of the default material for the element group. Elements within the group may use a different material, but each material specified must be of the same model type as that of the material given by this parameter. Note:
Elements of type PLATE can use materials of the following types: ELASTIC ORTHOTROPIC ILYUSHIN
INT [2] Integration scheme indicator. See the Theory and Modeling Guide for the triangular element integration schemes. {1 ≤ INT ≤ 4} 1 2 3 4 Note:
1-point (centroid). 3-point (interior). 3-point (mid-side). 7-point (interior). For linear analysis (small displacement, elastic material) ADINA uses the integration scheme given by INT = 2; the input value for parameter INT is thus ignored.
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Chap. 8 Finite element representation
RESULTS The calculated element response from the ADINA analysis.
EGROUP PLATE
[STRESS-RESULTANTS]
FORCES
Element nodal forces and moments are calculated, but stresses are not. These forces/moments are equivalent, in the virtual work sense, to the internal element stresses. The reference system is that of the degree-of-freedom system associated with the node (global or skew).
STRESS-RESULTANTS
Element stress resultants are calculated at all integration points, but forces are not.
INITIALSTRAIN Indicates initial strains applied to this element group.
[NONE]
NONE
No initial strains for elements of this group.
NODAL
Only the nodal strains input via INITIAL-CONDITION are accounted for.
ELEMENT
Only the element strains input via element data commands are accounted for.
BOTH
Both nodal and element strains are taken into consideration.
CMASS [MASTER CMASS] Requests the calculation of the following mass properties for the element group: total mass, total volume, moments and products of inertia, centroid, and center of mass. {YES/NO} THICKNESS Defines the default element thickness.
[1.0]
PRINT [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the PRINTDEFAULT parameter of the PRINTOUT command. {DEFAULT/NO/YES} SAVE [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the SAVEDEFAULT parameter of the PORTHOLE command. {DEFAULT/NO/YES} TBIRTH Default element birth time.
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EGROUP PLATE
TDEATH Default element birth time.
[0.0]
Auxiliary commands LIST EGROUPPLATE DELETE EGROUPPLATE
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EGROUP SHELL
EGROUP SHELL
Sec. 8.1 Element groups
NAME DISPLACEMENTS MATERIAL RINT SINT TINT RESULTS STRESSREFERENCE PRINTVECTORS NLAYERS INITIALSTRAIN FAILURE SECTIONRESULT CMASS STRAINS RUPTURE TIME-OFFSET OPTION THICKNESS INCOMPATIBLE-MODES PRINT SAVE TBIRTH TDEATH TINT-TYPE TMC-MATERIAL WTMC RUPTURE-LABEL RELROT-PENALTY
Defines an element group consisting of shell elements. NAME [(current highest element group label number) + 1] Label number of the element group to be defined. The label number of an existing element group can be given only if it is of type SHELL. Hence, to re-define the type of a named element group, you must first delete that group using DELETE EGROUP SHELL. DISPLACEMENTS [DEFAULT] Indicates whether large displacements are assumed for the kinematic formulation for the element group. SMALL
Small displacements only.
LARGE
Effects of large displacements are included.
DEFAULT
Formulation for element group defaults to that specified by KINEMATICS.
MATERIAL [1] The label number of the default material for the element group. Elements within the group may use a different material, but each material specified must be of the same model type as that of the material given by this parameter. Note:
Elements of type SHELL can use materials of the following types. Only elements marked with an asterisk (*) can be used with large strains, but are restricted to 3-, 4-, 9-, or 16-node single layer shell elements, in which the shell geometry is described in terms of midsurface nodes. ELASTIC *PLASTIC-MULTILINEAR ORTHOTROPIC CREEP THERMO-ISOTROPIC THERMO-PLASTIC *PLASTIC-BILINEAR PLASTIC-CREEP *PLASTIC-ORTHOTROPIC MULTILINEAR-PLASTIC-CREEP CREEP-VARIABLE PLASTIC-CREEP-VARIABLE MULTILINEAR-PLASTIC-CREEP-VARIABLE
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EGROUP SHELL
RINT [DEFAULT] Integration order for the local r-direction of the elements. {1 ≤ RINT ≤ 6} DEFAULT Full Gauss integration order, the reliable integration order, dependent on the polynomial order of the elements, i.e., the number of nodes per element side. SINT Integration order for the local s-direction of the elements. {1 ≤ SINT ≤ 6} DEFAULT
[DEFAULT]
same as RINT.
Note: For a triangular shell element, the integration scheme uses the following number of sampling points. See the Theory and Modeling Guide. NRS = RINT × SINTNo. of integration points 1 1 < NRS ≤ 4 4 < NRS ≤ 9 9 < NRS ≤ 36
1 4 7 13
TINT Integration order for the local t-direction (through thickness) of the elements.
[2]
TINT > 0
Gauss, Newton-Cotes or trapezoidal rule integration, see parameter TINT-TYPE
-7 ≤ TINT ≤ -3
Newton-Cotes integration (for backwards compatibility with previous versions of the AUI)
Note: For multilayer shell elements this integration order is applied to each layer. RESULTS The calculated element response from the ADINA analysis.
[STRESSES]
FORCES
Element nodal forces and moments are calculated, but stresses are not. These forces/moments are equivalent, in the virtual work sense, to the internal element stresses. The reference system is that of the degree-of-freedom system associated with the node (global or skew).
STRESSES
Element stresses and strains are calculated at all integration
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Sec. 8.1 Element groups
points, but forces are not. STRESSREFERENCE [GLOBAL] Indicates the reference system for calculated stresses. {GLOBAL/LOCAL/MATERIAL/ MIDSURFACE } GLOBAL
The global Cartesian coordinate system (X, Y, Z).
LOCAL
The local element system (r, s, t).
MATERIAL
The element material system, for orthotropic materials.
MIDSURFACE
The mid-surface coordinate system ( rˆ, sˆ, tˆ ).See Theory and Modeling Guide.
PRINTVECTORS [0] Indicator for printing, by ADINA, of the direction cosines of the element midsurface vectors (at the nodal points). 0
No printing.
1
Initial direction cosines printed.
2
Initial and updated direction cosines printed.
NLAYERS The number of layers for elements of the group. See LAYER. INITIALSTRAIN Indicates initial strains applied to this element group.
[1] [NONE]
NONE
No initial strains for elements of this group.
NODAL
Only the nodal strains input via INITIAL-CONDITION are accounted for.
ELEMENT
Only the element strains input via element data commands are accounted for.
BOTH
Both nodal and element strains are taken into consideration.
FAILURE [0] Label number of the default failure criterion assigned to elements of this group. Elements ADINA R & D, Inc.
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within the group may use a different failure criterion, but each failure criterion specified must be of the same type as that of the failure criterion given by this parameter, see FAILURE. A 0 value indicates no failure criterion to be used. Note that material models available for this option are: ISOTROPIC ORTHOTROPIC THERMO-ISOTROPIC THERMO-ORTHOTROPIC SECTIONRESULT [0] Indicates which of the following are calculated at integration point midsurface locations: element force and moment resultants (per unit length), membrane strains and curvatures and positions of the neutral axes. Printing and saving of this data for each element may be specified by the element data commands. -2
Calculation of force/moment resultants, strains/curvatures, neutral axes.
-1
Calculation of force/moment resultants, strains/curvatures.
0
No calculation.
1
Calculation of force/moment resultants.
2
Calculation of force/moment resultants, neutral axes.
Note:
Parameter SECTIONRESULT takes effect only if parameter RESULTS = STRESSES, and if the calculated data refers to the local element (r, s, t) system.
CMASS [MASTER CMASS] Requests the calculation of the following mass properties for the element group: total mass, total volume, moments and products of inertia, centroid, and center of mass. {YES/NO} STRAINS [DEFAULT] Indicates whether large strains are assumed for the kinematic formulation for the element group. SMALL
Small strains only.
LARGE
Effects of large strains are included. For details of restrictions, please refer to the note under the parameter MATERIAL.
DEFAULT
Formulation for element group defaults to that specified by KINEMATICS.
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Sec. 8.1 Element groups
Note: DISPLACEMENTS = LARGE is automatically set if STRAINS = LARGE is input. RUPTURE [ADINA] Indicates whether the program rupture criteria or user-supplied rupture criteria to be applied to the material used in this element group. ADINA
Use the program criteria.
USER
User must provide fortran-coded subroutine CURUP7 to decide the element rupture.
Note that material models available for this option are: PLASTIC-BILINEAR, PLASTIC-MULTILINEAR, PLASTIC-ORTHOTROPIC, THERMO-PLASTIC, CREEP, PLASTIC-CREEP, MULTILINEAR-PLASTIC-CREEP TIME-OFFSET [0.0] With this parameter, a creep law can be modified as follows (example given for creep law number 1) :
e c = a 0 ⋅ σ a1 ⋅ ( t − t 0 )
a2
where t is the absolute time and t0=TIME-OFFSET represents a shift in the time scale. Note:
When TIME-OFFSET is used, the same shift is applied to all time dependent terms. The TIME-OFFSET value can be negative or positive and can be modified for a restart run.
OPTION Indicates whether user-supplied code is used for this element group. {NONE / USER-CODED}
[NONE]
if OPTION = USER-CODED, then {STRESSREFERENCE, PRINTVECTORS, NLAYERS, INITIALSTRAIN, FAILURE, SECTIONRESULT, CMASS, STRAINS, RUPTURE} are not applicable THICKNESS Specifies the default thickness of elements in the group.
[1.0]
INCOMPATIBLE-MODES [DEFAULT] Specifies whether incompatible modes are included in the formulation of 4-node shell elements. {NO/YES/DEFAULT} NO
Incompatible modes are not included
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YES
EGROUP SHELL
Incompatible modes are included
DEFAULT Choice of formulation is set by the KINEMATICS command Incompatible modes are only applicable to quadrilateral MITC4 elements. They are not applicable to triangular collapsed MITC4 elements. PRINT [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the PRINTDEFAULT parameter of the PRINTOUT command. {DEFAULT/NO/YES} SAVE [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the SAVEDEFAULT parameter of the PORTHOLE command. {DEFAULT/NO/YES} TBIRTH Default element birth time.
[0.0]
TDEATH Default element birth time.
[0.0]
TINT-TYPE [GAUSS] Parameter TINT-TYPE controls the type of numerical integration through the shell thickness. GAUSS
Gauss integration is used with TINT points. (2 ≤ TINT ≤ 6)
NEWTON-COTES
Newton-Cotes integration is used with TINT points. (TINT = 3,5,7)
TRAPEZOIDAL
Trapezoidal rule integration is used with TINT points. Can only be used with MITC3, MITC4, MITC6, MITC9, MITC16 single layer shell elements. ( 2 ≤ TINT ≤ 20)
If TINT < 0, then Newton-Cotes integration is always used regardless of the value of TINTTYPE (for backwards compatibility with previous versions of the AUI). TMC-MATERIAL Label number of ADINA-T material used for thermal coupling.
[1]
WTMC [1.0] Plastic work to heat factor for the thermo-mechanical coupling. ( 0.0 ≤ WTMC ≤ 1.0)
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EGROUP SHELL
RUPTURE-LABEL User-rupture label number which is defined by the USER-RUPTURE command. Used only for RUPTURE = USER.
[0]
Auxiliary commands LIST EGROUP SHELL DELETE EGROUP SHELL
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EGROUP PIPE
NAME DISPLACEMENTS MATERIAL RINT SINT TINT RESULTS OVALIZATION INITIALSTRAIN ICALRA RADTOL CMASS RUPTURE TIME-OFFSET OPTION BOLT-TOL SECTION PRINT SAVE TBIRTH TDEATH BOLTFORCE BOLTNCUR TMC-MATERIAL
Defines an element group consisting of pipe elements. See the Theory and Modeling Guide for a complete description of pipe elements. NAME [(current highest element group label number) + 1] Label number of the element group to be defined. The label number of an existing element group can only be given if it is of type PIPE. Hence, to re-define the type of a named element group, you must first delete that group using DELETE EGROUP PIPE. DISPLACEMENTS [DEFAULT] Indicates whether large displacements are assumed for the kinematic formulation for the element group. SMALL
Small displacements only.
LARGE
Effects of large displacements are included.
DEFAULT
Formulation for element group defaults to that specified by KINEMATICS.
MATERIAL [1] The label number of the default material for an element group. Elements within the group may use a different material, as specified by element data command, but each material specified must be of the same model type as that of the material given by this parameter. Note:
Elements of type PIPE can use materials of the following types: ELASTIC, THERMO-ISOTROPIC, PLASTIC, PLASTIC-MULTILINEAR, THERMOPLASTIC, CREEP, PLASTIC-CREEP, CREEP-VARIABLE, MULTILINEAR-PLASTIC-CREEP, PLASTIC-CREEP-VARIABLE, MULTILINEAR-PLASTIC-CREEPVARIABLE
RINT [DEFAULT] Numerical integration order along the centroidal axis of each element (the local element rdirection). Negative values imply the closed Newton-Cotes integration method, and zero or positive values the Gauss integration method. DEFAULT
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AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
SINT [DEFAULT] Numerical integration order for the local s-direction of each element, which is the radial direction of the pipe). The same input convention for RINT is assumed. TINT [DEFAULT] Numerical integration order for the local t-direction or circumferential direction used in the composite trapezoidal rule. Only 4, 8, 12 or 24 integration points can be employed and the following default values are used by ADINA when other values of TINT are specified. 4 < TINT ≤ 8 < TINT ≤ 12 < TINT ≤
7 11 24
8 12 24
If element warping/ovalization is enabled then TINT ≥ 12 must be used for TINT = 24 must be used for DEFAULT
= 8 = 12 = 24
when when when
MASTER OVALIZATION = IN-PLANE. MASTER OVALIZATION = OUT-OF-PLANE or ALL. MASTER OVALIZATION = NO. MASTER OVALIZATION = IN-PLANE. MASTER OVALIZATION = OUT-OF-PLANE or ALL.
RESULTS The calculated element response from the ADINA analysis. FORCES
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[STRESSES]
Element nodal forces are calculated, stresses are not. These forces are equivalent, in the virtual work sense, to the internal element stresses.
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STRESSES
EGROUP PIPE
Element stresses and strains are calculated at all integration points, but no forces.
OVALIZATION [DEFAULT] Flag that indicates whether or not the pipe nodes in this element group have ovalization/ warping degrees of freedom. NO
Pipe element nodes do not have ovalization/warping degrees of freedom.
DEFAULT
Warping/Ovalization based on MASTER command. NO if MASTER OVALIZATION = NO YES if MASTER OVALIZATION = IN-PLANE, OUT-OF-PLANE or ALL.
INITIALSTRAIN Indicates initial strains applied to this element group.
[NONE]
NONE
No initial strains for elements of this group.
NODAL
Only the nodal strains input via INITIAL-CONDITION are accounted for.
ELEMENT
Only the element strains input via element data commands are accounted for.
BOTH
Both nodal and element strains are taken into consideration.
ICALRA Flag for the calculation of internal radii and internal areas at pipe nodes.
[0]
0
Internal radii and internal areas are not calculated.
1
Internal radii and internal areas are calculated and stored on the porthole file.
2
Internal radii and internal areas are calculated, stored on the porthole file and printed out.
RADTOL [0.001] For 4-node, circular bend pipe elements, the nodes should lie on a circular arc with the auxiliary node at the center of that arc. RADTOL provides a relative tolerance for checking this.
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Sec. 8.1 Element groups
CMASS [MASTER CMASS] Requests the calculation of the following mass properties for the element group: total mass, total volume, moments and products of inertia, centroid, and center of mass.{YES/NO} RUPTURE [ADINA] Indicates whether the program rupture criteria or user-supplied rupture criteria to be applied to the material used in this element group. ADINA
Use the program criteria.
USER
User must provide fortran-coded subroutine CURUP8 to decide the element rupture.
Note:
Material models available for this option are: PLASTIC-BILINEAR, PLASTIC-MULTILINEAR, THERMO-PLASTIC, CREEP, PLASTIC-CREEP, MULTILINEAR-PLASTIC-CREEP
TIME-OFFSET [0.0] With this parameter, a creep law can be modified as follows (example given for creep law number 1) :
e c = a 0 ⋅ σ a1 ⋅ ( t − t 0 )
a2
where t is the absolute time and t0=TIME-OFFSET represents a shift in the time scale. Note:
When TIME-OFFSET is used, the same shift is applied to all time dependent terms. The TIME-OFFSET value can be negative or positive and can be modified for a restart run.
OPTION This parameter is obsolete.
[NONE]
BOLT-TOL This parameter is obsolete.
[0.01]
SECTION Specifies the default cross-section label for elements in the group.
[1]
PRINT [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the PRINTDEFAULT parameter of the PRINTOUT command. {DEFAULT/NO/YES} SAVE [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the SAVEDEFAULT ADINA R & D, Inc.
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parameter of the PORTHOLE command. {DEFAULT/NO/YES} TBIRTH Default element birth time.
[0.0]
TDEATH Default element birth time.
[0.0]
BOLTFORCE Specify default bolt force for each element.
[0.0]
BOLTNCUR Specify time function for bolt element.
[0]
TMC-MATERIAL Label number of ADINA-T material used for thermal coupling.
[1]
Auxiliary commands LIST EGROUP PIPE DELETE EGROUP PIPE
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EGROUP SPRING
EGROUP SPRING
Sec. 8.1 Element groups
NAME PROPERTYSET RESULTS NONLINEAR SKEWSYSTEM BOLT OPTION PRINT SAVE TBIRTH TDEATH
Defines an element group consisting of spring elements. NAME [(current highest element group label number) + 1] Label number of the element group to be defined. The label number of an existing element group can be given only if it is of type SPRING. Hence, to re-define the type of a named element group, you must first delete that group using DELETE EGROUP SPRING. PROPERTYSET [1] The label number of the default property set (giving the stiffness, mass, damping properties) for the element group, defined via command PROPERTYSET. Elements within the group may use a different property set, as specified, e.g., by SPRING-POINTS. RESULTS The calculated element response from the ADINA analysis.
[FORCES]
FORCES
Element nodal forces are calculated. The reference system is that of the degree-of-freedom system associated with the node (global or skew).
STRESSES
Element stresses are calculated using the specified stress transformation (see command PROPERTYSET).
NONLINEAR [NO] Specifies whether springs in this group has nonlinear effects. {NO/MNO/GEOM/MNO-G} NO
Spring is linear
MNO
Spring properties may be nonlinear but geometric nonlinearities are not taken into account
GEOM
Spring properties may be nonlinear and geometric nonlinearities are taken into account
MNO-G
Spring with general nonlinear spring properties, with option of using skewsystem at the spring nodes
SKEWSYSTEM [NO] Skewsystem usage, only applicable to springs with option NONLINEAR = NO or MNO-G.
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NO
All property sets are assumed to be with respect to the global Cartesian system. ADINA performs all necessary transformations for any skewsystems at spring element nodes.
YES
Property sets are assumed to be with respect to the coordinate systems at the element nodes. Thus, in this case, ADINA does not perform any transformation between global and skew system.
BOLT This parameter is now obsolete. It is replaced by the parameter OPTION.
[NO]
OPTION [NONE] Specifies special options for springs in this group. {NONE/TIED/TRANSVERSE} NONE
No special options
TIED
Springs used to tie closely spaced shell surfaces
TRANSVERSE
Spring may act in the transverse direction (instead of axial). Only applicable when NONLINEAR=MNO
PRINT [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the PRINTDEFAULT parameter of the PRINTOUT command. {DEFAULT/NO/YES} SAVE [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the SAVEDEFAULT parameter of the PORTHOLE command. {DEFAULT/NO/YES} TBIRTH Default element birth time.
[0.0]
TDEATH Default element birth time.
[0.0]
Auxiliary commands LIST EGROUP SPRING DELETE EGROUP SPRING
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EGROUP GENERAL
EGROUP GENERAL
Sec. 8.1 Element groups
NAME MATRIXSET RESULTS SKEWSYSTEMS USER-SUPPLIED PRINT SAVE
Defines an element group consisting of linear general elements. NAME [(current highest element group label number) + 1] Label number of the element group to be defined. The label number of an existing element group can only be given if it is of type GENERAL. Hence to re-define the type of a named element group, you must first delete that group using DELETE EGROUP GENERAL. MATRIXSET [1] The label number of the default matrix set giving element stiffness, mass, damping and stress matrices for an element group, defined via command MATRIXSET. Elements within the group may use a different matrix set, as specified by element data commands. RESULTS The calculated element response from the ADINA analysis.
[STRESSES]
FORCES
Element nodal forces are calculated, but stresses are not. These forces are equivalent, in the virtual work sense, to the internal element stresses. The reference system is that of the degree-offreedom system associated with the node (global or skew).
STRESSES
Element stresses and strains are calculated at all integration points, but forces are not calculated.
SKEWSYSTEM
[NO]
NO
All matrix sets are assumed to be with respect to the global Cartesian system. ADINA performs all necessary transformations for any skewsystems at general element nodes.
YES
Matrix sets are assumed to be with respect to the coordinate systems at the element nodes. Thus, in this case, ADINA does not perform any transformation between global and skewsystems.
USER-SUPPLIED [NO] If USER-SUPPLIED=YES, then use the MATRIX USER-SUPPLIED command to input the required information, which will be used in the ADINA subroutine CUSERG for calculating the element stiffness, mass and damping matrices, and nodal forces. Note that if the stiffness, mass or damping matrices are constants, then they can instead be provided by the MATRIX STIFFNESS, MATRIX MASS or MATRIX DAMPING commands, respectively. If the MATRIX STIFFNESS command is used, then obviously USER-SUPPLIED=NO. Only one
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matrix set (specified by MATRIXSET) is allowed when USER-SUPPLIED=YES. NO
Element stiffness is directly input through the commands MATRIX STIFFNESS and MATRIXSET.
YES
Element stiffness is to be provided by the user from ADINA subroutine CUSERG, and the element nodal forces is to be calculated too. The command MATRIX USER-SUPPLIED must be input and the MATRIXSET command is used to combine the stiffness, mass and damping effects.
PRINT [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the PRINTDEFAULT parameter of the PRINTOUT command. {DEFAULT/NO/YES} SAVE [DEFAULT] Print element result flag. The DEFAULT value takes the setting from the SAVEDEFAULT parameter of the PORTHOLE command. {DEFAULT/NO/YES} Auxiliary commands LIST EGROUP GENERAL DELETEEGROUPGENERAL
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EGROUP FLUID2
EGROUP FLUID2
Sec. 8.1 Element groups
NAME SUBTYPE DISPLACEMENTS IPO MATERIAL INT RESULTS DEGEN FORMULATION CMASS
Defines an element group consisting of 2-D planar or axisymmetric fluid elements. NAME [(current highest element group label number) + 1] Label number of the element group to be defined. The label number of an existing element group can only be given if it is of type FLUID2. Hence to re-define the type of a named element group, you must first delete that group using DELETE EGROUP FLUID2. SUBTYPE Indicates the type of FLUID2 element.
[AXISYMMETRIC]
AXISYMMETRIC
Axisymmetric elements (which cannot be used in a cyclic symmetric analysis).
PLANE
2-D Planar elements.
DISPLACEMENTS [DEFAULT] Indicates whether large displacements are assumed for the kinematic formulation for the element group. Only applicable for FORMULATION = 0 or 1. SMALL
Small displacements only.
LARGE
Effects of large displacements are included.
DEFAULT
Formulation for element group defaults to that specified by KINEMATICS.
IPO [0] Each fluid region may required one point at which a hydrostatic pressure degree of freedom is specified. See the Theory and Modeling Guide. If required, IPO specifies the appropriate geometry point. IPO = 0 indicates no such requirement. MATERIAL [1] The label number of the default material for an element group. Elements within the group may use a different material, as specified by element data commands, but each material specified must be of the same model type as that of the material given by this parameter. Note:
Elements of type FLUID2 can only use a material of the type: FLUID.
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EGROUP FLUID2
INT Numerical integration order. {1 ≤ INT ≤ 4} DEFAULT
[DEFAULT]
Full Gauss integration order, the reliable integration order, dependent on the polynomial order of the elements, i.e., the number of nodes per element side.
RESULTS The calculated element response from the ADINA analysis.
[PRESSURES]
FORCES
Element nodal forces are calculated, but pressures are not. These forces are equivalent, in the virtual work sense, to the internal element pressures. The reference system is that of the degree-offreedom system associated with the node (global or skew).
PRESSURES
Element pressures are calculated at all integration points, but forces are not.
Note:
RESULTS=FORCES can not be applied to the potential based fluids.
DEGEN [DEFAULT] Indicator for spatial isotropy correction for degenerate (triangular) 8-node elements. When true tetrahedral elements are defined in this element group, DEGEN = UNUSED should be specified. The DEFAULT option means that the default is taken from the parameter DEGEN of the MASTER command. {DEFAULT/NO/YES/UNUSED} FORMULATION Indicates which fluid element to use: 0 1 2 3 4
[DEFAULT]
Displacement-based element without rotation penalty. Displacement-based element with rotation penalty. Potential-based element, acoustic formulation. Potential-based infinite element Potential-based element, subsonic formulation
Notes on the formulations: The potential-based formulations can only be used in conjunction with small displacements (DISPLACEMENTS=SMALL). Formulation 3 is obsolete and is maintained only for backwards compatibility with ADINA 7.5 and lower.
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Sec. 8.1 Element groups
Formulation 4 is allowed only when MASTER FLUIDPOTENTIAL=AUTOMATIC. DEFAULT
= 2 = 1
(cyclic symmetric analysis)
CMASS [MASTER CMASS] Requires the calculation of the following mass properties for the element group: total mass, total volume, moments and products of inertia, centroid, and center of mass. {YES/NO} Auxiliary commands LIST EGROUP FLUID2 DELETE EGROUP FLUID2
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EGROUP FLUID3
EGROUP FLUID3
NAME DISPLACEMENTS IPO MATERIAL RSINT TINT RESULTS DEGEN FORMULATION CMASS
Defines an element group consisting of three-dimensional fluid elements. NAME [(current highest element group label number) + 1] Label number of the element group to be defined. The label number of an existing element group can only be given if it is of type FLUID3. Hence, to re-define the type of a named element group, you must first delete that group using DELETE EGROUP FLUID3. DISPLACEMENTS [DEFAULT] Indicates whether large displacements are assumed for the kinematic formulation for the element group. Only applicable for FORMULATION = 0 or 1. SMALL
Small displacements only.
LARGE
Effects of large displacements are included.
DEFAULT
Formulation for element group defaults to that specified by KINEMATICS.
IPO [0] Each fluid region may required one point at which a hydrostatic pressure degree of freedom is specified. See the Theory and Modeling Guide. If required, IPO specifies the appropriate geometry point. IPO = 0 indicates no such requirement. MATERIAL [1] The label number of the default material for an element group. Elements within the group may use a different material, as specified by element data commands, but each material specified must be of the same model type as that of the material given by this parameter. Note:
Elements of type FLUID3 can only use a material of type: FLUID.
RSINT Numerical integration order for the element r-, s-directions. {1 ≤ INT ≤ 6} DEFAULT
[DEFAULT]
Full Gauss integration order, the reliable integration order, dependent on the polynomial order of the elements, i.e. the number of nodes per element side.
TINT [DEFAULT] Numerical integration order in the element t-direction. Same input convention as RSINT.
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Sec. 8.1 Element groups
RESULTS The calculated element response from the ADINA analysis.
[PRESSURES]
FORCES
Element nodal forces are calculated, but pressures are not. These forces are equivalent, in the virtual work sense, to the internal element pressures. The reference system is that of the degree-offreedom system associated with the node (global or skew).
PRESSURES
Element pressures are calculated at all integration points, but forces are not.The calculated element response from the ADINA analysis.
Note:
RESULTS=FORCES can not be applied to the potential based fluids.
DEGEN [DEFAULT] Indicator for spatial isotropy correction for degenerate 20-node elements. When true 10-node tetrahedral elements are defined in this element group through ENODES command, DEGEN = UNUSED should be specified. The DEFAULT option means that the default is taken from the parameter DEGEN of the MASTER command. {DEFAULT/NO/ YES/UNUSED} FORMULATION Indicates which fluid element to use: 0 1 2 3 4
[DEFAULT]
Displacement-based element without rotation penalty. Displacement-based element with rotation penalty. Potential-based element, acoustic formulation. Potential-based infinite element Potential-based element, subsonic formulation
Notes on the formulations: The potential-based formulations can only be used in conjunction with small displacements (DISPLACEMENTS=SMALL). Formulation 3 is obsolete and is maintained only for backwards compatibility with ADINA 7.5 and lower. Formulation 4 is allowed only when MASTER FLUIDPOTENTIAL=AUTOMATIC. DEFAULT
= 2 = 1
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Chap. 8 Finite element representation
EGROUP FLUID3
CMASS [MASTER CMASS] Requests the calculation of the following mass properties for the element group; total mass, total volume, moments and products of inertia, centroid, and center of mass. {YES/NO} Auxiliary commands LIST EGROUP FLUID3 DELETE EGROUP FLUID3
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EGCONTROL
EGCONTROL
Sec. 8.1 Element groups
MAXELG
EGCONTROL specifies general control data for element groups. MAXELG [9999] Maximum number of elements in a single element subgroup. If the number of elements in a group is greater than MAXELG it will be split into subgroups such that each subgroup has MAXELG or fewer elements. This parameter has no effect if PPROCESS NPROC is greater than 1, for which element group splitting is handled independently of MAXELG. Auxiliary commands LIST EGCONTROL
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BOLT-OPTIONS
BOLT-OPTIONS
TYPE TABLES STEPS TIME TOLERANCE DAMPING
Defines bolt options for use with the EGROUP BEAM command. TYPE Specifies the type of bolt. {FORCE/LENGTH} FORCE
Force-tensioning bolt
LENGTH
Length-reducing bolt
[FORCE]
TYPE can be overwritten by the BOLT-TABLE command. TABLES [NO] Indicates whether bolt tables (BOLT-TABLE command) are used to specify the bolt loading sequence. If TABLES=YES, at least one BOLT-TABLE command must be specified in the model. {NO/YES} STEPS [1] Specifies number of bolt steps used to apply the full bolt load. Not used if TABLES=YES is specified. TIME Specifies bolt time. Not used if TABLES=YES is specified.
[0]
TOLERANCE [0.01] Specifies the default bolt convergence tolerance. A different tolerance value may be specified for a group of bolts with the BOLT-TOL parameter in EGROUP BEAM command. DAMPING Specifies bolt damping.
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Sec. 8.1 Element groups
BOLT-TABLE
BOLT-TABLE
NAME TYPE TIME
sequencei bolt-numberi factori savei Specifies the bolt loading sequence. NAME Bolt-table label number.
[current highest label + 1]
TYPE Specifies the type of bolt. {FORCE/LENGTH} FORCE
Force-tensioning bolt
LENGTH
Length-reducing bolt
[FORCE]
The specification of TYPE in this command overwrites any from the BOLT-OPTIONS command. TIME Specifies bolt time.
[0]
sequencei Bolt sequence number. bolt-numberi Bolt number assigned in the EGROUP BEAM command. Note that if bolt-number=0, it means all bolts are loaded in same sequence. factori Bolt factor. savei [DEFAULT] Save flag. {DEFAULT/NO/YES} When the setting is DEFAULT, the save flag is NO, except for last bolt in the table, for which the save flag = YES. Note that the same sequence with different bolt numbers must have the same save flag. If multiple entries have the same sequence and the same bolt number, only the last one will be taken. Sequence numbers must start at number 1 and have no gaps. Bolt time must be different for each bolt-table. The same sequence must have the same save flags.
Converts a set of shell elements along an edge of a face/surface into shell transition elements. BODY1 Label number of the body of FACE1 that has a shell mesh.
[0]
FACE1 Label number of the face on BODY1. If BODY1 is 0, FACE1 is a surface label number.
[1]
EDGE Label number of the edge where the shell transition elements are to be created. If BODY1 is 0, EDGE is a line label number. GROUP1 [Highest shell element group number of mesh on FACE1] Element group number of the shell mesh on FACE1. BODY2 Label number of the body that has a 3-D solid mesh.
[0]
FACE2 [1] Label number of face on BODY2 where the shell transition elements are to be created. If BODY2 is 0, FACE2 is a surface label number. GROUP2
[Highest 3-D solid element group number of mesh on BODY2] Element group number of the 3-D solid mesh on BODY2. SUBSTRUCTURE [Currently active substructure] Substructure number for the nodes created by this command.
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BLAYER
BLAYER
Sec. 8.2 Mesh generation
SUBSTRUC GROUP GEOM
bodyi facei edgei ptypei thick0i nlayeri thickti Command BLAYER generates boundary layers on specified body faces for the specified (substructure, group). In 3D, boundary layers are grown normal to body faces. In 2D, boundary layers are grown normal to body edges along body faces. Notes for 3D models: 1 2 3 4 5 6 7
BLAYER is active only if: number of bodies > 0 and number of volumes = 0 and all bodies have been meshed. BLAYER executes only if number of nodes per element is 4. In case of multiple bodies, "interface" body faces must be linked. Linked body faces cannot have boundary layers on both sides. Once boundary layers have been generated and in case of multiple bodies, do not delete body meshes unless you intend to delete all of them. There can be only one element group. As a rule of thumb, the total thickness should be less than the element size on the body face.
Notes for 2D models: 1 2 3 4 5 6 7
BLAYER is active only if number of body faces > 0 and number of surfaces = 0 and all body faces have been meshed. BLAYER executes only if number of nodes per element is 3. In case of multiple bodies, "interface" body edges must have same nodes. Interface body edges cannot have boundary layers on both sides. Once boundary layers have been generated and in case of multiple bodies, do not delete body meshes unless you intend to delete all of them. There can be only one element group. As a rule of thumb, the total thickness should be less than the element size on the body edge.
SUBSTRUC Element substructure. GROUP Element group.
[current substructure label number] [current group label number]
GEOM [YES] Option to use the geometric modeler for placement of nodes on body faces/edges. {YES/ NO}
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BLAYER
YES
The geometric modeler (parasolid) is used to place nodes on body faces/edges.
NO
The mesh is used to place nodes on body faces/edges.
bodyi Label number of the body. facei Label number of the face. edgei Label number of the edge. In 3D, this is a dummy argument. ptypei Progression type for boundary layers. {GEOMETRIC/ARITHMETIC} thick0i Thickness of first layer (off face). nlayeri Number of layers. thickti Total thickness.
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Copies face triangulation which can be later be used by meshing commands like GFACE or GBODY. Enables the creation of identical meshes on similar faces. BODY1 Label number of body where the face triangulation(s) is to be copied from. {> 0}
[NONE]
FACE1 [0] Label number of face on BODY1 where the triangulation is to be copied from. See notes below if FACE1=0. {≥ 0} BODY2 Label number of body where the face triangulation(s) is to be copied to. {> 0}
[NONE]
FACE2 [0] Label number of face on BODY2 where the triangulation is to be copied from. See notes below if FACE2=0. {≥ 0} TRANSFORMATION Label number of the transformation from BODY1 (FACE1) to BODY2 (FACE2).
[0]
PCTOLERANCE [as set in TOLERANCES GEOMETRIC] Relative tolerance to be used to check if faces are matched using the provided transformation. Notes: If FACE1>0 and FACE2>0, it is assumed FACE1 transforms into FACE2 and the triangulation stored internally for FACE1 is copied onto FACE2 if they match. If FACE1=0 and FACE2=0, any face of BODY1 is checked against any face of BODY2 for a match using the provided transformation. The face triangulations are copied for all matching faces.
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DELETE-TRIANGULATION
DELETE-TRIANGULATION OPTION BODY FACE Deletes face triangulations created by the COPY-TRIANGULATION command. OPTION [ALL] Indicates whether triangulation is deleted for all relevant faces on all bodies or for selected faces on a body. {ALL/SELECT} BODY Body label where triangulation is to be deleted. {>0} FACE [0] Face label where triangulation is to be deleted. If FACE=0, then triangulation on all relevant faces of BODY will be deleted. {≥0}
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LIST-TRIANGULATION
Sec. 8.2 Mesh generation
LIST-TRIANGULATION Lists all faces (body and face labels) which have triangulation created by the COPY-TRIANGULATION command.
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SUBDIVIDE DEFAULT
SUBDIVIDE DEFAULT
MODE PROGRESSION SIZE NDIV PSIZE MINCUR
Defines default mesh subdivision data for subsequent model geometry definitions. Model geometry created or imported will initially have the subdivision data given by this command. Note that this command does not update any current geometry subdivision data, it only specifies defaults for subsequent geometry definitions. SUBDIVIDE DEFAULT has a similar syntax, but quite distinct action, to SUBDIVIDE MODEL, which assigns a given subdivision data to all currently defined geometry. MODE Selects the method of model subdivision data specification.
[NONE]
NONE
no default mode. Subdivision mode will depend on the SUBDIVIDE commands for each individual geometry type
LENGTH
An element size is input corresponding to the length of an element edge.
DIVISIONS
A geometry line or edge is assigned a number of equal subdivisions.
POINTWISE
A geometry line or edge is subdivided according to the desired element size at its end-points.
PROGRESSION [GEOMETRIC] Sets the method of element edge length distribution along a line or edge of the geometry model. ARITHMETIC
The difference in length of each element edge from its adjacent edges is constant.
GEOMETRIC
The ratio of lengths of adjacent element edges is constant.
APPROXIMATE
The distribution of edge lengths is made such that a given ratio of end-lengths is only approximately satisfied.
Note:
PROGRESSION = APPROXIMATE is only provided for compatibility with earlier versions of ADINA-IN. It is recommended that ARITHMETIC or GEOMETRIC normally be used.
SIZE [0.0] If MODE=LENGTH, this parameter specifies the element edge length. Then SIZE=0.0 means
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SUBDIVIDE DEFAULT
Sec. 8.2 Mesh generation
that the element edge length is the length of the edge (i.e. every edge will have 1 subdivsion). If MODE=POINTWISE, this parameter specifies the maximum element edge length. NDIV Number of subdivisions assigned to a geometry line/edge. PSIZE Element size at geometry points. MINCUR Minimum number of subdivisions for curved lines and edges used when MODE=POINTWISE.
[1] [0.0] [1]
Auxiliary commands LIST SUBDIVIDE DEFAULT Lists the current default subdivision data.
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SUBDIVIDE MODEL
SUBDIVIDE MODEL
MODE SIZE NDIV PROGRESSION MINCUR
Assigns mesh subdivision data to the entire current model geometry. The data can be in the form of a specified element size, or the number of subdivisions along each line. MODE Selects the method of model subdivision data specification.
[POINTWISE]
LENGTH
An element size is input corresponding to the length of an element edge.
DIVISIONS
Each model geometry line or edge is assigned the same number of equal subdivisions.
POINTWISE
Each model geometry line or edge is subdivided according to the element size at its end-points.
SIZE [0.0] If MODE=LENGTH, this parameter specifies the element edge length. Then SIZE=0.0 means that the element edge length is the length of the edge (i.e. every edge will have 1 subdivsion). If MODE=POINTWISE, this parameter specifies the maximum element edge length. NDIV Number of subdivisions assigned to each geometry line or edge.
[1]
PROGRESSION [GEOMETRIC] Sets the method of element edge length distribution along each line or edge of the geometry model . ARITHMETIC The difference in length of each element edge from its adjacent edges is constant. GEOMETRIC
The ratio of lengths of adjacent element edges is constant.
APPROXIMATE
The distribution of edge lengths is made such that a given ratio of end-lengths is only approximately satisfied.
Note:
PROGRESSION = APPROXIMATE is only provided for compatibility with earlier versions of ADINA-IN. It is recommended that ARITHMETIC or GEOMETRIC normally be used.
MINCUR Minimum number of subdivisions for curved lines and edges used when MODE = POINTWISE.
[1]
Auxiliary commands LIST SUBDIVIDE MODEL
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SUBDIVIDE POINT
SUBDIVIDE POINT
Sec. 8.2 Mesh generation
NAME SIZE
pointi Assigns mesh subdivision data (element sizes) to a set of geometry points. NAME Label number of a geometry point. Other points may be specified in subsequent accompanying data lines. SIZE Requested element size. The size of an element is defined to be the maximum length of an edge of that element. {≥ 0.0} Note:
The element size at a geometry point may be used to determine the subdivision data of geometry entities: lines and edges, and thereby that of surfaces, volumes, faces and bodies.
pointi Label number of a geometry point. Note:
A zero element size at a point indicates that any line or edge for which the point is a vertex (end-point) will have only a single element edge if the mode of that line/ edge is POINTWISE.
Auxiliary commands LIST SUBDIVIDE POINT
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SUBDIVIDE LINE
SUBDIVIDE LINE
NAME MODE SIZE NDIV RATIO PROGRESSION CBIAS
linei Assigns mesh subdivision data to a set of geometry lines. The data can be in the form of a specified element size, or the number of subdivisions along the line. P1
NAME Label number of a geometry line. Other geometry lines to have the same subdivision data may be given on accompanying data-lines. MODE [DIVISIONS] Selects the method of mesh subdivision data specification. This controls the actual parameters used, other parameters are ignored. DIVISIONS
The geometry lines are assigned a number of subdivisions which can be graded in size according to the selected progression rule (NDIV, RATIO, PROGRESSION).
LENGTH
An element size is input corresponding to the length of an element edge (SIZE).
POINTWISE
The number of subdivisions, and any necessary grading, for the geometry line is calculated from the element size specified at the end points of the geometry line. See SUBDIVIDE POINT, POINT-SIZE (SIZE, PROGRESSION).
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SUBDIVIDE LINE
COMBINED
Sec. 8.2 Mesh generation
For lines of type COMBINED (COUPLED=YES), the subdivision data assigned to the parent lines (which are combined to define the line) are transferred to the combined line, overwriting any existing subdivision for the combined line. This mode guarantees that the ‘junctions’ where parent lines meet is assigned a subdivision location, i.e. a node will be generated at these positions during mesh generation.
SIZE [0.0] If MODE=LENGTH, this parameter specifies the element edge length. Then SIZE=0.0 means that the element edge length is the length of the edge (i.e. every edge will have 1 subdivsion). If MODE=POINTWISE, this parameter specifies the maximum element edge length. NDIV Number of subdivisions assigned to the geometry lines.
[1]
RATIO [1.0] Ratio of lengths of the last to the first element edges along the geometry line. The grading of element lengths is governed by PROGRESSION. “Last” refers to the end of the line corresponding to parametric coordinate u = 1.0, whilst “first” refers to the end of the line corresponding to parametric coordinate u = 0.0. PROGRESSION [GEOMETRIC] When element edges are to be graded along a geometry line, i.e., when RATIO ≠ 1.0, the distribution of element edge lengths can be selected from: ARITHMETIC
The difference in length of each element edge from its adjacent edges is constant.
GEOMETRIC
The ratio of lengths of adjacent element edges is constant.
APPROXIMATE
The distribution of edge lengths is made such that RATIO is only approximately satisfied.
Note:
PROGRESSION = APPROXIMATE is only provided for compatibility with earlier versions of ADINA-IN. It is recommended that ARITHMETIC or GEOMETRIC normally be used.
CBIAS Indicates if central bias is used. {NO/YES}
[NO]
linei Label number of a geometry line.
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SUBDIVIDE LINE
Auxiliary commands LIST SUBDIVIDE LINE
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SUBDIVIDE SURFACE
Sec. 8.2 Mesh generation
SUBDIVIDE SURFACE
NAME MODE SIZE NDIV1 NDIV2 RATIO1 RATIO2 PROGRESSION CBIAS1 CBIAS2
surfacei Assigns mesh subdivision data to a set of geometry surfaces. The data can be in the form of a specified element size, or the number of divisions along the edges of the geometry surface. The subdivision data is actually assigned to the geometry lines which comprise the edges of the geometry surfaces. P2 P1
v P3
NDIV2, RATIO2 u NDIV1, RATIO1
P4
NAME Label number of a geometry surface. Other geometry surfaces to have the same subdivision data may be given on accompanying data-lines. MODE [DIVISIONS] Selects the method of mesh subdivision data specification. This controls the actual parameters used, other parameters are ignored. LENGTH
An element size is input corresponding to the length of an element edge. Each edge of the geometry surfaces is subdivided separately so as to give element edges which are approximately of length SIZE (SIZE).
DIVISIONS
Each parametric direction of the geometry surfaces is assigned a number of subdivisions which can be graded in size according to the selected progression rule (NDIV1, NDIV2, RATIO1, RATIO2, PROGRESSION).
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POINTWISE
SUBDIVIDE SURFACE
Each edge of the geometry surfaces is assigned a number of sub-divisions which is calculated, along with any necessary grading, from the element size specified at the end points of the edge. See SUBDIVIDE POINT, POINT-SIZE (SIZE, PROGRES SION).
SIZE [0.0] If MODE=LENGTH, this parameter specifies the element edge length. Then SIZE=0.0 means that the element edge length is the length of the edge (i.e. every edge will have 1 subdivsion). If MODE=POINTWISE, this parameter specifies the maximum element edge length. NDIV1 [1] Number of subdivisions assigned to the first parametric direction, u, of the geometry surfaces. NDIV2 [1] Number of subdivisions assigned to the second parametric direction, v, of the geometry surfaces RATIO1 [1.0] Ratio of lengths of the last to the first element edges along the edges corresponding to the first parametric direction, u, of the geometry surfaces. The grading of element edge lengths is governed by PROGRESSION. RATIO2 [1.0] Ratio of lengths of the last to the first element edges along the edges corresponding to the second parametric direction, v, of the geometry surfaces. The grading of element edge lengths is governed by PROGRESSION. PROGRESSION [GEOMETRIC] When element edges are to be graded, the distribution of element edge lengths can be selected from: ARITHMETIC
The difference in length of each element edge from its adjacent edges is constant.
GEOMETRIC
The ratio of lengths of adjacent element edges is constant.
APPROXIMATE
The distribution of edge lengths is made such that RATIO is only approximately satisfied.
Note:
CBIAS1
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SUBDIVIDE SURFACE
Sec. 8.2 Mesh generation
Indicates if central bias is used along the parametric u direction. {NO/YES} CBIAS2 Indicates if central bias is used along the parametric v direction. {NO/YES}
[NO]
surfacei Label number of a geometry surface. Auxiliary commands LIST SUBDIVIDE SURFACE
volumei Assigns mesh subdivision data to a set of geometry volumes. The data can be in the form of a specified element size, or the number of divisions along the edges of the geometry volume. The subdivision data is actually assigned to the geometry lines which comprise the edges of the geometry volumes.
P2
NDIV1, RATIO1 P1
NDIV2, RATIO2 v P3
NDIV3, RATIO3
P4 u
P5
P6 w
P7
P8
NAME Label number of a geometry volume. Other volumes to have the same subdivision data may be given on accompanying data-lines. MODE [DIVISIONS] Selects the method of mesh subdivision data specification. This controls the actual parameters used, other parameters are ignored. LENGTH
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SUBDIVIDE VOLUME
Sec. 8.2 Mesh generation
DIVISIONS
Each parametric direction of the geometry volumes is assigned a number of subdivisions, which can be graded in size according to the selected progression rule (NDIV1, NDIV2, NDIV3, RATIO1, RATIO2, RATIO3, PROGRESSION).
POINTWISE
Each edge of the geometry volumes is assigned a number of subdivisions, which is calculated, along with any necessary grading, from the element size specified at the end points of the edge. See SUBDIVIDE POINT, POINT-SIZE (SIZE, PROGRESSION).
SIZE [0.0] If MODE=LENGTH, this parameter specifies the element edge length. Then SIZE=0.0 means that the element edge length is the length of the edge (i.e. every edge will have 1 subdivsion). If MODE=POINTWISE, this parameter specifies the maximum element edge length. NDIV1 [1] Number of subdivisions assigned to the first parametric direction, u, of the geometry volumes. NDIV2 [1] Number of subdivisions assigned to the second parametric direction, v, of the geometry volumes. NDIV3 Number of subdivisions assigned to the third parametric direction, w, of the geometry volumes.
[1]
RATIO1 [1.0] Ratio of lengths of the last to the first element edges along the edges corresponding to the first parametric direction, u, of the geometry volumes. The grading of element edge lengths is governed by PROGRESSION. RATIO2 [1.0] Ratio of lengths of the last to the first element edges along the edges corresponding to the second parametric direction, v, of the geometry volumes. The grading of element edge lengths is governed by PROGRESSION. RATIO3 [1.0] Ratio of lengths of the last to the first element edges along the edges corresponding to the third parametric direction, w, of the geometry volumes. The grading of element edge lengths is governed by PROGRESSION.
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SUBDIVIDE VOLUME
PROGRESSION [GEOMETRIC] When element edges are to be graded the distribution of element edge lengths can be selected from: ARITHMETIC
The difference in length of each element edge from its adjacent edges is constant.
GEOMETRIC
The ratio of lengths of adjacent element edges is constant.
APPROXIMATE
The distribution of edge lengths is made such that the ratio of first to last edge lengths (RATIO1, RATIO2, or RATIO3) is only approximately satisfied.
Note:
PROGRESSION = APPROXIMATE is only provided for compatibility with earlier versions of ADINA-IN. It is recommended that ARITHMETIC or GEOMETRIC normally be used.
CBIAS1 Indicates if central bias is used along the parametric u direction. {NO/YES}
[NO]
CBIAS2 Indicates if central bias is used along the parametric v direction. {NO/YES}
[NO]
CBIAS3 Indicates if central bias is used along the parametric w direction. {NO/YES}
[NO]
volumei Label number of a geometry volume. Auxiliary commands LIST SUBDIVIDE VOLUME
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SUBDIVIDE EDGE
SUBDIVIDE EDGE
Sec. 8.2 Mesh generation
NAME BODY MODE SIZE NDIV RATIO PROGRESSION
edgei Assigns mesh subdivision data to edges of a solid geometry body. The data can be in the form of a specified element size, or the number of subdivisions along the edge. NAME Label number of a geometry edge of BODY. Other edges (of BODY) to have the same subdivision data may be given in accompanying data-lines. BODY Label number of the solid geometry body.
[currently active body]
MODE [LENGTH] Selects the method of mesh subdivision data specification. This controls the actual parameters used, other parameters are ignored. DIVISIONS
The geometry edge is assigned a number of subdivisions, which can be graded in size according to the selected progression rule (NDIV, RATIO, PROGRESSION).
LENGTH
An element size is input corresponding to the length of an element edge (SIZE). The number of subdivisions, and any necessary grading, for the geometry edges is calculated from the element size specified at the end points of the geometry edge. See SUBDIVIDE POINT, POINT-SIZE (SIZE, PROGRESSION).
POINTWISE
SIZE [0.0] If MODE=LENGTH, this parameter specifies the element edge length. Then SIZE=0.0 means that the element edge length is the length of the edge (i.e. every edge will have 1 subdivsion). If MODE=POINTWISE, this parameter specifies the maximum element edge length. NDIV Number of subdivisions assigned to a geometry edges.
[1]
RATIO [1.0] Ratio of lengths of the last to the first element edges along the geometry edges. The grading of element lengths is governed by PROGRESSION.
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SUBDIVIDE EDGE
PROGRESSION [GEOMETRIC] When element edges are to be graded along the geometry edges (i.e., when RATIO ≠ 1.0), then the distribution of element edge lengths can be selected from the following. ARITHMETIC
The difference in length of each element edge from its adjacent edges is constant.
GEOMETRIC
The ratio of lengths of adjacent element edges is constant.
edgei Label number of a geometry edge (of BODY). Auxiliary commands LIST SUBDIVIDE EDGE
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SUBDIVIDE FACE
SUBDIVIDE FACE
Sec. 8.2 Mesh generation
NAME BODY MODE SIZE NDIV PROGRESSION MAX-SIZE
facei Assigns mesh subdivision data to faces of a solid geometry body. The data can be in the form of a specified element size, or the number of divisions along the edges of the geometry faces. NAME Label number of the geometry face (of BODY). Other faces (of BODY) to have the same subdivision data may be given on accompanying data lines. BODY Label number of the solid geometry body.
[currently active body]
MODE [LENGTH] Selects the method of mesh subdivision data specification. This controls the actual parameters used, other parameters are ignored. DIVISIONS
The edges of the geometry faces are assigned a number of subdivisions (NDIV).
LENGTH
An element size is input corresponding to the length of an element face. Each edge of the geometry face is subdivided separately so as to give element edges approximately the length of SIZE (SIZE).
POINTWISE
The number of subdivisions, and any necessary grading, for the edges of geometry faces calculated from the element size specified at the end points of the geometry edges. See SUBDIVIDE POINT, POINT-SIZE (SIZE, PROGRESSION).
SIZE [0.0] If MODE=LENGTH, this parameter specifies the element edge length. Then SIZE=0.0 means that the element edge length is the length of the edge (i.e. every edge will have 1 subdivsion). If MODE=POINTWISE, this parameter specifies the maximum element edge length. NDIV Number of subdivisions assigned to the edges of the geometry faces.
[1]
PROGRESSION [GEOMETRIC] When element edges are to be graded, the distribution of element edge lengths can be
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SUBDIVIDE FACE
selected from the following: ARITHMETIC
The difference in length of each element edge from its adjacent edges is constant.
GEOMETRIC
The ratio of lengths of adjacent element edges is constant.
MAX-SIZE [0.0] If set to a value greater than 0.0, free-form meshing will be allowed to create elements greater in size than the max size on the face’s boundary. Free-form meshing will however not be allowed to create elements with a size greater than MAX-SIZE. Relevant only with MESHING=FREE-FORM and METHOD=DELAUNAY in the GFACE command. {≥ 0.0} facei Label number of a geometry face (of BODY). Auxiliary commands LIST SUBDIVIDE FACE
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SUBDIVIDE BODY
SUBDIVIDE BODY
Sec. 8.2 Mesh generation
NAME MODE SIZE NDIV PROGRESSION MAX-SIZE
bodyi Assigns mesh subdivision data to a set of solid geometry bodies. The data can be in the form of a specified element size or the number of divisions along the edges of the geometry bodies. The subdivision data is assigned to the edges of the geometry bodies. NAME Label number of a solid geometry body. Other geometry bodies to have the same subdivision data may be given in accompanying data lines. MODE [LENGTH] Selects the method of mesh subdivision data specification. This controls the actual parameters used, other parameters are ignored. DIVISIONS
Each edge of the geometry bodies is assigned a number of subdivisions (NDIV).
LENGTH
An element size is input corresponding to the length of an element edge. Each edge of the geometry bodies is subdivided separately so as to give element edges which are approximately of length SIZE (SIZE).
POINTWISE
Each edge of the geometry bodies is assigned a number of subdivisions, which are calculated, along with any necessary grading, from the element size specified at the end points of the edge. See SUBDIVIDE POINT, POINT-SIZE (SIZE, PROGRESSION).
SIZE [0.0] If MODE=LENGTH, this parameter specifies the element edge length. Then SIZE=0.0 means that the element edge length is the length of the edge (i.e. every edge will have 1 subdivsion). If MODE=POINTWISE, this parameter specifies the maximum element edge length. NDIV Number of subdivisions assigned to the edges of the geometry bodies.
[1]
PROGRESSION [GEOMETRIC] When element edges are to be graded the distribution of element edge lengths can be selected from the following
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SUBDIVIDE BODY
ARITHMETIC
The difference in length of each element edge from its adjacent edges is constant.
GEOMETRIC
The ratio of lengths of adjacent element edges is constant.
MAX-SIZE [0.0] If set to a value greater than 0.0, free-form meshing will be allowed to create elements greater in size than the max size on the face’s boundary. Free-form meshing will however not be allowed to create elements with a size greater than MAX-SIZE. Relevant only with MESHING=FREE-FORM and METHOD=DELAUNAY in the GBODY command. {≥ 0.0} Note that MAX-SIZE is passed down to the bounding faces. bodyi Label number of a solid geometry body. Auxiliary commands LIST SUBDIVIDE BODY
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POINT-SIZE
Sec. 8.2 Mesh generation
POINT-SIZE
namei
OPTION INPUT SIZE-FUNCTION MAXSIZE MINSIZE BODY sizei
Specifies the mesh-size (element edge length) for a set of geometry points, either directly, or by a size-function, or by evaluation from the lengths of the lines/edges which meet at the points. The set of points can be given by label or by reference to other geometry entities in the model. OPTION Indicates how the mesh-size is to be evaluated:
[DIRECT]
DIRECT
The mesh-size is input in the data lines.
ATTACHED
The lengths of the lines/edges which meet at a point, together with input minimum, maximum values are used to determine the mesh-size at that point.
FUNCTION
A pre-defined size-function is used to calculate the mesh size at a point, dependent on its location.
INPUT Indicates how the set of points is defined:
[POINT]
MODEL
All geometry points.
POINT
The geometry points will be explicitly identified by label number.
LINE
The end-points of a set of geometry lines.
SURFACE
The vertices of a set of geometry surfaces.
VOLUME
The vertices of a set of geometry volumes.
EDGE
The end-points of a set of solid geometry edges.
FACE
The vertices of a set of solid geometry faces.
BODY
The vertices of a set of solid geometry bodies.
SIZE-FUNCTION Label number of a size-function, input when OPTION = FUNCTION. See command SIZE-FUNCTION.
[1]
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POINT-SIZE
MAXSIZE The maximum mesh-size for the input points. This is used in two cases:
[0.0]
OPTION = DIRECT, INPUT = MODEL
The mesh-size at every geometry point in the model will be set to MAXSIZE.
OPTION = ATTACHED
The mesh-size computed from the attached lines/edges will be subject to a maximum value of MAXSIZE.
MINSIZE [0.0] The minimum mesh-size for the input points, used to provide a lower bound on the computed mesh-size when OPTION = ATTACHED. BODY [currently active body] Label number of a solid geometry body. Used when INPUT = EDGE or FACE. namei Entity label number. sizei Mesh-size, (element edge length) for entity namei. (Used when OPTION = DIRECT). Note: If there is any ambiguity in the input, e.g. INPUT = LINE, OPTION = DIRECT with two different mesh-sizes assigned to two lines which meet at a point, the mesh size at the point is taken from the entity (line) with the higher label number.
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SIZE-FUNCTION BOUNDS defines a mesh-size function in terms of a bounding box with faces parallel to the global coordinate planes and the mesh-sizes at the vertices of the box. The mesh-size at any other point is interpolated from this bounding box. A size-function may be used to set point mesh-sizes, via POINT-SIZE, and may also be used directly by the free-form mesh generation commands GFACE, GBODY to control the generated element sizes. In 8.3 and earlier versions, the size of a point outside the bounding box is given by the size of the point’s closest location on the bounding box (that size is interpolated from the sizes at the 8 corners). In version 8.4, inside the bounding box, the size is interpolated from the sizes at the 8 corners (same as version 8.3 and earlier). Outside the bounding box, the size follows a geometric progression (see SIZE-FUNCTION POINT for geometric progression definition) with a fixed factor of 1.4. NAME [(current highest size-function label number) + 1] Label number of the size-function to be defined. XMIN, YMIN, ZMIN [current minimum coordinates of model] Minimum coordinates of the bounding box. XMAX, YMAX, ZMAX [current maximum coordinates of model] Maximum coordinates of the bounding box. SIZE1 Mesh-size (element edge length) at (XMAX,YMAX,ZMAX). SIZE2 Mesh-size (element edge length) at (XMIN,YMAX,ZMAX). SIZE3 Mesh-size (element edge length) at (XMIN,YMIN,ZMAX). SIZE4 Mesh-size (element edge length) at (XMAX,YMIN,ZMAX).
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SIZE-FUNCTION BOUNDS
SIZE5 Mesh-size (element edge length) at (XMAX,YMAX,ZMIN). SIZE6 Mesh-size (element edge length) at (XMIN,YMAX,ZMIN). SIZE7 Mesh-size (element edge length) at (XMIN,YMIN,ZMIN). SIZE8 Mesh-size (element edge length) at (XMAX,YMIN,ZMIN). Auxiliary commands LIST SIZE-FUNCTION DELETE SIZE-FUNCTION
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SIZE-FUNCTION HEX defines a mesh-size function in terms of a bounding hexahedral volume, specified by its vertex coordinates, and the mesh size at those vertices. The meshsize at any other point is interpolated from this bounding box. A size-function may be used to set point mesh-sizes, via POINT-SIZE, and may also be used directly by the free-form mesh generation commands GFACE, GBODY to control the generated element sizes. In 8.3 and earlier versions, the size of a point outside the bounding hexahedral volume is given by the size of the point’s closest location on the bounding hexahedral volume (that size is interpolated from the sizes at the 8 corners). In version 8.4, inside the bounding hexahedral volume, the size is interpolated from the sizes at the 8 corners (same as version 8.3 and earlier). Outside the bounding hexahedral volume, the size follows a geometric progression (see SIZE-FUNCTION POINT for geometric progression definition) with a fixed factor of 1.4. NAME [(current highest size-function label number) + 1] Label number of the size-function to be defined. X1, Y1, Z1 Global Cartesian coordinates of vertex 1 of the bounding hexahedral volume. ... X8, Y8, Z8 Global Cartesian coordinates of vertex 8 of the bounding hexahedral volume. SIZE1 Mesh-size (element edge length) at vertex 1. SIZE2 Mesh-size (element edge length) at vertex 2. SIZE3 Mesh-size (element edge length) at vertex 3. SIZE4
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SIZE-FUNCTION HEX
Mesh-size (element edge length) at vertex 4. SIZE5 Mesh-size (element edge length) at vertex 5. SIZE6 Mesh-size (element edge length) at vertex 6. SIZE7 Mesh-size (element edge length) at vertex 7. SIZE8 Mesh-size (element edge length) at vertex 8. Auxiliary commands LIST SIZE-FUNCTION DELETE SIZE-FUNCTION
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SIZE-FUNCTION POINT
SIZE-FUNCTION POINT
Sec. 8.2 Mesh generation
NAME MODE POINT X Y Z SIZE DISTANCE SCALE TYPE A1 A2 A3 PROGRESS
Defines a mesh-size function of source type where the element size is dependent on the distance from a given location. The size-function may be used to set point mesh-sizes, via command POINT-SIZE, and also may be used directly by the free-form mesh generation commands GFACE, GBODY to control element sizes during the meshing process. NAME [(current highest size-function label) + 1] The identifying label number of the size-function. MODE Indicates how the source location is defined: POINT
The source location is given by a geometry point.
POSITION
The source location is given by a position vector (X,Y,Z).
POINT Label number of a geometry point. X [0.0] Y [0.0] Z [0.0] Global Cartesian system components of the position vector giving the source location. SIZE Constant (minimum) element size. The size function will yield this value within the distance given by parameter DISTANCE from the specified location. Further away, the element size gradually increases as determined by this command. {> 0.0} DISTANCE Distance from location for which the size function is constant, giving element size SIZE. {> SIZE} SCALE Scaling factor for the distance from the source location.
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[1.0]
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SIZE-FUNCTION POINT
TYPE [LINEAR] Indicates the type of growth function for the element size away from the source location. Let d=distance from source location, R = MAX[ 0.0, ((d-DISTANCE)/SCALE)], δ= element size, then the following function types are available:
LINEAR
δ = SIZE × [1.0 + A1 × R ]
QUADRATIC
δ = SIZE × 1.0 + A1 × R + A2 × R 2
POWER
[ ] δ = SIZE × [1.0 + A1 × R + A2 × R + A3 × R ] δ = SIZE × [1.0 + R ]
EXPONENTIAL
δ = SIZE × e ( A1× R )
2
CUBIC
3
A1
[
]
A1 A2 A3 Function coefficients. {≥ 0.0 for TYPE = LINEAR, QUADRATIC, CUBIC}
[0.0] [0.0] [0.0]
PROGRESS [NONE] This option controls the progression of the meshing from the defined point. {NONE/ ARITHMETIC/GEOMETRIC} NONE
TYPE, A1, A2, A3 are used according to the existing description (8.3 and earlier versions).
ARITHMETIC
Only A1 is used. Sizing follows an arithmetic progression, in other words, past the sphere of radius DISTANCE, sizes increase (as the distance to the sphere increases) by a constant value given by A1. Start with size=SIZE, then next size is the previous size+A1.
GEOMETRIC
Only A1 is used. Sizing follows a geometric progression, in other words, past the sphere of radius DISTANCE, sizes increase (as the distance to the sphere increases) by a constant factor given by A1. Start with size=SIZE, then next size is the previous size*A1.
Auxiliary commands LIST SIZE-FUNCTION DELETE SIZE-FUNCTION
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SIZE-FUNCTION AXIS
SIZE-FUNCTION AXIS
Sec. 8.2 Mesh generation
NAME MODE SYSTEM AXIS LINE P1 P2 X0 Y0 Z0 XA YA ZA SIZE DISTANCE SCALE TYPE A1 A2 A3 PROGRESS
Defines a mesh-size function of source type where the element size is dependent on the distance from a given axis (an unbounded straight line). The size-function may be used to set point mesh-sizes, via command POINT-SIZE, and also may be used directly by the free-form mesh generation commands GFACE, GBODY to control element sizes during the meshing process. NAME [(current highest size-function label) + 1] The identifying label number of the size-function. MODE Selects the method of defining the axis. This controls which parameters actually define the axis - other parameters are ignored. AXIS LINE POINTS VECTORS
- The axis is taken as a coordinate axis of a given coordinate system. - The axis is taken as the straight line passing through the end points of a given geometry line (which is not necessarily straight, but must be open - i.e. have non-coincident end points). - The axis is taken as the straight line between two given (noncoincident) geometry points. - The axis is defined by a position and a direction vector.
SYSTEM [current active coordinate system] Label number of a coordinate system. One of the axes of this coordinate system may be used to define the axis, via parameter AXIS, when MODE=AXIS. AXIS [XL] Selects which of the basic axes (XL,YL,ZL) of the local coordinate system, given by parameter SYSTEM, is used to define the axis. {XL/YL/ZL} LINE Label number of a geometry line defining the axis. P1, P2 Label numbers of geometry points used to define the axis. X0 [0.0] Y0 [0.0] Z0 [0.0] Global coordinates of the position vector defining the axis when MODE=VECTORS. ADINA R & D, Inc.
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XA [1.0] YA [0.0] ZA [0.0] Components (with respect to the global coordinate system) of the axis direction when MODE=VECTORS. SIZE Constant (minimum) element size. The size function will yield this value within the distance given by parameter DISTANCE from the specified axis. Further away, the element size gradually increases as determined by this command. {> 0.0} DISTANCE Distance from the axis for which the size function is constant, giving element size SIZE. {> SIZE} SCALE Scaling factor for the distance from the source axis.
[1.0]
TYPE [LINEAR] Indicates the type of growth function for the element size away from the source axis. Let d=distance from axis, R = MAX[ 0.0, ((d-DISTANCE)/SCALE)], δ = element size, then the following function types are available: A1 A2 A3 Function coefficients. {≥ 0.0 for TYPE = LINEAR, QUADRATIC, CUBIC} LINEAR
δ = SIZE × [1.0 + A1 × R ]
QUADRATIC
δ = SIZE × 1.0 + A1 × R + A 2 × R 2
POWER
[ ] δ = SIZE × [1.0 + A1 × R + A 2 × R + A3 × R ] δ = SIZE × [1.0 + R ]
EXPONENTIAL
δ = SIZE × e ( A1× R )
2
CUBIC
[0.0] [0.0] [0.0]
3
A1
[
]
PROGRESS [NONE] This option controls the progression of the meshing from the defined point. {NONE/ ARITHMETIC/GEOMETRIC} NONE
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AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
SIZE-FUNCTION AXIS
Sec. 8.2 Mesh generation
ARITHMETIC
Only A1 is used. Sizing follows an arithmetic progression, in other words, past the cylinder of radius DISTANCE, sizes increase (as the distance to the cylinder increases) by a constant value given by A1. Start with size=SIZE, then next size is the previous size+A1.
GEOMETRIC
Only A1 is used. Sizing follows a geometric progression, in other words, past the cylinder of radius DISTANCE (where size is given by SIZE), sizes increase (as the distance to the cylinder increases) by a constant factor given by A1. Start with size=SIZE, then next size is the previous size*A1.
Auxiliary commands LIST SIZE-FUNCTION DELETE SIZE-FUNCTION
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SIZE-FUNCTION PLANE
SIZE-FUNCTION PLANE
Sec. 8.2 Mesh generation
NAME MODE X Y Z NX NY NZ P1 P2 P3 SYSTEM COORDINATE SIZE DISTANCE SCALE TYPE A1 A2 A3 PROGRESS
Defines a mesh-size function of source type where the element size is dependent on the distance from a given plane. The size-function may be used to set point mesh-sizes, via command POINT-SIZE, and also may be used directly by the free-form mesh generation commands GFACE, GBODY to control element sizes during the meshing process. NAME [(current highest size-function label) + 1] The identifying label number of the size-function. MODE This controls the origin and direction of the size-function source plane as follows: POSITION-NORMAL
The origin is given by a position vector (X,Y,Z), and the plane normal by a direction vector (NX,NY,NZ).
POINT-NORMAL
The origin is given by a geometry point P1, and the plane normal by a direction vector (NX,NY,NZ).
THREE-POINT
The origin is given by a geometry point P1, and the plane normal is determined from two other points, P2, P3, lying in the plane. The points cannot be collinear.
XPLANE YPLANE ZPLANE
The size-function source plane passes through the specified coordinate value (COORDINATE) for a given coordinate system (SYSTEM).
X [0.0] Y [0.0] Z [0.0] The position vector of a point lying in the source plane. Used when MODE=POSITIONNORMAL. NX [1.0] NY [0.0] NZ [0.0] The direction vector of the normal to the source plane. Used when MODE=POSITIONNORMAL or POINT-NORMAL.
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SIZE-FUNCTION PLANE
P1 P2 P3 Label numbers of three non-collinear geometry points lying in the source plane. P1 is used when MODE=POINT-NORMAL or THREE-POINT, and P2, P3 are only used when MODE=THREE-POINT. SYSTEM [current active coordinate system] Label number of a coordinate system. The source plane passes through the base Cartesian coordinate value as determined by parameters MODE and COORDINATE. Used when MODE=XPLANE, YPLANE, or ZPLANE. COORDINATE [0.0] The position of the size-function sourc plane along the specified coordinate direction of coordinate system SYSTEM. Used when MODE=XPLANE, YPLANE, or ZPLANE. SIZE Constant (minimum) element size. The size function will yield this value within the distance given by parameter DISTANCE from the specified plane. Further away, the element size gradually increases as determined by this function. {> 0.0} DISTANCE Distance from the plane for which the size function is constant, giving element size SIZE. {> SIZE} SCALE Scaling factor for the distance from the source plane.
[1.0]
TYPE [LINEAR] Indicates the type of growth function for the element size away from the source plane. Let d=distance from plane, R = MAX[ 0.0, ((d-DISTANCE)/SCALE)], δ = element size, then the following function types are available:
LINEAR
δ = SIZE × [1.0 + A1 × R ]
QUADRATIC
δ = SIZE × 1.0 + A1 × R + A 2 × R 2
POWER
[ ] δ = SIZE × [1.0 + A1 × R + A 2 × R + A3 × R ] δ = SIZE × [1.0 + R ]
EXPONENTIAL
δ = SIZE × e ( A1× R )
CUBIC
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AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
SIZE-FUNCTION PLANE
Sec. 8.2 Mesh generation
A1 A2 A3 Function coefficients. {≥ 0.0 for TYPE = LINEAR, QUADRATIC, CUBIC}
[0.0] [0.0] [0.0]
PROGRESS [NONE] This option controls the progression of the meshing from the defined point. {NONE/ ARITHMETIC/GEOMETRIC} NONE
TYPE, A1, A2, A3 are used according to the existing description (8.3 and earlier versions).
ARITHMETIC
Only A1 is used. Sizing follows an arithmetic progression, in other words, sizes increase (as the DISTANCE to the plane increases) by a constant value given by A1. Start with size=SIZE, then next size is the previous size+1.0*A1, etc.
GEOMETRIC
Only A1 is used. Sizing follows a geometric progression, in other words, sizes increase (as the DISTANCE to the plane increases) by a constant value given by A1. Start with size=SIZE, then next size is the previous size*A1, etc.
Auxiliary commands LIST SIZE-FUNCTION DELETE SIZE-FUNCTION
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SIZE-FUNCTION COMBINED
SIZE-FUNCTION COMBINED
NAME
szfunci Defines a mesh-size function as a combination of other size-functions. The element size at any given location is taken as the minimum of all the size-functions which contribute to this combination. The size-function may be used to set point mesh-sizes, via command POINT-SIZE, and also may be used directly by the free-form mesh generation commands GFACE, GBODY to control element sizes during the meshing process. NAME [(current highest size-function label) + 1] The identifying label number of the size-function. szfunci Label number of an existing size-function. This function cannot be the same as NAME, or of type COMBINED - i.e. recursive combinations are not allowed. Auxiliary commands LIST SIZE-FUNCTION DELETE SIZE-FUNCTION
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SIZE-LOCATIONS
SIZE-LOCATIONS
Sec. 8.2 Mesh generation
BODY FACE
loci xi yi zi sizei Specifies the mesh-size (element edge length) at coordinate locations (i.e. independent of any geometry point positions). These size-locations may be utilized by the free-meshing commands GFACE, GBODY to locally set element sizes within the bounds of a solid geometry face or body. The points along with the sizes are inserted into a “size octree” which will be used for mesh density purposes in GFACE and GBODY. BODY [currently active body] Label number of a solid geometry body to which the size-locations are to be associated. FACE [0] Label number of a the solid geometry face (of BODY) to which the size-locations are to be associated. If FACE = 0, the size-locations are to be associated with the solid geometry body interior and not with any particular one of its faces. Conversely, if FACE > 0, then the sizelocations are only associated with that face alone, and not with the interior of the body or any other of its faces. loci Location identifier. xi, yi, zi Global Cartesian coordinates of the size-location loci. sizei Mesh-size, element edge length at (xi, yi, zi). Auxiliary commands LIST SIZE-LOCATIONS BODY FACE DELETE SIZE-LOCATIONS BODY FACE
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NLTABLE
NLTABLE
NAME BODY
gtypei ent1i ent2i nlayeri Creates a table which specifies the minimum number of layers across thin setions in a body or on a face. Each thin section is specified by 2 opposing faces or edges. Tables can be used by commands GBODY and GFACE. NAME Label number of a table - NLTABLE. BODY Geometry body label. gtypei Specifies the entity type for entries ent1i and ent2i. EDGE
ent1i and ent2i are edges on face.
FACE
ent1i and ent2i are faces.
ent1i First face or edge label. ent2i Second face or edge label. nlayeri Minimum number of elements across the 2 faces or edges. Note:
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This command allows the user to control where the thin sections should be considered at the face/face level and also at the edge/edge level for a given face.
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
GPOINT
Sec. 8.2 Mesh generation
GPOINT
NAME NODE NCOINCIDE NCTOLERANCE SUBSTRUCTURE
Creates a node at a geometry point. NAME The label number of a geometry point at which a node is to be created. NODE The label number of node to be created.
[(highest node label number) + 1]
NCOINCIDE Selects the method of nodal coincidence checking. ALL
[NO]
The global coordinates of the generated node is compared against those of existing nodes of the substructure. If there is coincidence to within NCTOLERANCE × (max. difference in global coordinates between all current nodes of the substructure) then no new node is created at that location.
NO
No nodal coincidence checking is carried out.
NCTOLERANCE Tolerance used to determine nodal coincidence.
[TOLERANCES GEOMETRIC]
SUBSTRUCTURE [current substructure label number] Label number of the substructure in which the node is created.
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GLINE
GLINE
NAME NODES AUXPOINT NCOINCIDE NCENDS NCTOLERANCE SUBSTRUCTURE GROUP NCDOMAIN MIDNODES
linei Generates elements along a set of geometry lines. Elements can be created within element groups of type: TRUSS, BEAM, ISOBEAM, PIPE, GENERAL, or FLUID2 (interface). The number of elements, and the distribution of their lengths, is governed by the subdivision data assigned to the geometry lines, e.g., via SUBDIVIDE LINE. Note that either a single line or multiple lines may be specified for generation of elements, using the same control parameters. AUXPOINT NODES = 2
NODES = 3
NODES = 4
NAME The label number of a geometry line along which elements are to be generated. NODES The number of nodes per element. 2, 3, 4 2 2, 4 2, 3
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[2]
for TRUSS, ISOBEAM and GENERAL elements. for BEAM elements. for PIPE elements. for FLUID2 (interface) elements.
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
GLINE
Sec. 8.2 Mesh generation
AUXPOINT The label number of the auxiliary geometry point used to orient BEAM, ISOBEAM, and PIPE elements. A node is generated at this point, unless one already exists at that location, which becomes the auxiliary node for each element generated on the geometry line. NCOINCIDE Selects the method of nodal coincidence checking.
[ALL]
Coincidence checking is used to determine whether to place a new node at a geometric location when there is already at least one node close to that geometric location. A node at (XB,YB,ZB) is close to a geometric location (XA,YA,ZA) if |XB-XA| ≤ COINCIDENCE * XLEN |YB-YA| ≤ COINCIDENCE * YLEN |ZB-ZA| ≤ COINCIDENCE * ZLEN where NCTOLERANCE is a parameter of this command and (XLEN, YLEN, ZLEN) are decided by the following: If NCTOL-TYPE = RELATIVE-LOCAL in command TOLERANCES GEOMETRIC, (XLEN, YLEN, ZLEN) are the lengths of the bounding box for the volume before generation. If NCTOL-TYPE = RELATIVE-GLOBAL in command TOLERANCES GEOMETRIC, (XLEN, YLEN, ZLEN) are the lengths of the bounding box for the model before generation. If NCTOL-TYPE = ABSOLUTE in command TOLERANCES GEOMETRIC or no bounding box in the model, (XLEN, YLEN, ZLEN) are taken as (1.0, 1,0, 1.0). ALL
The global coordinates of all generated nodes are compared against those of existing nodes of the substructure.
ENDS
Coincidence checking is carried out only for the nodes generated at the end points of the geometry lines. The end point(s) participating in this checking process may be selected via NCENDS.
LINE
Coincidence checking is carried out for all generated nodes, but comparison is made only against those nodes already generated on the line under consideration.
SELECTED
Coincidence checking is carried out at the end points of the geometry lines, but comparison is made only against the nodes generated for the input set of lines for the current command execution and those already generated for the geometry domain indicated by NCDOMAIN.
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NO
GLINE
No nodal coincidence checking is carried out.
NCENDS [12] Selects which end points of the geometry lines participate in nodal coincidence checking. NCENDS is an integer of up to two distinct digits, either 1 or 2, indicating which end points of the geometry line are subject to nodal coincidence checking. NCENDS is only used when NCOINCIDE = ENDS. NCTOLERANCE Tolerance used to determine nodal coincidence.
[TOLERANCES GEOMETRIC]
SUBSTRUCTURE [current substructure label number] Label number of the substructure in which the elements and nodes are generated. GROUP [current element group] The label number of the element group into which the elements are generated. The group type must be one of those listed above. NCDOMAIN [0] Label number of a geometry domain for which nodal coincidence is checked. See DOMAIN. Used only when NCOINCIDE = SELECTED. NCDOMAIN = 0 indicates that no domain is to be used. MIDNODES [CURVED] Indicates whether the mid-side nodes for higher order elements are to be placed on the straight line between the relevant vertex nodes, or on the underlying curved geometry. {CURVED/STRAIGHT} linei Label number of a geometry line. Note:
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Elements are generated in order, in the direction from the starting point P1 to the ending point P2 of the geometry line.
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
surfacei Generates elements on a set of geometry surfaces. Elements can be created within element groups of type: TWODSOLID, PLATE, SHELL, GENERAL, FLUID2, or FLUID3 (interface). The distribution of elements, including their size, is governed by the subdivision data assigned to the edges of the geometry surfaces, e.g., via SUBDIVIDE SURFACE. Note that either a single surface or multiple surfaces may be specified for generation of elements, with the same control parameters.
Quadrilateral surface
Regular subdivision
Irregular subdivision
Triangular surface
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GSURFACE
NAME The label number of a geometry surface on which elements are to be generated. NODES [8 (3 for plate elements)] The number of nodes per element. {3/4/6/7/8/9/16} PATTERN [AUTOMATIC] Selects the type of pattern used to further subdivide quadrilateral surface cell subdivisions. Allowable values for PATTERN are integer numbers 0 through 11, or the string value AUTOMATIC. PATTERN=1 to 9 is allowed for triangular elements (NODES=3, 6, 7) and PATTERN=10, 11 is allowed only for NODES=4. See Figure. PATTERN OPTIONS:
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2
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4
5
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8
9
10
11
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GSURFACE
Sec. 8.2 Mesh generation
NCOINCIDE Selects the method of nodal coincidence checking.
[ALL]
Coincidence checking is used to determine whether to place a new node at a geometric location when there is already at least one node close to that geometric location. A node at (XB,YB,ZB) is close to a geometric location (XA,YA,ZA) if |XB - XA| ≤ NCTOLERANCE*XLEN |YB - YA| ≤ NCTOLERANCE*YLEN |ZB - ZA| ≤ NCTOLERANCE*ZLEN where where NCTOLERANCE is a parameter of this command and (XLEN, YLEN, ZLEN) are decided by the following: If NCTOL-TYPE = RELATIVE-LOCAL in command TOLERANCES GEOMETRIC, (XLEN, YLEN, ZLEN) are the lengths of the bounding box for the body before generation. If NCTOL-TYPE = RELATIVE-GLOBAL in command TOLERANCES GEOMETRIC, (XLEN, YLEN, ZLEN) are the lengths of the bounding box for the model before generation. If NCTOL-TYPE = ABSOLUTE in command TOLERANCES GEOMETRIC or no bounding box in the model, (XLEN, YLEN, ZLEN) are taken as (1.0, 1,0, 1.0). If there are no nodes close to that geometric location, a new node is placed at that geometric location. Otherwise, parameter NCOINCIDE governs whether a new node is placed at that geometric location, or whether a close node is used instead, as shown in the following table: NCOINCIDE
Which nodes to consider for coincidence all
Which nodes to check against all
BOUNDARIES
those on all vertices and edges of the face
all
SELECTED
those on all vertices and edges of the face
those within the geometry domain specified by parameter NCDOMAIN
ALL
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GSURFACE
GROUP
those on all vertices and edges of the face or faces meshed by the current command
those that are in the same element group
NO
none
none
NCEDGE [1234] Selects which edges of the geometry surfaces participate in nodal coincidence checking. NCEDGE is an integer of up to four distinct digits in the range 1 through 4. NCEDGE is only used when NCOINCIDE = BOUNDARIES. NCVERTEX [1234] Selects which vertices of the geometry surfaces participate in nodal coincidence checking. NCVERTEX is an integer of up to four distinct digits in the range 1 through 4. NCVERTEX is only used when NCOINCIDE = BOUNDARIES. NCTOLERANCE Tolerance used to determine nodal coincidence.
[TOLERANCES GEOMETRIC]
SUBSTRUCTURE [current substructure label number] Label number of the substructure in which the elements and nodes are generated. GROUP [current element group] The label number of the element group into which the generated elements are generated. PREFSHAPE [AUTOMATIC] This specifies the preferred shape of the cells created when the surface subdivision is irregular. If MESHING=MAPPED, AUTOMATIC - The command selects the appropriate cell shape depending on the surface geometry and element (group) type. QUADRILATERAL - A quadrilateral cell shape is preferred. TRIANGULAR - A triangular cell shape is preferred. If MESHING=FREE-FORM, AUTOMATIC - QUADRILATERAL if METHOD=ADVFRONT, TRIANGULAR if METHOD=DELAUNAY. QUADRILATERAL - A quadrilateral cell shape is preferred. TRIANGULAR - A triangular cell shape is preferred. QUAD-DIRECT - Quadrilateral only meshing.
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GSURFACE
Sec. 8.2 Mesh generation
CRACK-TYPE = LINE
CPOINT2
CPOINT1
CPOINT2
CPOINT1
CRACK-TYPE = POINT
TIP-POINT
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TIP-OPTION = CIRCULAR-ARC RADIU S
TIP-OPTION = SINGULAR
GSURFACE
CPOINT1
DI
US
RA
DI
TIP-OPTION = RIGHT-ARC US
TIP-OPTION = LEFT-ARC RA
CPOINT2 TIP-POINT
CPOINT1
TIP-POINT
CPOINT2 TIP-POINT
CPOINT1 TIP-POINT
CPOINT2
Q-POINT = QUARTER midside node
MESHING Selects the type of mesh generation to be employed. MAPPED Rule-based mapping of surface edge subdivisions. FREE-FORM
[MAPPED]
Free-form mesh generation based on advancing front or Delaunay scheme.
SMOOTHING Indicates whether or not Laplacian smoothing is employed to improve mesh quality. {YES/NO}
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GSURFACE
Sec. 8.2 Mesh generation
DEGENERATE [NO] Indicates whether triangular surfaces (with coincident vertices) are to be treated as degenerate quadrilaterals or triangles (with a special consideration for the degenerate edge, see Figure) for irregular rule-based mapped meshing. {YES/NO} CRACK-TYPE [NONE] Selects the type of crack propagation on surfaces, which controls mesh generation. See Figures. NONE
No crack propagation.
LINE
Crack propagation along line.
POINT
Crack is stationary at a point.
Note: When CRACK-TYPE ≠ NONE, GSURFACE will adjust the mesh generated for a set of input surfaces (i.e., more than one surface is typically required) for use in fracture mechanics problems, as shown in the Figures. TIP-POINT The label number of the crack tip point.
[1]
TIP-OPTION [SINGULAR] Allows the crack tip region to be represented as a single point or a circular arc. SINGULAR
The tip region is a single point.
RIGHT-ARC
The tip region is a 90° arc quadrant to the right of the tip.
LEFT-ARC
The tip region is a 90° arc quadrant to the left of the tip.
CIRCULAR-ARC
The tip region is semi-circular.
RADIUS The radius of the circular arc generated about the crack tip.
[0.0]
Q-POINT [QUARTER] Controls the placement of mid-side nodes in elements adjacent to the crack-tip. MID
The nodes are generated without any special placement.
QUARTER
Mid-side nodes are generated at the “¼” point adjacent to crack tip.
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GSURFACE
CPOINT1 [0] CPOINT2 [0] Allows for the specification of the points that are to be generated at key positions. This provides the ability to subsequently refer to these locations and any lines they belong to. Note that the point label numbers CPOINT1 and CPOINT2 must not have been defined prior to this command. See Figures. COLLAPSED [NO] Selects whether triangular TWODSOLID, FLUID2 or FLUID-3 (interface) elements are to be treated as collapsed quadrilateral elements by ADINA. {YES/NO} NCDOMAIN [0] Label number of a geometry domain for which nodal coincidence is checked. See DOMAIN. Used only when NCOINCIDE = SELECTED. NCDOMAIN = 0 indicates that no domain is to be used. MIDNODES [CURVED] Indicates whether the mid-side nodes for higher order elements are to be placed on the straight line between the relevant vertex nodes, or on the underlying curved geometry. {CURVED/STRAIGHT} METHOD Indicates the type of free-form meshing algorithm to be used. There are two available methods: ADVFRONT - Based upon advancing front methodology. DELAUNAY - Based upon Delaunay insertion methodology.
[ADVFRONT]
FLIP [NO] Reverses the orientation of shell elements on the surface. This parameter is only used when the element type is SHELL for ADINA or SHELL CONDUCTION for ADINA-T. {NO/YES} surfacei Label numbers of geometry surfaces.
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GVOLUME
GVOLUME
Sec. 8.2 Mesh generation
NAME NODES PATTERN NCOINCIDE NCFACE NCEDGE NCVERTEX NCTOLERANCE SUBSTRUCTURE GROUP MESHING PREFSHAPE DEGENERATE NCDOMAIN MIDNODES METHOD BOUNDARY-METHOD
volumei Generates elements on a set of geometry volumes. Elements can be created within element groups of type THREEDSOLID or FLUID3. The distribution of elements, including their size, is governed by the subdivision data assigned to the edges of the geometry volumes, e.g., via SUBDIVIDE VOLUME. NAME The label number of a geometry volume on which elements are to be generated. NODES The number of nodes per element. {4/8/10/11/20/27}
[20]
PATTERN [0] Selects the pattern used to subdivide hexahedral volume into tetrahedral elements (used when NODES=4, 10 or 11) - see Figures. PATTERN=0 indicates that one of the patterns 1 through 4 is to be automatically selected so as to match the patterns already used for adjacent volumes. If no pattern is suitable, for PATTERN=0, then a warning message is given and no elements are generated - in this case existing pattern usage must be examined carefully to avoid pattern mismatches which would result in incompatible meshes. (This parameter is only used when MESHING=MAPPED) NCOINCIDE [BOUNDARIES] Selects the method of nodal coincidence checking. {ALL/BOUNDARIES/SELECTED/ BOUNDEXSEL/GROUP/NO} Coincidence checking is used to determine whether to place a new node at a geometric location when there is already at least one node close to that geometric location. A node at (XB,YB,ZB) is close to a geometric location (XA,YA,ZA) if |XB - XA| ≤ NCTOLERANCE*XLEN |YB - YA| ≤ NCTOLERANCE*YLEN |ZB - ZA| ≤ NCTOLERANCE*ZLEN where where NCTOLERANCE is a parameter of this command and (XLEN, YLEN, ZLEN) are decided by the following:
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V2
V2
V1
V4
V3
V6
V5
V7
V4
V3
V6
V8
PATTERN = 2
PATTERN = 1 V2
V1
V2
V4
V6
V5
V7
V1
V4
V3
V6
V8
V7
PATTERN = 3
V5
V8
PATTERN = 4 V2
PATTERN = 5
V7
V1
V4
V3
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GVOLUME
Sec. 8.2 Mesh generation
If NCTOL-TYPE = RELATIVE-LOCAL in command TOLERANCES GEOMETRIC, (XLEN, YLEN, ZLEN) are the lengths of the bounding box for the body before generation. If NCTOL-TYPE = RELATIVE-GLOBAL in command TOLERANCES GEOMETRIC, (XLEN, YLEN, ZLEN) are the lengths of the bounding box for the model before generation. If NCTOL-TYPE = ABSOLUTE in command TOLERANCES GEOMETRIC or no bounding box in the model, (XLEN, YLEN, ZLEN) are taken as (1.0, 1,0, 1.0). If there are no nodes close to that geometric location, a new node is placed at that geometric location. Otherwise parameter NCOINCIDE governs whether a new node is placed at that geometric location, or whether a close node is used instead, as shown in the following table: NCOINCIDE
Which nodes to consider for coincidence
Which nodes to check against
ALL
all
all
BOUNDARIES
those on the selected vertices, edges and faces of the volume. Vertices, edges and faces are selected by parameters NCVERTEX, NCEDGE and NCFACE
all
SELECTED
those on all vertices, edges and faces of the volume or volumes meshed by the current command
those within the geometry domain selected by parameter NCDOMAIN
BOUNDEXSEL
those on all vertices, edges and faces of the volume except surfaces in the domain specified by NCDOMAIN
all
GROUP
those on all vertices, edges and faces of the volume or volumes meshed by the current command
those that are in the same element group
NO
none
none
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GVOLUME
NCFACE [123456] Selects which faces of the geometry volumes participate in nodal coincidence checking. NCFACE is an integer of up to six distinct digits in the range 1 through 6. NCFACE is only used when NCOINCIDE = BOUNDARIES. Refer to the follwoing figure for numbering (F1, F2, etc.) NCEDGE [123456789ABC] Selects which edges of the geometry volumes participate in nodal coincidence checking. NCEDGE is an alphanumeric string which can include the digits 1-9 and the characters A, B, C. NCEDGE is only used when NCOINCIDE = BOUNDARIES. Refer to the follwoing figure for numbering (E1, E2, etc.) F2 V2
E6 F3
E2
V4
E7
E8
F4
E12
E10 V7
E2
E5
F5
V6
V2 F3
E4
F1 E3
V3
E6 V1
E1
E3 E7
E9
F5
F4
E5 V5
E8 E9
V8
E11
E4
V4
V5
V1
E1
F1
V3
F2
V6
F6
F2 V2
F3
E2
V1
E3
E6
V3
E4
E5
P4
E3
F4
E5
E7
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E8
E6 V4
V1 E4
F1
F2
F4
E1
E2
E1
F1
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V2
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GVOLUME
Sec. 8.2 Mesh generation
NCVERTEX [12345678] Selects which vertices of the geometry volumes participate in nodal coincidence checking. NCVERTEX is an integer of up to eight distinct digits in the range 1 through 8. NCVERTEX is only used when NCOINCIDE = BOUNDARIES. Refer to the follwoing figure for numbering (V1, V2, etc.) NCTOLERANCE Tolerance used to determine nodal coincidence.
[TOLERANCES GEOMETRIC]
SUBSTRUCTURE [current substructure label number] Label number of the substructure in which the elements and nodes are generated. GROUP [current element group] The label number of the element group in which the generated elements are created. MESHING Selects the type of mesh generation to be employed.
[MAPPED]
MAPPED
Rule-based mapping based on volume edge subdivisions.
FREE-FORM
Free-form mesh generation.
When MESHING = MAPPED, and the volume subdivision is regular, the resulting mesh will consist entirely of hexahedral (brick) cells. If the subvision is irregular, the resulting mesh will be a mix of hexahedra and prisms, and the parameter PREFSHAPE (following) can be used. If the subdivision is neither regular nor irregular, an error message will be given. Example: In the case of the rectangular volume shown in the figure accompanying the command NCVERTEX (see preceding page), if we define Ni as the number of subdivisions on edge Ei (i = 1, 2, ...12), and set N2 = N4 = N12 = N10; N1 = N3 = N11 = N9; and N5 = N6 = N7 = N8, we have the volume set up with regular subdivisions, and the resulting mesh will be allhexahedral. If, however, we set N5 = N6 = N7 = N8; N1 = N9; N2 = N10; N3 = N11; and N4 = N12, the volume is set up with irregular subdivisions. PREFSHAPE [AUTOMATIC] Specifies the preferred shape of the cells created when the volume subdivision is irregular,
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whereby the command employs a rule-based scheme for mapped meshing. AUTOMATIC
The appropriate cell shape is determined by the program, depending on the volume geometry and element group type.
HEXAHEDRAL
A brick cell shape is preferred.
PRISMATIC
A prism cell shape is preferred.
DEGENERATE [YES] Indicates whether or not volumes of shape PRISM, TETRA or PYRAMID are to be treated as degenerate hexahedra with special consideration of the degenerate edges. {YES/NO} NCDOMAIN [0] Label number of a geometry domain for which nodal coincidence is checked. See DOMAIN. Used only when NCOINCIDE = SELECTED or NCOINCIDE = BOUNDEXSEL. NCDOMAIN = 0 indicates that no domain is to be used. MIDNODES [CURVED] Indicates whether the mid-side nodes for higher order elements are to be placed on the straight line between the relevant vertex nodes, or on the underlying curved geometry. {CURVED/STRAIGHT} METHOD [DELAUNAY] Indicates the type of free-form meshing algorithm to be used. There are two available methods: advancing front and Delaunay. This parameter is used only when MESHING=FREEFORM. {ADVFRONT/DELAUNAY} BOUNDARY-METHOD [ADVFRONT] Indicates the type of free-form meshing algorithm to be used for triangular elements on volume’s boundary. There are two available methods: advancing front and Delaunay. This parameter is only used when MESHING=FREE-FORM. {ADVFRONT / DELAUNAY} volumei Label number of a geometry volume.
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GEDGE
GEDGE
Sec. 8.2 Mesh generation
NAME NODES AUXPOINT NCOINCIDE NCTOLERANCE SUBSTRUCTURE GROUP BODY NCDOMAIN MIDNODES
edgei Generates elements along a set of solid geometry edges. Elements can be created within element groups of types TRUSS, BEAM, ISOBEAM, PIPE, GENERAL or FLUID2- interface. The number of elements, and the distribution of their lengths, is governed by the subdivision data assigned to the geometry edges, e.g., via SUBDIVIDE EDGE. Note that either a single edge or multiple edges may be specified for generation of elements. NAME
3-node isobeam elements
The label number of a geometry edge along which elements are to be generated. NODES The number of nodes per element. 2, 3, 4 2 2, 4 2, 3
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[2]
for TRUSS, ISOBEAM and GENERAL elements. for BEAM elements. for PIPE elements. for FLUID2 (interface) elements.
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GEDGE
AUXPOINT The label number of the auxiliary geometry point used to orient BEAM, ISOBEAM, and PIPE elements. A node is generated at this point, unless one already exists at that location, which becomes the auxiliary node for each element generated on the geometry edge. NCOINCIDE Selects the method of nodal coincidence checking.
[ENDS]
Coincidence checking is used to determine whether to place a new node at a geometric location when there is already at least one node close to that geometric location. A node at (XB,YB,ZB) is close to a geometric location (XA,YA,ZA) if |XB-XA| ≤ COINCIDENCE * XLEN |YB-YA| ≤ COINCIDENCE * YLEN |ZB-ZA| ≤ COINCIDENCE * ZLEN where NCTOLERANCE is a parameter of this command and (XLEN, YLEN, ZLEN) are decided by the following: If NCTOL-TYPE = RELATIVE-LOCAL in command TOLERANCES GEOMETRIC, (XLEN, YLEN, ZLEN) are the lengths of the bounding box for the volume before generation. If NCTOL-TYPE = RELATIVE-GLOBAL in command TOLERANCES GEOMETRIC, (XLEN, YLEN, ZLEN) are the lengths of the bounding box for the model before generation. If NCTOL-TYPE = ABSOLUTE in command TOLERANCES GEOMETRIC or no bounding box in the model, (XLEN, YLEN, ZLEN) are taken as (1.0, 1,0, 1.0). ALL
The global coordinates of all generated nodes are compared against those of existing nodes of the substructure.
ENDS
Coincidence checking is carried out only for the nodes generated at the end points of the geometry edges.
SELECTED
Coincidence checking is carried out at the end points of the geometry edges, but comparison is made only against those nodes generated for the input set of edges for the current command execution and those already generated for the geometry domain indicated by NCDOMAIN.
NO
No nodal coincidence checking is carried out.
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GEDGE
NCTOLERANCE Tolerance used to determine nodal coincidence.
Sec. 8.2 Mesh generation
[TOLERANCES GEOMETRIC]
SUBSTRUCTURE [current substructure] Label number of the substructure in which the elements and nodes are generated. GROUP [current element group] The label number of the element group into which the elements are generated. The group type must be one of those listed above. BODY The solid geometry part (body) label number.
[currently active body]
NCDOMAIN [0] Label number of a geometry domain for which nodal coincidence is checked. See DOMAIN. Used only when NCOINCIDE = SELECTED. NCDOMAIN = 0 indicates that no domain is to be used. MIDNODES [CURVED] Indicates whether the mid-side nodes for higher order elements are to be placed on the straight line between the relevant vertex nodes, or on the underlying curved geometry. {CURVED/STRAIGHT} edgei Label number of a geometry edge.
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GFACE
GFACE
NAME NODES NCOINCIDE NCTOLERANCE SUBSTRUCTURE GROUP PREFSHAPE BODY COLLAPSED SIZE-FUNCTION NCDOMAIN MIDNODES METHOD NLAYER NLTABLE GEO-ERROR SAMPLING MIN-SIZE AUTO-GRADING SIMULATE
facei Generates elements on a set of solid geometry faces. Elements can be created within element groups of type TWODSOLID, PLATE, SHELL, FLUID2, FLUID3-interface or GENERAL. There are two methods for quadrilateral mesh generation (controlled by PREFSHAPE parameter). If PREFSHAPE=QUAD-DIRECT,a proprietary algorithm is used to generate an allquad mesh. This methodology requires an even number of subdivisions for each bounding edge (enforced automatically). If PREFSHAPE=QUADRILATERAL, an advancing front method is used which may leave some triangles in the mesh. Two triangular free-form meshing methods (controlled by METHOD parameter) are available: advancing front and Delaunay. The distribution of elements, including their size, is governed by the subdivision data assigned to the edges of geometry faces, e.g. via SUBDIVIDE FACE. NAME The label number of a solid geometry face on which elements are to be generated. NODES [8 (3 for PLATE elements)] The number of nodes per element. {3/4/6/7/8/9/16}
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Sec. 8.2 Mesh generation
GFACE
NCOINCIDE [BOUNDARIES] Selects the method of nodal coincidence checking. {ALL/BOUNDARIES/BOUNDEXSEL/ GROUP/EXSELECTED/NO/SELECTED} Coincidence checking is used to determine whether to place a new node at a geometric location when there is already at least one node close to that geometric location. A node at (XB,YB,ZB) is close to a geometric location (XA,YA,ZA) if |XB - XA| ≤ NCTOLERANCE*XLEN |YB - YA| ≤ NCTOLERANCE*YLEN |ZB - ZA| ≤ NCTOLERANCE*ZLEN where where NCTOLERANCE is a parameter of this command and (XLEN, YLEN, ZLEN) are decided by the following: If NCTOL-TYPE = RELATIVE-LOCAL in command TOLERANCES GEOMETRIC, (XLEN, YLEN, ZLEN) are the lengths of the bounding box for the body before generation. If NCTOL-TYPE = RELATIVE-GLOBAL in command TOLERANCES GEOMETRIC, (XLEN, YLEN, ZLEN) are the lengths of the bounding box for the model before generation. If NCTOL-TYPE = ABSOLUTE in command TOLERANCES GEOMETRIC or no bounding box in the model, (XLEN, YLEN, ZLEN) are taken as (1.0, 1,0, 1.0). If there are no nodes close to that geometric location, a new node is placed at that geometric location. Otherwise, parameter NCOINCIDE governs whether a new node is placed at that geometric location, or whether a close node is used insted, as shown in the following table: NCOINCIDE
Which nodes to consider for coincidence
Which nodes to check against
ALL
all
all
BOUNDARIES
those on all vertices and edges of the face
all
BOUNDEXSEL
those on all vertices, edges and faces of the geometry body except edges in the domain specified by NCDOMAIN
all
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GFACE
GROUP
those on all vertices and edges of the face or faces meshed by the current command
those that are in the same element group
EXSELECTED
those on all vertices, edges and faces of the geometry body or bodies meshed by the current command
all, except those coming from the entities in the in the DOMAIN provided. Similar in concept to BOUNDEXSEL (the DOMAIN provided contains entities bounding the body to be meshed)
NO
none
none
SELECTED
nodes on boundary
nodes coming from the entities in domain NCDDOMAIN
NCTOLERANCE Tolerance used to determine nodal coincidence.
[TOLERANCES GEOMETRIC]
SUBSTRUCTURE [current substructure] Label number of the substructure in which the elements and nodes are generated. GROUP [current element group] The label number of the element group into which the elements are generated. PREFSHAPE [TRIANGULAR] Specifies the shape or preferred shape of the elements generated. {QUADRILATERAL/ TRIANGULAR/QUAD-DIRECT} QUADRILATERAL
Quadrilateral elements are preferred.
TRIANGULAR
Triangular elements are generated.
QUAD-DIRECT
Quadrilateral elements are generated.
BODY The solid geometry body label number.
[currently active solid body]
COLLAPSED [NO] Selects whether triangular TWODSOLID, FLUID2 or FLUID3-interface elements are to be treated as collapsed quadrilateral elements by ADINA. {YES/NO} 8-124
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GFACE
Sec. 8.2 Mesh generation
SIZE-FUNCTION [0] Label number of a mesh-size function (see command SIZE-FUNCTION) which may be used to control the element sizes away from the boundary edges of the face. SIZE-FUNCTION = 0 implies a size function is not to be used. Was not used in 8.3 and earlier (or if used with advancing front, was not giving the expected results). It is now functional if METHOD = DELAUNAY and BOUNDARY = DELAUNAY. (ADINA) NCDOMAIN [0] Label number of a geometry domain for which nodal coincidence is checked. See DOMAIN. Used only when NCOINCIDE = SELECTED. NCDOMAIN = 0 indicates that no domain is to be used. MIDNODES [CURVED] Indicates whether the mid-side nodes for higher order elements are to be placed on the straight line between the relevant vertex nodes, or on the underlying curved geometry. {CURVED/STRAIGHT} METHOD [ADVFRONT] Indicates the type of free-form meshing algorithm to be used. There are two available methods: advancing front and Delaunay. {ADVFRONT/DELAUNAY} NLAYER [1] Specifies a minimum number of elements across. By default, this option is off. To be turned on, NLAYER must be greater than 1. If NLAYER > 1 the distribution of elements, including their size, is also governed by the presence of thin sections on the face. NLAYER > 1 and NLTABLE = 0
NLAYER is taken as the minimum number of elements across anywhere in the body.
NLAYER > 1 and NLTABLE > 0
the minimum number of elements across is taken from the table NLTABLE (see command NLTABLE).
d
Geometry
Mesh L
d/L = geometrical discretization error ADINA R & D, Inc.
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GFACE
When NLAYER = 2, the program will make sure that there are NO interior mesh edges (segments) with both end vertices located on the boundary. Notes: 1) Only the first face (if more than one) will be affected by NLTABLE. 2) This option works best if a given bounding edge is NOT close to more than one other bounding edges within a small area, e.g., case of a small sphere close to the corner of a square. 3) The number of requested thin layers will be present in the thin sections but there is no guarantee near side boundaries. NLTABLE Table which indicates the thin sections of face.
[0]
GEO-ERROR [0.0] Relative geometric discretization error (see picture). If GEO-ERROR > 0.0 the distribution of elements, including their size, is also governed by the curvature of the geometry body's bounding edges and faces. (Only applicable if METHOD=DELAUNAY.) SAMPLING Number of sampling points on edge Meaningful only if GEO-ERROR option turned on. For edges: number of sampling points = SAMPLING For faces: number of sampling points = SAMPLINGxSAMPLING MIN-SIZE Minimum size allowed. Meaningful only if GEO-ERROR option turned on. It is important to give a meaningful value to MIN-SIZE to avoid overrefinement and, as a consequence, high CPU times for this command. (Only applicable if METHOD=DELAUNAY.) AUTO-GRADING [NO] Mesh densities required to satisfy smooth gradation. {NO/YES} If AUTO-GRADING=YES the distribution of elements, including their size, is also governed by the requirement for smoothly graded mesh densities. SIMULATE [NO] This parameter can be used (SIMULATE=YES) to see the effect on the body edge subdivisions of the GFACE command without actually meshing. It is relevant for the following cases: - MESHING= FREE-FORM, and GEO-ERROR > 0.0 or AUTO-GRADING = YES - MESHING=FREE-FORM and PREFSHAPE=QUAD-DIRECT (will modify body edge subdivisions so that the body face has an even number of subdivisions; necessary condition for quadrilateral meshing on the body face)
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bodyi deg-edgei Command GBODY creates elements for a solid geometry body. Elements can be created within element groups of type THREEDSOLID or FLUID3. There are two tetrahedral free-form meshing METHODs available: advancing front and Delaunay. There are two triangular free-form meshing BOUNDARY-METHODs available: advancing front and Delaunay. Mapped meshing is available only when the body type is a Parasolid® body and the geometry of the body is either tetrahedron, hexahedron, prism or pyramid.
NAME The label number of a solid geometry body for which elements are to be generated. NODES The number of nodes per element. {4/8/10/11/20/27}
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Sec. 8.2 Mesh generation
GBODY
NCOINCIDE [BOUNDARIES] Selects the method of nodal coincidence checking. {ALL/BOUNDARIES/BOUNDEXSEL/ GROUP/EXSELECTED/NO/SELECTED} Coincidence checking is used to determine whether to place a new node at a geometric location when there is already at least one node close to that geometric location. A node at (XB,YB,ZB) is close to a geometric location (XA,YA,ZA) if |XB - XA| ≤ NCTOLERANCE*XLEN |YB - YA| ≤ NCTOLERANCE*YLEN |ZB - ZA| ≤ NCTOLERANCE*ZLEN where where NCTOLERANCE is a parameter of this command and (XLEN, YLEN, ZLEN) are decided by the following: If NCTOL-TYPE = RELATIVE-LOCAL in command TOLERANCES GEOMETRIC, (XLEN, YLEN, ZLEN) are the lengths of the bounding box for the body before generation. If NCTOL-TYPE = RELATIVE-GLOBAL in command TOLERANCES GEOMETRIC, (XLEN, YLEN, ZLEN) are the lengths of the bounding box for the model before generation. If NCTOL-TYPE = ABSOLUTE in command TOLERANCES GEOMETRIC or no bounding box in the model, (XLEN, YLEN, ZLEN) are taken as (1.0, 1,0, 1.0). If there are no nodes close to that geometric location, a new node is placed at that geometric location. Otherwise parameter NCOINCIDE governs whether a new node is placed at that geometric location, or whether a close node is used instead, as shown in the following table: NCOINCIDE
Which nodes to consider for coincidence
Which nodes to check against
ALL
all
all
BOUNDARIES
those on all vertices, edges and faces of the geometry body
all
BOUNDEXSEL
those on all vertices, edges and faces of the geometry body except faces in the domain specified by NCDOMAIN
all
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GBODY
GROUP
those on all vertices, edges and faces of the geometry body or bodies meshed by the current command
those that are in the same element group
EXSELECTED
those on all vertices, edges and faces of the geometry body or bodies meshed by the current command
all, except those coming from the entities in the in the DOMAIN provided. Similar in concept to BOUNDEXSEL (the DOMAIN provided contains entities bounding the body to be meshed)
NO
none
none
SELECTED
nodes on boundary
nodes coming from the entities in domain NCDDOMAIN
NCTOLERANCE Tolerance used to determine nodal coincidence.
[TOLERANCES GEOMETRIC]
SUBSTRUCTURE [current substructure] Label number of the substructure in which the elements and nodes are created. GROUP [current element group] The label number of the element group into which the elements are generated. PREFSHAPE [AUTOMATIC] Specifies the preferred shape of the cells created when the body subdivision is irregular, whereby the command employs a rule-based scheme for mapped meshing. AUTOMATIC
The appropriate cell shape is determined by the program, depending on the body geometry and element group type.
HEXAHEDRAL
A brick cell shape is preferred.
PRISMATIC
A prism cell shape is preferred.
This parameter is used only when MESHING=MAPPED.
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GBODY
Sec. 8.2 Mesh generation
SIZE-FUNCTION [0] Selects an auxiliary mesh-size function which controls the element sizes within the body. See command SIZE-FUNCTION. SIZE-FUNCTION = 0 indicates that a size-function is not to be used. Was not used in 8.3 and earlier (or if used with advancing front, was not giving the expected results). It is now functional if METHOD = DELAUNAY and BOUNDARY = DELAUNAY. (ADINA) DELETE-SLIVER [NO] Controls whether triangular “sliver” element faces are to be removed from the body boundary before generating volume elements. Such slivers can arise from small geometry features such as fillets or rounds with small curvature, or by inappropriate edge subdivision data. The presence of such slivers can result in poor quality elements and a degradation of the meshing process. Enabling the prior removal of such slivers may result in a mesh which smoothest over small geometric features - if these features are important then the local subdivision data should be refined about them. {YES/NO} Note:
This parameter is ignored if METHOD=DELAUNAY.
ANGLE-MIN [5.0] Provides an angle-tolerance for detecting boundary slivers. A triangular element face is considered a sliver if one of its internal angles is less than ANGLE-MIN (in degrees). {0.0 ≤ ANGLE-MIN ≤ 10.0} (The upper bound precludes unrealistic sliver definitions). MIDNODES [CURVED] Indicates whether the mid-side nodes for higher order elements are to be placed on the straight line between the relevant vertex nodes, or on the underlying curved geometry. {CURVED/STRAIGHT} METHOD [DELAUNAY] Indicates the type of free-form meshing algorithm to be used. There are two available methods: advancing front and Delaunay. This parameter is only used when MESHING=FREE-FORM. {ADVFRONT/DELAUNAY} PATTERN [0] Selects the pattern used to subdivide the hexahedral body cells into tetrahedral elements (used when NODES=4, 10 or 11) - see figures - GVOLUME command. PATTERN=0 indicates that one of the patterns 1 through 5 is to be automatically selected so as to match the patterns already used for adjacent volumes. If no pattern is suitable, for PATTERN=0, then a warning message is given and no elements are generated - in this case existing pattern usage must be examined carefully to avoid pattern mismatches which would result in incompatible meshes. This parameter is only used when MESHING=MAPPED.
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GBODY
MESHING [FREE-FORM] Selects the type of mesh generation to be employed. {MAPPED/FREE-FORM} MAPPED
A rule based mapping of body edge subdivisions. Mapped meshing is available only when the body is a Parasolid body and the topology of the body is similar to a hexahedron, prism, pyramid, or tetrahedron.
FREE-FORM
when NODES=4,10,11 free-form mesh generation based on advancing front or Delaunay scheme creates tetrahedral elements. when NODES=8,27 free-form mesh generation based on advancing front creates a mix of hexahedral and tetrahedral elements, with hexahedral elements occupying most of the volume space.
DEGENERATE Indicates how bodies with triangular faces are to be handled:
[NO]
NO
The triangular face is not given any special consideration for its degenerate edge.
YES
The volume is treated as a degenerate hexahedral shape.
Note:
This parameter is only used when MESHING=MAPPED.
BOUNDARY-METHOD [ADVFRONT] Indicates the type of free-form meshing algorithm to be used for triangular elements on
d
Geometry
Mesh L
d/L = geometrical discretization error body’s boundary. There are two available methods: advancing front and Delaunay. {ADVFRONT/DELAUNAY} ADVFRONT
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GBODY
Sec. 8.2 Mesh generation
DELAUNAY
Note:
the distribution of elements, including their size, is governed by the subdivision data assigned to the geometry bodies, e.g. via command SUBDIVIDE BODY and by the rules of smooth gradation. This means subdivisions on body edges may be overwritten to allow for smooth gradation of element sizes.
This parameter is only used when MESHING=FREE-FORM.
DEG-EDGE [0] The degenerate edge of the body. This parameter is only used if the body is a prism body, MESHING=MAPPED, and DEGENERATE = YES. GEO-ERROR [0.0] Relative geometric discretization error (see picture). If GEO-ERROR > 0.0 the distribution of elements, including their size, is also governed by the curvature of the geometry body's bounding edges and faces. (Only applicable if BOUNDARY-METHOD=DELAUNAY.) SAMPLING Number of sampling points on edge Meaningful only if GEO-ERROR option turned on. For edges: number of sampling points = SAMPLING For faces: number of sampling points = SAMPLINGxSAMPLING MIN-SIZE Minimum size allowed. Meaningful only if GEO-ERROR option turned on. It is important to give a meaningful value to MIN-SIZE to avoid overrefinement and, as a consequence, high CPU times for this command. (Only applicable if BOUNDARY-METHOD=DELAUNAY.) NLAYER [1] When NODES = 4,10,11 and MESHING = FREE-FORM, specifies a minimum number of elements across. By default, this option is off. To be turned on, NLAYER must be greater than 1. If BOUNDARY-METHOD = DELAUNAY, this option also applies to any bounding face (of the body). If no NLTABLE is specified, NLAYER is used as the minimum number of elements across anywhere in body. When NLAYER = 2, the program will make sure that there are NO interior mesh edges (segments) with both end vertices located on the boundary. NLTABLE Table which indicates the thin sections of body and/or body faces.
[0]
AUTO-GRADING [NO] Mesh densities required to satisfy smooth gradation. {NO/YES} If AUTO-GRADING=YES the distribution of elements, including their size, is also governed
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GBODY
by the requirement for smoothly graded mesh densities. NCDOMAIN [0] Label number of a geometry domain for which nodal coincidence is checked. See DOMAIN. Used only when NCOINCIDE=SELECTED or NCOINCIDE=BOUNDEXSEL. NCDOMAIN=0 indicates that no domain is to be used. PYRAMIDS [NO] When NODES = 8,20,27 and MESHING = FREE-FORM, indicates whether pyramid elements should be used to transition from hexahedra to tetrahedra. If PYRAMIDS = ONLY, no hexahedra are created and pyramids are created for each boundary quadrilateral cell. In order to guarantee (if possible) quadrilateral surface meshes on all faces of a body (as opposed to possible triangles among the quads), it is necessary to set PYRAMIDS=ONLY or YES. Note that when PYRAMIDS=YES, pyramids may be created not only for boundary quad facets but also for interior quad facets (if those facets connect directly to tetrahedra), meaning that a possibly large number of pyramids may be created. If the program fails to create all the pyramids that are needed, an error message will be displayed and the command will be cancelled. In this case, it is recommended to decrease the maximum dihedral angle allowed for quad facets (see DANGMAXC parameter), use PYRAMIDS=ONLY or change the mesh density. {NO/YES/ONLY} DANGMAXB Max angular deviation (from 90 degrees) for the angle at corners of hex side faces.
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DANGMAXC [60/20] Max angular deviation (from 180 degrees) for the dihedral angle at diagonals of hex side faces Default = 60 degrees (20 degrees if PYRAMIDS = YES). DANGMAXD Max angular deviation (from 90 degrees) for the dihedral angle at hex edges.
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HEXALAYER [NO] When NODES = 8,20,27 and MESHING = FREE-FORM, specifies the number of hexahedral element layers to be grown from body’s boundary faces (0 or 1).By default, this number is set to 0. To be turned on, HEXALAYER must be equal to YES. SIMULATE [NO] This parameter can be used (SIMULATE=YES) to see the effect on the body edge subdivisions of the GBODY command without actually meshing. It is relevant for the following cases: - MESHING= FREE-FORM, and GEO-ERROR>0.0 or AUTO-GRADING=YES
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GBODY
Sec. 8.2 Mesh generation
- MESHING=FREE-FORM and NODES=8,20,27 (brick elements) EVEN [SUM] When GBODY is used with NODES=8,20,27, the command pre-processes the subdivisions to make sure the all-quad mesher will produce all-quad meshes on the body faces. This parameter controls the number of subdivisions as follows. {SUM/LINK/ALL} SUM
For each body face, the program forces the sum of the subdivisions of the bounding edges to be even.
LINK
The program forces any bounding edge of a linked face (FACELINK) to have an even number of subdivisions. Note that the program also forces the sum of the subdivisions of the bounding edges of non-linked faces to be even.
ALL
The program forces any edge to have an even number of subdivisions.
MIDFACENODES [TRIA] Determines where the mid-face node on a quadrilateral facet (of an hexahedral or pyramid element) should be placed. TRIA places the mid-face nodes mid-way on the diagonal of the two triangles making up the facet. QUAD places the mid-face node at the centroid of the four facet vertices. {TRIA/QUAD} When elements with quad facets connect with tetrahedral elements, TRIA should be selected. Otherwise, QUAD should be selected. This only concerns free form meshing (higher order mixed meshing) and quadrilateral facets on linked body faces. bodyi Label numbers of geometry bodies. The data line input allows for more than one body to be meshed via a single GBODY command call. deg-edgei The degenerate edge of bodyi . This data is only used if the body is a prism body, MESHING=MAPPED, and DEGENERATE=YES.
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GHEXA
GHEXA
NAME NODES NCOINCIDE NCDOMAIN NCTOLERANCE GROUP MIDNODES SIZE MINSIZE PROJECT SMOOTH DANGMAXA OPTIONA SHIFTX SHIFTY SHIFTZ MAX-REF
Generates brick element (hexahedron) dominant free-form meshes for a given body. Note that this command - meshes the boundary as well as the inside of the given body - does not take into account edge subdivisions (see SIZE parameter) - does not update edge subdivisions - should only be used on near-primitive bodies Any body connected (typically via a face) to a body meshed with GHEXA must be meshed with GBODY in order to produce compatible meshes (at the interface). However, because GHEXA does not guarantee that nodes classified on the body's boundary are actually on the body's boundary, it is not always possible to mesh connected bodies. This is due to the fact that GBODY (unlike GHEXA) always assumes that nodes classified on the body's boundary are actually on the body's boundary. Because GHEXA does not guarantee the creation of an all-quad surface mesh, it may be necessary to mesh connected bodies with tetrahedral elements only. cover (cutaway)
gear (cutaway) pulley
NAME Label number of geometry body. NODES The number of nodes per element. {8/20/27}
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Sec. 8.2 Mesh generation
NCOINCIDE [BOUNDARIES] Selects the method of nodal coincidence checking.{ALL/BOUNDARIES/BOUNDEXSEL/ GROUP/NO} Coincidence checking is used to determine whether to place a new node at a geometric location when there is already at least one node close to that geometric location. A node at (XB,YB,ZB) is close to a geometric location (XA,YA,ZA) if |XB - XA| ≤ NCTOLERANCE*XLEN |YB - YA| ≤ NCTOLERANCE*YLEN |ZB - ZA| ≤ NCTOLERANCE*ZLEN where NCTOLERANCE is a parameter of this command and (XLEN,YLEN,ZLEN) are the lengths of the bounding box for the model before generation. If there is no bounding box, then XLEN,YLEN,ZLEN are taken as (1.0,1.0,1.0). If there are no nodes close to that geometric location, a new node is placed at that geometric location. Otherwise parameter NCOINCIDE governs whether a new node is placed at that geometric location, or whether a close node is used instead, as shown in the following table:
NCOINCIDE
Which nodes to consider for coincidence
Which nodes to check against
ALL
all
all
BOUNDARIES
those on all boundaries as defined by the input boundary cell sets
all
BOUNDEXSEL
those on boundaries as defined by the input boundary cell sets except those in the domain specified by NCDOMAIN
all
GROUP
those on boundaries as defined by the input boundary cell sets
those that are in the same element group
NO
none
none
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GHEXA
NCDOMAIN [0] Label number of a geometry domain for which nodal coincidence is checked. See DOMAIN. Used only when NCOINCIDE = BOUNDEXSEL. NCDOMAIN = 0 indicates that no domain is to be used. NCTOLERANCE Tolerance used to determine nodal coincidence.
[TOLERANCES GEOMETRIC]
GROUP [current element group] The label number of the element group in which the generated elements are created. MIDNODES [STRAIGHT] Indicates whether the mid-side nodes for higher order elements are to be placed on the straight line between the relevant vertex nodes (STRAIGHT), or on the underlying curved geometry using either mapping from parameter space to real space (CURVED), or projection (PROJECT). {CURVED/STRAIGHT/PROJECT} SIZE Desired (uniform) mesh density for elements to be created. The generated element size will only approximately be equal to SIZE. MIN-SIZE This parameter is obsolete.
[0.0]
PROJECT [YES] Mesh vertices on the body’s boundary are projected onto the corresponding body’s entities. It refers to the mesh obtained after subdividing the body’s polyhedral representation. It does not relate to MIDNODES. {YES/NO} SMOOTH [NO] Mesh vertices on the body’s boundary are smoothed. It refers to the mesh obtained after subdividing the body’s polyhedral representation. {YES/NO} DANGMAXA [20.0] Maximum angle allowed for face normals before and after collapsing of edges, considering the body’s polyhedral representation. The polyhedral representation is obtained by intersecting the body with a regular grid (with cell size equal to 2 x SIZE), which is then subdivided (once) to obtain the final mesh topology. {0.0 ≤ DANGMAXA ≤ 180.0} OPTIONA [YES] Option to allow faces to share more than one edge during the collapsing of edges considering the body’s polyhedral representation (see DANGMAXA). {YES/NO}
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Sec. 8.2 Mesh generation
NO
Allows faces to share more than one edge during collapsing of edges. MIN-SIZE will more likely be respected, but the body may not be successfully meshed.
YES
Does not allow faces to share more than one edge during collapsing of edges. MINSIZE is less likely to be respected, but successful meshing of the body is more probable.
SHIFTX [0.0] SHIFTY [0.0] SHIFTZ [0.0] Shifts along the X, Y and Z directions the bounding box used for the grid (whose intersection with the body gives the body's polyhedral representation). MAX-REF [5] When problems are detected, the grid can be locally refined to resolve those problems. MAXREF indicates how many times the program is allowed to subdivide the problem grid cells and restart. If the problems can not be resolved, it is suggested to reduce SIZE (uniformly).
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GADAPT
GADAPT
NAME NODES NCOINCIDE NCTOLERANCE SUBSTRUCTURE GROUP MIDNODES NCDOMAIN COLLAPSED
bodyi facei Functionality of this command is as follows: In 3D, facei =0 Takes a finite element mesh attached to a body or set of bodies, deletes it (keeping the boundary mesh intact), adapts the boundary mesh based on the provided mesh densities and remeshes the interior(s). In 2D, facei ≠ 0 Takes a finite element mesh attached to a body face or set of body faces, deletes it (keeping the boundary mesh intact), adapts the boundary mesh based on the provided mesh densities and remeshes the interior(s). Desired (new) mesh densities are provided to the program using the SIZE-LOCATIONS command. The SIZE-LOCATIONS entries would typically correspond to node locations along with mesh densities. Note that they do not have to be as long as they are inside the geometric entity given in the argument. If there are no SIZE-LOCATIONS entries, the quality of the boundary mesh is optimized without changing the mesh density. NAME The label number of a solid geometry body for which elements are to be generated. NODES The number of nodes per element. {4/8/10/11/20/27} NCOINCIDE Selects the method of nodal coincidence checking.
[4] [BOUNDARIES]
Coincidence checking is used to determine whether to place a new node at a geometric location when there is already at least one node close to that geometric location. A node at (XB,YB,ZB) is close to a geometric location (XA,YA,ZA) if |XB - XA| ≤ NCTOLERANCE*XLEN |YB - YA| ≤ NCTOLERANCE*YLEN |ZB - ZA| ≤ NCTOLERANCE*ZLEN
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GADAPT
where NCTOLERANCE is a parameter of this command and (XLEN,YLEN,ZLEN) are the lengths of the bounding box for the body before generation. If there is no bounding box, then XLEN,YLEN,ZLEN are taken as (1.0,1.0,1.0). If there are no nodes close to that geometric location, a new node is placed at that geometric location. Otherwise parameter NCOINCIDE governs whether a new node is placed at that geometric location, or whether a close node is used instead, as shown in the following table: NCOINCIDE
Which nodes to consider for coincidence
Which nodes to check against
ALL
all
all
BOUNDARIES
those on all vertices, edges and faces of the geometry body
all
BOUNDEXSEL
those on all vertices, edges and faces of the geometry body except faces in the domain specified by NCDOMAIN
all
GROUP
those on all vertices, edges and faces of the geometry body or bodies meshed by the current command
those that are in the same element group
NO
none
none
NCTOLERANCE [TOLERANCES GEOMETRIC] Tolerance used to determine nodal coincidence.then XLEN,YLEN,ZLEN are taken as (1.0,1.0,1.0). SUBSTRUCTURE [current substructure] Label number of the substructure in which the elements and nodes are created. GROUP [current element group] The label number of the element group into which the elements are generated.
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MIDNODES [CURVED] Indicates whether the mid-side nodes for higher order elements are to be placed on the straight line between the relevant vertex nodes, or on the underlying curved geometry. {CURVED/STRAIGHT} NCDOMAIN [0] Label number of a geometry domain for which nodal coincidence is checked. See DOMAIN. Used only when NCOINCIDE=SELECTED or NCOINCIDE=BOUNDEXSEL. NCDOMAIN=0 indicates that no domain is to be used. COLLAPSED [NO] Selects whether tetrahedral THREEDSOLID, or FLUID3 elements are to be treated as collapsed hexahedral elements by ADINA. {NO/YES} bodyi Label numbers of geometry bodies. The data line input allows for more than one body to be meshed via a single GADAPT command call. facei Label number of a geometry face (of BODY).
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GBCELL
GBCELL
SUBSTRUCTURE GROUP NODES NCOINCIDE NCTOLERANCE NCDOMAIN COLLAPSED PYRAMIDS BCELL
bcelli Creates 3D elements from boundary cells. Boundary cells are grouped into sets using the BCELL command. The boundary cells must form a water-tight domain and must be oriented towards the domain. This command creates node sets and element face sets corresponding to each boundary cell set. SUBSTRUCTURE [current substructure label number] Label number of the substructure in which the elements and nodes are created. The default value is defined by the last preceding SUBSTRUCTURE command. GROUP [current element group number] The label number of the element group in which the generated elements are created. The default value is determined by the last preceding SET EGROUP command. The group type must be one of those listed above. NODES The number of nodes per element. Allowable values for each analysis program are ADINA ADINA-T ADINA-F
Note that if NODES=8, 20, or 27, boundary cells must be made up of all 4-node quadrilateral cells. NCOINCIDE [BOUNDARIES] Selects the method of nodal coincidence checking. {ALL/BOUNDARIES/GROUP/NO} Coincidence checking is used to determine whether to place a new node at a geometric location when there is already at least one node close to that geometric location. A node at (XB,YB,ZB) is close to a geometric location (XA,YA,ZA) if |XB - XA| |YB - YA| |ZB - ZA|
where NCTOLERANCE is a parameter of this command and (XLEN,YLEN,ZLEN) are the lengths of the bounding box for the model before generation. If there is no bounding box, then XLEN,YLEN,ZLEN are taken as (1.0,1.0,1.0).
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GBCELL
If there are no nodes close to that geometric location, a new node is placed at that geometric location. Otherwise parameter NCOINCIDE governs whether a new node is placed at that geometric location, or whether a close node is used instead, as shown in the following table: NCOINCIDE
Which nodes to consider Which nodes to for coincidence check against
ALL
all
all
BOUNDARIES
those on all boundaries as defined by the input boundary cell sets
all
GROUP
those on boundaries as defined by the input boundary cell sets
those that are in the same element group
NO
none
none
NCTOLERANCE
[value set by parameter COINCIDENCE of command TOLERANCES GEOMETRIC] Tolerance used to determine nodal coincidence. NCDOMAIN [0] Label number of a geometry domain for which nodal coincidence is checked. See DOMAIN. Used only when NCOINCIDE = SELECTED or NCOINCIDE = BOUNDEXSEL. NCDOMAIN = 0 indicates that no domain is to be used. COLLAPSED [NO] Selects whether tetrahedral THREEDSOLID, or FLUID3 elements are to be treated as collapsed hexahedral elements by ADINA. NO YES
- Tetrahedral elements are not collapsed - Tetrahedral elements are treated as collapsed hexahedra
PYRAMIDS [NO] When NODES = 8,20,27, this parameter indicates whether pyramid elements should be used to transition from hexahedral to tetrahedral elements. If PYRAMIDS = ONLY, no hexahedral elements are created and pyramid elements are created for each boundary quadrilateral cell. {NO/YES/ONLY}
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GBCELL
Sec. 8.2 Mesh generation
BCELL [ALL] Indicates whether all boundary cells are used to create the 3-D mesh. {ALL/SELECT} ALL
All boundary cells are used.
SELECT
Selected boundary cells as specified by bcelli are used.
bcelli Label number of boundary cell. Boundary cells specified in the list are used to create the 3-D mesh.
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ELDELETE LINE
ELDELETE
NAME GROUP SUBSTRUCTURE NODE-DELETE
linei ELDELETE SURFACE
NAME GROUP SUBSTRUCTURE NODE-DELETE
surfacei ELDELETE VOLUME
NAME GROUP SUBSTRUCTURE NODE-DELETE
volumei ELDELETE EDGE
NAME GROUP SUBSTRUCTURE NODE-DELETE BODY
edgei ELDELETE FACE
NAME GROUP SUBSTRUCTURE NODE-DELETE BODY
facei ELDELETE BODY
NAME GROUP SUBSTRUCTURE NODE-DELETE
bodyi ELDELETE deletes elements generated on a given geometry entity for a specific element group. The nodes connected to the deleted elements may also be optionally deleted (provided they are not connected to other elements or define other model features). NAME Label number of the geometry entity for which generated elements are to be deleted. GROUP Element group label number. SUBSTRUCTURE Substructure label number.
[current group number]
[current substructure number]
NODE-DELETE Node deletion option. {YES/NO}
[YES]
BODY [currently active body] Label number of a solid geometry body. Used for edge/face references in ELDELETE EDGE/ FACE linei /surfacei /volumei /edgei /facei /bodyi Line/Surface/Volume/Edge/Face/Body label number.
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COPY-MESH-BODY
COPY-MESH-BODY
Sec. 8.2 Mesh generation
BODY1 BODY2 SUBSTRUCTURE GROUP NCOINCIDE NCDOMAIN NCTOLERANCE TRANSFORMATION
Copies a mesh from one body to another body via affine transformation. BODY1 Body whose mesh is to be copied. {>0} BODY2 Target body. {>0} SUBSTRUCTURE [current substructure] Label number of the substructure in which the elements and nodes are created. GROUP [current element group] The label number of the element group into which the elements are generated. NCOINCIDE Selects the method of nodal coincidence checking.
[BOUNDARIES]
Coincidence checking is used to determine whether to place a new node at a geometric location when there is already at least one node close to that geometric location. A node at (XB,YB,ZB) is close to a geometric location (XA,YA,ZA) if |XB - XA| ≤ NCTOLERANCE*XLEN |YB - YA| ≤ NCTOLERANCE*YLEN |ZB - ZA| ≤ NCTOLERANCE*ZLEN where where NCTOLERANCE is a parameter of this command and (XLEN, YLEN, ZLEN) are decided by the following: If NCTOL-TYPE = RELATIVE-LOCAL in command TOLERANCES GEOMETRIC, (XLEN, YLEN, ZLEN) are the lengths of the bounding box for the body before generation. If NCTOL-TYPE = RELATIVE-GLOBAL in command TOLERANCES GEOMETRIC, (XLEN, YLEN, ZLEN) are the lengths of the bounding box for the model before generation. If NCTOL-TYPE = ABSOLUTE in command TOLERANCES GEOMETRIC or no bounding box in the model, (XLEN, YLEN, ZLEN) are taken as (1.0, 1,0, 1.0). If there are no nodes close to that geometric location, a new node is placed at that geometric location. Otherwise parameter NCOINCIDE governs whether a new node is placed at that geometric location, or whether a close node is used instead, as shown in the following table:
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NCOINCIDE
Which nodes to consider for coincidence
Which nodes to check against
ALL
all
all
BOUNDARIES
those on all vertices, edges and faces of the geometry body
all
BOUNDEXSEL
those on all vertices, edges and faces of the geometry body except those in the domain specified by NCDOMAIN
all
GROUP
those on all vertices, edges and faces of the geometry body or bodies meshed by the current command
those that are in the same element group
NO
none
none
NCDOMAIN [0] Label number of a geometry domain for which nodal coincidence is checked. See DOMAIN. Used only when NCOINCIDE=SELECTED or NCOINCIDE=BOUNDEXSEL. NCDOMAIN=0 indicates that no domain is to be used. NCTOLERANCE Tolerance used to determine nodal coincidence.
[1.0E-5]
TRANSFORMATION Transformation used to match BODY1 to BODY2. Using this transformation, all faces on BODY1 must match all faces on BODY2. {>0}
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CSURFACE
CSURFACE
NAME NODES PATTERN NCOINCIDE NCTOLERANCE SUBSTRUCTURE GROUP
Generates a set of contact segments on a contact-surface, see CONTACTSURFACE. Contact segments are normally created by default from associated finite elements defined on the geometry of the contact-surface. However, a target contact-surface which is rigid (or has a completely known displacement), may be defined to consist of contact segments with no associated finite elements. The distribution of segments, including their size, is governed by the subdivision data assigned to the geometry components of the contact-surface, e.g., via SUBDIVIDE LINE, SUBDIVIDE SURFACE. NAME The label number of a contact-surface on which contact segments are to be generated. NODES The number of nodes per contact segment.
[2 (2-D); 4 (3-D)]1 [3 (2-D); 9 (3-D)]2
The default value is indicated by the superscripts 1 or 2 as follows: 1. 2.
The permitted values depend on whether the contact-surface is 2-D or 3-D: 2-D contact-surface – {2/3}. 3-D contact-surface – {3/4/6/9}. PATTERN [1] Selects the type of triangulation pattern used to further subdivide the quadrilateral surface subdivisions into triangular segments, only used when NODES = 3, i.e., for 3-D contact segments. (See GSURFACE for PATTERN options). NCOINCIDE [SURFACE] Controls nodal coincidence checking. If SURFACE is selected, nodal coincidence is carried out, but comparison is made against only those nodes already generated on the contactsurface. {YES/NO/SURFACE} NCTOLERANCE Tolerance used to determine nodal coincidence.
[TOLERANCES GEOMETRIC]
SUBSTRUCTURE [current substructure number] Label number of the substructure in which the contact segments and nodes are generated. GROUP [current contact group number] The label number of the contact group into which the contact segments are generated. ADINA R & D, Inc.
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CSDELETE
CSDELETE LINE
NAME GROUP CONTACTSURFACE NODE-DELETE
CSDELETE SURFACE
NAME GROUP CONTACTSURFACE NODE-DELETE
CSDELETE EDGE
NAME GROUP CONTACTSURFACE NODE-DELETE BODY
CSDELETE FACE
NAME GROUP CONTACTSURFACE NODE-DELETE BODY
Deletes contact segments generated on a given geometry entity for a specified contact group. Nodes connected to the contact segments may be optionally deleted (provided they do not connect to other elements or define other model features). NAME Label number of the geometry entity for which generated elements are to be deleted. GROUP [current active contact group number] Contact group label number. Contact segments should have already been generated on geometry entity "NAME". CONTACTSURFACE Contact surface label number. NODE-DELETE Node deletion option:
[1] [YES]
NO
No nodes are deleted as a result of this command
YES
Nodes which are only connected to elements in the deleted set (i.e. those generated on the line for the particular element group) will be deleted.
BODY The body label number.
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GLUEMESH
GLUEMESH
Sec. 8.3 Elements
NAME EXTENSION
stypei namei bodyi
sidei
Glues two dissimilar meshes together. The mesh on each side (master or slave) may span over several sites. NAME Label number of GLUEMESH. EXTENSION [0.01] Extension for the master surface (as a ratio of element length). {0.00 < EXTENSION ≤ 0.25 } This extension is only applied to glueing of 3-D meshes. stypei Type of site the gluing is applied to. Sites must be either all 2-D types (line, edge, elementedge) or all 3-D types (surface, face, element-face). {‘LINE’/‘SURFACE’/‘EDGE’/‘FACE’/‘ELEMENT-EDGE’/‘ELEMENT-FACE’} For example, GLUEMESH NAME=1 ‘SURFACE’ 1 0 SLAVE ‘SURFACE’ 5 0 MASTER namei Site label number. bodyi Body label number when stypei = EDGE or FACE. sidei Indicates whether site is on the master or slave side. {SLAVE/MASTER}
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TRUSS-POINTS
TRUSS-POINTS namei pointi materiali areai printi savei tbirthi tdeathi epsini Defines axisymmetric truss elements at geometry points. Coincidence checking is used when generating nodes at the geometry points, with tolerance adjusted by the command TOLERANCES GEOMETRIC. Note: The current element group must be of type TRUSS, with axisymmetric subtype, for this command to be active. namei Label number of an axisymmetric truss element. pointi Label number of the geometry point associated with the axisymmetric truss element. materiali [0] Label number for the material to be used with element “namei”. A zero value indicates that the element group default material is to be used. areai The cross-sectional area of the element.
[1.0]
printi [DEFAULT] Printing flag for the element. If DEFAULT is specified, printout is controlled by PRINTOUT PRINTDEFAULT. {YES/NO/DEFAULT} savei [DEFAULT] Saving (to the porthole file) flag for the element. If DEFAULT is specified, saving is controlled by PORTHOLE SAVEDEFAULT. {YES/NO/DEFAULT} tbirthi Time of element birth.
[0.0]
tdeathi Time of element death.
[0.0]
epsini Element initial strain.
[0.0]
Auxiliary commands LIST TRUSS-POINTS DELETE TRUSS-POINTS
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SPRING POINTS
Sec. 8.3 Elements
SPRING POINTS namei p1i dof1i p2i dof2i pseti printi savei axi ayi azi tbirthi tdeathi Defines spring elements either between two degrees of freedom at distinct geometry points, or a “grounded” degree of freedom at a single geometry point. Coincidence checking is used when generating nodes at the geometry points, with tolerance adjusted by the command TOLERANCES GEOMETRIC. Note:
The current element group must be of type SPRING for this command to be active.
namei Label number of a spring element. p1i Label number of the first (or only) geometry point at one end of the spring element. dof1i The degree of freedom selected for the spring element at the first point “p1i”. 1 2 3 4 5 6
X translation. Y translation. Z translation. X rotation. Y rotation. Z rotation.
p2i Label number of the second geometry point at the opposite end of the spring element from point “p1i”. Input of p2i = 0 implies that the degree of freedom “dof1i” at point “p1i” is connected to ground. dof2i The degree of freedom for the spring element at point “p2i”. The choice of input values is the same as for entry “dof1i”. If p2i = 0, then input for dof2i is ignored. pseti Label number of the spring property set for element springi. See PROPERTYSET.
[1]
printi [DEFAULT] Printing flag for the element. If DEFAULT is specified, printout is controlled by PRINTOUT PRINTDEFAULT. {YES/NO/DEFAULT}
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SPRING POINTS
savei [DEFAULT] Saving (to the porthole file) flag for the element. If DEFAULT is specified, saving is controlled by PORTHOLE SAVEDEFAULT. {YES/NO/DEFAULT} axi, ayi, azi [0.0] Global coordinate system components of the spring element direction, used if the spring connects two coincident points, or one point to ground. Note that this vector is only used for nonlinear spring elements. tbirthi Element birth time.
[0.0]
tdeathi Element death time.
[0.0]
Note:
tbirthi < tdeathi,
or
tbirthi = tdeathi = 0.0
Auxiliary commands LIST SPRING POINTS DELETE SPRING POINTS
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SPRING LINES
Sec. 8.3 Elements
SPRING LINES namei line1i dof1i line2i dof2i pseti printi savei axi ayi azi tbirthi tdeathi option Defines “spring-lines”, i.e. a set of spring elements either between two degrees of freedom along distinct geometry lines, or a “grounded” degree of freedom along a single geometry line. namei Label number of a spring-line. line1i Label number of the first (or only) geometry line at one end of the spring-line. dof1i The degree of freedom selected for the spring elements along the first line “line1i”. 1 2 3 4 5 6
X translation. Y translation. Z translation. X rotation. Y rotation. Z rotation.
line2i Label number of the second geometry line at the opposite end of the spring-line from “line1i”. Input of line2i = 0 implies that the degree of freedom “dof1i” at line “line1i” is connected to ground. dof2i The degree of freedom selected for the spring elements along the second line “line2i”. If line2i = 0, then input for dof2i is ignored. pseti Label number of the spring property set for spring-line “namei”. See PROPERTYSET.
[1]
printi [DEFAULT] Printing flag for the element. If DEFAULT is specified, printout is controlled by PRINTOUT PRINTDEFAULT. {YES/NO/DEFAULT} savei [DEFAULT] Saving (to the porthole file) flag for the element. If DEFAULT is specified, saving is controlled by PORTHOLE SAVEDEFAULT. {YES/NO/DEFAULT}
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SPRING LINES
axi, ayi, azi [0.0] Global coordinate system components of the spring-line direction, used if the spring-line connects two coincident nodes, or one node to ground. tbirthi Element birth time.
[0.0]
tdeathi Element death time.
[0.0]
Note:
tbirthi < tdeathi,
or
tbirthi = tdeathi = 0.0
option [SAME] {SAME / REVERSE} When multiple nodes exist on the line1 and line2, this flags how the spring element between nodes on each entity is defined. SAME -
A spring is constructed between nodes at the corresponding parametric order on each line. Parametric order is in the increasing u-parameter direction for lines.
REVERSE - A spring is constructed between nodes at the corresponding parametric order on each line, but for line2 the parametric order is reversed. Auxiliary commands LIST SPRING LINES DELETE SPRING LINES
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REBAR-LINE
REBAR-LINE
Sec. 8.3 Elements
NAME NCOINCIDE
linei Defines a rebar using lines. The rebar defined is then referenced in the EGROUP TRUSS command to model rebar elements. NAME [(current highest rebar-line label number) + 1] Label number of the rebar-line to be defined. This label is referenced in the EGROUP TRUSS command. NCOINCIDE [NO] Coincidence checking is used to determine whether to place a new node at end point of geometry line. {NO/YES} linei List of geometry line label numbers used for defining the rebar. Auxiliary commands LIST REBAR-LINE DELETE REBAR-LINE
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TRUSS-LINE
TRUSS-LINE name line1 line2 material area print save tbirth tdeath gapwidth intloc epsin option Creates 2-node general truss elements between line1 and line2 or 1-node axisymmetric truss elements on line1 at the line subdivision locations. name Label number of a truss-line line1 Line1 label number line2 Line2 label number. Specify line2=0 for axisymmetric truss element. material [0] Material label number. A zero input value indicates that elements generated on the line will take the default material for the host element group. area Cross-sectional area for each TRUSS element on the line.
[1.0]
print [DEFAULT] Printing flag for the element. If DEFAULT is specified, printout is controlled by PRINTOUT PRINTDEFAULT. {YES/NO/DEFAULT} YES
Print element results as requested by parameter RESULTS of the relevant EGROUP command.
NO
No results are printed for TRUSS elements on the line.
DEFAULT
Element printing is governed by parameter PRINTDEFAULT of the PRINTOUT command.
save [DEFAULT] Saving (to the porthole file) flag for the element. If DEFAULT is specified, saving is controlled by PORTHOLE SAVEDEFAULT. {YES/NO/DEFAULT} YES
Save, on the porthole file, element results as requested by parameter RESULTS of the relevant EGROUP command.
NO
No saving of results for TRUSS elements on the line.
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Sec. 8.3 Elements
TRUSS-LINE
DEFAULT
Saving of element results is governed by parameter SAVEDEFAULT of the PORTHOLE command.
tbirth The time of element birth.
[0.0]
tdeath The time of element death.
[0.0]
Note: tbirth < tdeath, or tbirth = tdeath = 0.0 gapwidth Gap width for each TRUSS element on the line.
[0.0]
intloc [NO] Option to print the location of the integration point. {YES/NO} YES
Print the element integration point (global) coordinates, in the undeformed configuration. No printing of integration point data for TRUSS elements on the line.
NO
epsin Initial strain for each TRUSS element on the line. option {SAME/REVERSE}
[0.0] [SAME]
When multiple nodes exist on the line1 and line2, this flags how the truss element between nodes on each entity is defined. SAME
A truss is constructed between nodes at the corresponding parametric order on each line. Parametric order is in the increasing u-parameter direction for lines.
REVERSE
A truss is constructed between nodes at the corresponding parametric order on each line. For line2 the parametric order is reversed.
Auxiliary commands LIST TRUSS-LINE DELETE TRUSS-LINE
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ELTHICKNESS
Sec. 8.3 Elements
ELTHICKNESS namei thick1i thick2i thick3i ... thick16i Defines thickness for 3D shell elements and axisymmetric shell elements (EGROUP ISOBEAM SUBTYPE =AXISYMMETRIC). namei The element label number, in the current element group. thick1i Thickness of shell element “i” at local node number 1.
[0.0]
thick2i Thickness of shell element “i” at local node number 2.
[thick1i]
. . . thick16i Thickness of shell element “i” at local node number 16.
[thick1i]
Note:
Thickness is measured in the direction of the director/normal vector at the node.
Note:
The thicknesses “thickni” are defined for midsurface nodes, ignoring top/bottom nodes of transition elements.
Auxiliary commands LIST ELTHICKNESS DELETE ELTHICKNESS
ni xi yi zi sysi Defines coordinates for current substructure nodes. The coordinates given refer to the local system specified by parameter SYSTEM. SYSTEM [currently active system] Label number of the required local coordinate system. This specifies the coordinate system to which any appended data line coordinates refer and determines which column heading names are allowed by any ENTRIES data line. ENTRIES Defines, as column headings, the input for the subsequent tabular entries. The heading names depend on the type of local coordinate system specified by SYSTEM. Note:
Less than five entry column headings may be given e.g., to specify nodes in a coordinate plane, but the column heading NAME must always be specified.
ni Label number for the desired current substructure node, input under the column heading NAME. xi yi zi Coordinate values in local coordinate system “sysi”.
[0.0] [0.0] [0.0]
sysi [SYSTEM] Local coordinate system label number. Note “sysi” defaults to the system specified by SYSTEM, which in turn defaults to the currently active coordinate system. Auxiliary commands LIST COORDINATES NODE FIRST LAST SYSTEM GLOBAL DELETE COORDINATES NODE FIRST LAST If GLOBAL = YES the coordinates are listed in terms of the global Cartesian system.
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SKEWSYSTEM NODES
SKEWSYSTEMS NODES ni node1i node2i node3i Defines “skew” Cartesian coordinate systems in terms of nodes. Skew systems can be referenced via DOF-SYSTEM to indicate the local orientation of nodal degrees of freedom. ni Label number for the skew system to be defined. node1i node2i node3i Node label numbers. The vector from node1i to node2i defines the direction of the local X-axis of the skew system. The vector from node1i to node3i is taken to lie in the local XY-plane of the skew system. Note that the three nodes must not be collinear. Auxiliary commands LIST SKEWSYSTEM DELETE SKEWSYSTEM
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DOF-SYSTEM NODES
DOF-SYSTEM NODES
Sec. 9.1 Nodal data
SUBSTRUCTURE
nodei skewsystemi Assigns skew coordinate systems to the degrees of freedom associated with a set of nodes in the current substructure. SUBSTRUCTURE [current substructure] Label number of the substructure for the nodes referenced in the accompanying data lines. nodei Label number of a node in the current substructure given by SUBSTRUCTURE. skewsystemi Label number of a skew coordinate system, as defined by SKEWSYSTEM. Setting skewsystemi = 0 assigns the global Cartesian system to the nodal degrees of freedom. Auxiliary commands LIST DOF-SYSTEM NODES DELETE DOF-SYSTEM NODES
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Chap. 9 Direct finite element data input
MASSES NODES
MASSES NODES nodei mass1i mass2i mass3i mass4i mass5i mass6i Assigns concentrated masses to a set of nodes in the current substructure. nodei Label number of a node. mass1i [0.0] The mass assigned to nodei for the x-translational degree of freedom (global or skew). mass2i [0.0] The mass assigned to nodei for the y-translational degree of freedom (global or skew). mass3i [0.0] The mass assigned to nodei for the z-translational degree of freedom (global or skew). mass4i [0.0] The mass moment of inertia assigned to nodei for the x-rotational degree of freedom (global or skew). mass5i [0.0] The massmoment of inertia assigned to nodei for the y-rotational degree of freedom (global or skew). mass6i [0.0] The mass moment of inertia assigned to nodei for the z-rotational degree of freedom (global or skew). Auxiliary commands LIST MASSES NODES DELETE MASSES NODES
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DAMPERS NODES
Sec. 9.1 Nodal data
DAMPERS NODES nodei damp1i damp2i damp3i damp4i damp5i damp6i Assigns concentrated dampers to a set of nodes in the current substructure. nodei Label number of a node. damp1i [0.0] The damper assigned to nodei for the x-translational degree of freedom (global or skew). damp2i [0.0] The damper assigned to nodei for the y-translational degree of freedom (global or skew). damp3i [0.0] The damper assigned to nodei for the z-translational degree of freedom (global or skew). damp4i [0.0] The rotational damper assigned to nodei for the x-rotational degree of freedom (global or skew). damp5i [0.0] The rotational damper assigned to nodei for the y-rotational degree of freedom (global or skew). damp6i [0.0] The rotational damper assigned to nodei for the z-rotational degree of freedom (global or skew). Auxiliary commands LIST DAMPERS NODES DELETE DAMPERS NODES
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Chap. 9 Direct finite element data input
SHELLNODESDOF NODES
SUBSTRUCTURE
nodei nsdofi ndirvi Specifies the number of degrees of freedom and the director vector number, if applicable, for midsurface shell element nodes. This specification overrides the global default set by MASTER SHELLNDOF. SUBSTRUCTURE [current substructure] The substructure for each node specified in this command. nodei The node number. nsdofi [MASTER SHELLNDOF] Number of degrees of freedom for nodei, if the node is a shell node. FIVE
Shell midsurface rotational degrees of freedom are used.
SIX
Global or skew degrees of freedom are used.
AUTOMATIC
The program chooses the number of degrees of freedom to be used based on certain modeling considerations. See Theory and Modeling Guide.
ndirvi Number of a director vector defined by the SHELLDIRECTORVECTOR. Auxiliary commands LIST SHELLNODESDOF NODES DELETE SHELLNODESDOF NODES
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SHELLDIRECTORVECTOR
SHELLDIRECTORVECTOR ni vxi vyi vzi
Sec. 9.1 Nodal data
OPTION SUBSTRUCTURE
(OPTION = COMPONENTS)
or ni phii thetai
(OPTION = EULERANGLES)
Defines director vectors that can be applied to shell element nodes in the model via command SHELLNODESDOF. Director vectors are used in shell analysis to define the shell director vectors for those nodes with five (5) degrees of freedom. It is not necessary to specify director vectors for these nodes, however, as the program will automatically compute director vectors for those nodes for which you do not assign director vectors. OPTION
[COMPONENTS]
COMPONENTS
Director vectors are input in the form of vector components in the global coordinate system. Input vx, vy and vz in the data lines.
EULERANGLES
Director vectors are input in the form of Euler rotation angles in the global coordinate system. Input phi and theta in the data lines.
SUBSTRUCTURE [current substructure] The substructure for the director vector specified by this command. ni Director vector number. vxi vyi vzi Components of the director vector. This vector need not be normalized.
[0.0] [0.0] [0.0]
phii thetai Euler rotation angles measured in degrees.
[0.0] [0.0]
Auxiliary commands LIST SHELLDIRECTORVECTOR FIRST LAST OPTION SUBSTRUCTURE DELETE SHELLDIRECTORVECTOR FIRST LAST OPTION SUBSTRUCTURE
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NODESET
NODESET
NAME ALL-EXT OPTION GROUP ZONE ELSET TARGET ANGLE
nodei substructurei reusei (OPTION = NODE) namei (OPTION = MERGE/SUBTRACT/INTERSECT) namei bodyi (OPTION = LINE-EDGE/SURFACE-FACE) Defines a collection of nodes by label number. The NODESET may be referenced by other commands such as CONSTRAINT, RIGIDLINK, BEAMSET, and SPRINGSET. NAME [(current highest nodeset label number) + 1] Label number of NODESET. ALL-EXT [NO] Indicates whether this node set includes all nodes on the external boundary of the model. If ALL-EXT=YES, then "nodei" is a list of nodes which will be excluded in this node set. Note that parameter ALL-EXT is used only for OPTION = NODE. {YES/NO} OPTION [NODE] The option to define the NODESET. {NODE/GROUP/ZONE/ELEDGESET/ELFACESET/ MERGE/SUBTRACT/INTERSECT/LINE-EDGE/SURFACE-FACE/CHAIN}
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NODE
NODESET is defined from table input.
GROUP
NODESET is defined from given Element Group.
ZONE
NODESET is defined from given Zone name. Note that all nodes are added only from zone entities that contain element information.
ELEDGESET
NODESET is defined from given element edge set in parameter ELSET.
ELFACESET
NODESET is defined from given element face set in parameter ELSET.
MERGE
NODESET is defined by merging nodesets specified in the table.
SUBTRACT
NODESET is defined by subtracting from the TARGET nodeset the nodesets specified in the table.
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
NODESET
Sec. 9.1 Nodal data
INTERSECT
NODESET is defined as the intersection of all nodesets specified in the table.
LINE-EDGE
NODESET is defined from nodes currently on geometry lines and edges.
SURFACE-FACE NODESET is defined from nodes currently on geometry surfaces and faces. CHAIN
NODESET is defined according to the normal direction of the first element face in the table. All element faces of continuous normal direction with the same element type will be selected. All nodes on these element faces will be filled in the table.
GROUP [0] If GROUP > 0 all element nodes of this group will be included in this NODESET. Used only for OPTION = GROUP. ZONE Zone name. Used only for OPTION = ZONE. ELSET Label number of element edge set if OPTION = ELEDGESET. Label number of elfaceset if OPTION = ELFACESET. Ignored for other values of OPTION.
[0]
TARGET Label number of target nodeset for OPTION = SUBTRACT.
[0]
ANGLE Angle (in degrees) used to determine all continuous normal directions.
[0.0]
nodei Node label number. Used only for OPTION = NODE. substructurei [current substructure] Substructure label number for nodei. Used only for OPTION = NODE. reusei Reuse label number for nodei. Used only for OPTION = NODE.
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namei Label number of element node set. Used only for OPTION = MERGE/SUBTRACT/INTERSECT/LINE-EDGE/SURFACE-FACE. bodyi Label number of element node set. Used only for OPTION = LINE-EDGE/SURFACEFACE. Auxiliary commands LIST NODESET DELETE NODESET
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RIGIDNODES SHELL
Sec. 9.1 Nodal data
RIGIDNODES SHELL nodei Specifies shell midsurface nodes for which the rotation normal to the shell is constrained to the perpendicular translations of neighboring shell midsurface nodes. This effectively removes the usual singularity associated with the lack of stiffness for the shell normal rotation degree of freedom. This condition may be used, for example, in conjunction with beam or spring elements to connect two or more offset shell surfaces. Note that any node specified cannot have 5 or 6 degrees-of-freedom explicitly assigned (either directly or to any attached geometry); i.e. they must have an “automatic” number of degrees-of-freedom assignment. Thereafter, if the automatic calculation otherwise results in 5 degrees-of-freedom, the actual number of degree-of-freedom will be output as 6 and the required constraint will be applied. nodei The label number of a shell midsurface node. The node must belong to the main structure (not any substructure). Auxiliary commands LIST RIGIDNODES SHELL
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AXES-NODES
AXES-NODES
NAME NODE1 NODE2 NODE3
Defines an “axes-system” via three model nodes. Axes-systems can be referenced by element data commands (e.g., EDATA) to indicate the local orientation of the orthotropic material properties and/or initial strain. NAME Label number for the desired axes-system. This is numbered independently for each element group. NODE1 Label number of the first node defining the axes-system. NODE2 Label number of the second node defining the axes-system. NODE3 Label number of the third node defining the axes-system. Note:
The local x-direction of the axes-system is determined by the vector from NODE1 to NODE2. The local z-direction of the axes-system is determined as the normal to the plane defined by the three nodes NODE1, NODE2, and NODE3. The local y-direction of the axes-system is then given by the right-hand rule.
Auxiliary commands LIST AXES-NODES DELETEAXES-NODES
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AXES-INITIALSTRAIN
AXES-INITIALSTRAIN
Sec. 9.2 Element data
NAME LINE ALFA GROUP
elei This command defines sets of axes to be used with the definition of the directions of the initial strains in each element. Elements are input in the data lines. A geometry line labeled LINE and an angle ALFA (in degrees) are used to define the initial strain axes orientations. The elements can belong to the current element group or an element group input through the GROUP parameter. Axes initial strain system can be referenced by commands INITIAL STRAINS and INITIAL SGRADIENTS to specify initial strains or initial strain gradients. This command is applicable to 2D, 3D, plate and shell elements. NAME [(current highest defined label) + 1] Label number for the desired axes-initial strain system to apply to the specified elements.. LINE Label number of the defined geometry line. The geometry line must either be a straight line or an arc line. ALFA An angle (in degrees) is used together with the geometry line.
[0.0]
GROUP [current element group] Element group number which this axes-initial strain system is applied to. elei Element number which this axes-initial strain system is applied to. Auxiliary commands LISTAXES-INITIALSTRAIN DELETEAXES-INITIALSTRAIN
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AXES-ORTHOTROPIC
Chap. 9 Direct finite element data input
AXES-ORTHOTROPIC
NAME LINE ALFA GROUP
elei This command defines sets of principal material axes orientations for the elements used with the orthotropic material model. Elements are input in the data input lines. A geometry line labeled LINE and an angle ALFA (in degrees) are used to define the principal material axes orientations. The elements can belong to the current element group or an element group input through the GROUP parameter. This command is applicable for 2D, plate and shell elements. NAME [(highest axes-orthotropic system) + 1] Label number for the desired axes-orthotropic system. LINE Label number of the defined geometry line. The geometry line must be a straight line or an arc line. ALFA An angle (in degrees) is used together with the geometry line.
[0.0]
GROUP [current element group] Element group number which this axes-orthotropic system is applied to. elei Element number which this axes-orthotropic system is applied to. Auxiliary commands LIST AXES-ORTHOTROPIC DELETE AXES-ORTHOTROPIC
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ELEDGESET
Sec. 9.2 Element data
ELEDGESET edgei
eli
NAME ALL-EXT OPTION TARGET groupi (OPTION = ELEDGE)
namei
(OPTION = MERGE/SUBTRACT/INTERSECT)
namei
bodyi
(OPTION = LINE-EDGE)
Defines an element edge set containing edges of 2-D elements. An element edge set can be used for load application (APPLY-LOAD command) such as pressure, normal traction and heat flux. It can also be used in the definition of a 2-D contact surface (see command CONTACT-ELEMSET ). NAME [(current highest eledgeset label number) + 1] Label number of the element edge set. ALL-EXT [NO] Indicates whether this element edge set includes all external boundary element edges. If ALL-EXT=YES, then edgei is a list of element edges which will be excluded in this element edge set. Note that parameter ALL-EXT is used only for OPTION = ELEDGE. {YES/NO} OPTION [ELEDGE] The option to define the element edge set.{ELEDGE/LINE-EDGE/MERGE/SUBTRACT/ INTERSECT} ELEDGE
Define an element edge set by specifying element edges in the table
LINE-EDGE
Define an element edge set from geometry lines or edges
MERGE
Merge element edge sets specified in the table
SUBTRACT
Subtract from the TARGET element edge set the element edge sets specified in the table
INTERSECT
Obtain the intersection of all element edge sets specified in the table
TARGET Label number of target element face set for OPTION = SUBTRACT .
[0]
edgei Edge number of the element. Used only for OPTION = ELEDGE.
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ELEDGESET
eli Label number of the element. Used only for OPTION = ELEDGE. groupi Label number of the element group. Used only for OPTION = ELEDGE. namei Label number of element edge set. Used only for OPTION = MERGE/SUBTRACT/INTERSECT (without bodyi) or OPTION = LINE-EDGE (with bodyi). bodyi Label number of body; if bodyi = 0 , this means that the geometry is a line. Used only for OPTION = LINE-EDGE. Auxiliary commands LIST ELEDGESET DELETE ELEDGESET
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ELEMENTSET
ELEMENTSET
Sec. 9.2 Element data
NAME GROUP
eli groupi Defines an element set containing elements specified in the parameter GROUP and in the table entries. Element sets containing beam or truss elements can be referenced in the SWEEP and REVOLVE commands to generate reinforcement beam or truss elements. Element sets containing 3-D solid, 2-D solid, and shell elements can be referenced in the SETAXES-MATERIAL and SET-AXES-STRAIN commands to specify the orientation of orthotropic material properties or initial strains for the elements. NAME Label number of ELEMENTSET. GROUP [0] Specifies an element group to be included in this element set. If GROUP > 0 is specified, all elements in the group will be included in this element set. eli Label number of the element. groupi Label number of the element group for element eli. Auxiliary commands LIST ELEMENTSET DELETE ELEMENTSET
FIRST LAST FIRST LAST
Example ELEMENTSET NAME=2 GROUP=5 3 2 TO 10 2 @ The above command will create an element set 2 which contains all elements in element group 5 and elements 3 to 10 in element group 2.
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Chap. 9 Direct finite element data input
ELFACESET facei
ELFACESET
NAME ALL-EXT OPTION GROUP ZONE ANGLE TARGET
eli
groupi
(OPTION = ELFACE)
namei
(OPTION = MERGE/SUBTRACT/INTERSECT)
namei
bodyi
(OPTION = SURFACE-FACE)
Defines an element face set containing faces of 3-D and shell elements. An element face set can be used for load application ( APPLY-LOAD command) such as pressure, normal traction and heat flux. It can also be used in the definition of a 3-D contact surface (see command CONTACT-ELEMSET ). NAME [(current highest elfaceset label number + 1)] Label number of the element face set. ALL-EXT [NO] Indicates whether this element face set includes all external boundary element faces. If ALLEXT=YES, then facei is a list of element faces which will be excluded in this element face set. Note that parameter ALL-EXT is used only for OPTION = ELFACE.{YES/NO} OPTION [ELFACE] The option to define the ELFACESET. {ELFACE/GROUP/ZONE-3D/ZONE-SHELL/ CHAIN/SURFACE-FACE/MERGE/SUBTRACT/INTERSECT} ELFACE
ELFACESET is defined from table input.
GROUP
ELFACESET is defined from given Element Group.
ZONE-3D
ELFACESET is defined from given ZONE name and only external 3D element faces are selected.
ZONE-SHELL
ELFACESET is defined from given ZONE name and only SHELL element faces are selected.
CHAIN
ELFACESET is defined according to the normal direction of first element face in the table. All element faces of continuous normal direction with same element type will be filled in table.
SURFACE-FACE
ELFACESET is defined from geometry sufaces or faces.
MERGE
ELFACESET is defined by merging element face sets specified in the table.
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ELFACESET
Sec. 9.2 Element data
SUBTRACT
ELFACESET is defined by subtracting from the TARGET element face set the element face sets specified in the table.
INTERSECT
ELFACESET defined by obtaining the intersection of all element face sets specified in the table.
GROUP If GROUP > 0 and the GROUP is a SHELL element group, all element faces of this group will be included in this ELFACESET. Used only for OPTION = GROUP.
[0]
ZONE Zone name. Used only for OPTION = ZONE-3D/ZONE-SHELL. ANGLE Angle (in degrees) used to determine all continuous normal directions. {0.0 ≤ ANGLE ≤ 90.0} TARGET Label number of target element face set for OPTION = SUBTRACT .
[0.0]
[0]
facei Face number of the element. Used only for OPTION = ELFACE. eli Label number of the element. Used only for OPTION = ELFACE. groupi Label number of the element group. Used only for OPTION = ELFACE. namei Label number of element face set. Used only for OPTION = MERGE/SUBTRACT/INTERSECT (without bodyi) or OPTION = SURFACE-FACE (with bodyi). bodyi Label number of body; if bodyi = 0 , this means that the geometry is a surface. Used only for OPTION = SURFACE-FACE. Auxiliary commands LIST ELFACESET DELETE ELFACESET
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ENODES
Sec. 9.2 Element data
ENODES
SUBSTRUCTURE GROUP NNODES
(ENTRIES EL AUX N1 N2 ... NK) eli auxi n1i n2i n3i n4i ... nki ENODES defines element nodal connectivity for the substructure and element group specified. The defaults are the currently active substructure and element group. NNODES is only used for specifying maximum number of nodes allowed for ADINA GENERAL elements SUBSTRUCTURE [currently active substructure] Label number for the substructure to which subsequent nodal and element data refer. GROUP Element group label number.
[currently active element group]
NNODES [32] Maximum number of nodes allowed for ADINA GENERAL elements. (command line input only). ENTRIES Defines, as column headings, the input for the subsequent tabular entries. Specifies the element nodes for which the global node numbers shall be input. The column heading EL must always be specified first, and the essential and optional nodal headings for each type of element are: eli eli eli eli eli eli eli eli eli eli eli eli
eli Element number within the current substructure and element group.
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Chap. 9 Direct finite element data input
ENODES
auxi n1i , n2i , n3i ,... , nki The global node numbers defining the element in the order given by ENTRIES. Note:
Node auxi is required by the BEAM, ISOBEAM and PIPE elements.
Note:
The spring element is defined by n1i, id1i, n2i and id2i, where id1i and id2i are the global degrees of freedom. Parameter id2i is ignored when n2i=0
Node numbering The node numbering convention and other pertinent information for the truss, beam, isobeam, pipe, plate and general elements are described in the corresponding sections in the Theory and Modeling Guide, Volume I: ADINA, as follows: Element TRUSS BEAM ISOBEAM PIPE PLATE GENERAL
Section 2.1 2.4 2.5 2.8 2.6 2.9.1
The node numbering for the TWODSOLID/FLUID2, THREEDSOLID/FLUID3, SHELL and SPRING elements is explained in the following sections. 1. TWODSOLID/FLUID2 elements The TWODSOLID/FLUID2 elements are triangles and quadrilaterals. Their nodes are numbered as shown in Fig. ENODES-1. 2. THREEDSOLID/FLUID3 elements The THREEDSOLID/FLUID3 elements fall into two categories based on node numbering: (a)
the brick elements (4-, 8-, 20-, 21- and 27-node) and degenerate elements formed by collapsing the 8-, 20- and 27-node brick elements, and
(b)
the tetrahedral elements (4-, 10- and 11-node).
Fig. ENODES-2 shows the node numbering convention of the 27-node brick element. Note that node 21 is in the center of the element. The elements that are based on the 27-node brick must be numbered according to the convention shown in the figure, e.g., a node number that is reserved for a vertex cannot be used to number a node on an edge. Fig. ENODES-3 shows the node numbering for elements based on the 27-node brick.
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ENODES
Sec. 9.2 Element data
•
The 21-, 20-, and 8-node bricks (Fig. ENODES-3(f), (d) and (a) respectively) result when the nodes on the element faces, the node at the element center, and the nodes on the element edges are progressively left out.
•
The 6-node prism (Fig. ENODES-3(b)) and its corresponding numbering are obtained by collapsing one face (1-4-8-5) of the 8-node brick.
•
The 15-node prism (Fig. ENODES-3(c)) and its corresponding numbering are obtained by collapsing one face (1-4-8-5) of the 20-node brick.
•
The 13-node pyramid (Fig. ENODES-3(e)) and its corresponding numbering are obtained from the 20-node brick by collapsing one face (1-2-3-4), and then collapsing the edge so formed into the apex of the pyramid.
•
The 14-node pyramid (Fig. ENODES-3(g)) and its corresponding numbering are obtained from the 27-node brick by collapsing one face (1-2-3-4), and then collapsing the edge so formed into the apex of the pyramid; nodes 21 – 26 are not used, leaving only the last node (27) on the base of the pyramid.
The 4-, 10- and 11-node tetrahedral elements are numbered as shown in Fig. ENODES-4. 3. SHELL elements Fig. ENODES-5 shows the node numbering conventions for SHELL elements. •
In midsurface nodes representation (Fig. ENODES-5(a)), node numbers 13 – 16 are always reserved for element interior nodes. Therefore, in the case of a 9-node shell element defined using midsurface nodes, the nodes defined are the 1 – 4 at the vertices, 5 – 8 on the edges and 13 in the center of the element. The center node is defined by nodes 13 and 29 if the 9-node shell element is defined using top-bottom nodes representation.
•
In top-bottom nodes representation (Fig. ENODES-5(b)), the element interior nodes are numbered 13 – 16 on the top surface and 29 – 32 on the bottom surface. Each top surface node has a dual bottom surface node. Nodes 1 – 16 are on the top surface, or on the middle surface if the dual node on the bottom surface is not present. Nodes 17 – 32 are on the bottom surface.
•
Triangular shell elements are obtained by degeneration of these quadrilateral shell elements, that is, by assigning nodes 1 and 4 (also nodes 17 and 20 if applicable) to the same global number. Note that for triangular shell elements, nodes 8 and 12 (also nodes 24 and 28 if applicable) are not used. Further, interior nodes are not allowed. Some examples of triangular shell elements using midsurface node representation are shown in Fig. ENODES-6.
4. Nonlinear SPRING elements For nonlinear springs, the stiffness of the spring can change as functions of the displacement
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Chap. 9 Direct finite element data input
ENODES
between 2 nodes (or node to ground). The 2 categories of nonlinear spring are --
material nonlinear only (MNO) spring (specify NONLINEAR=MNO in EGROUP SPRING command)
--
geometric nonlinear spring (specify NONLINEAR=GEOM in EGROUP SPRING command)
Option 1 (MNO): The 2 nodes of the spring are initially coincident. The spring action is assumed to act always in the global directions regardless of the current relative positions of the 2 nodes. Figure ENODES-7 illustrates the use, where n1 and n2 have moved apart but the spring stiffness continues to act into the global directions. To use this spring option, specify ENODES el n1 id1 n2 where id1 = 1, 2 and 3 indicates global X, Y and Z directions respectively. id1 = 4, 5, and 6 for torsional springs. If n2 = 0, then a grounded spring is defined. Option 2 (MNO): The 2 nodes of the spring are initially coincident. The spring action is assumed to act always in an arbitrary direction specified by the user. Figure ENODES-8 illustrates the use of this option. To use this spring option, the EDATA command is used to specify the spring action direction. ENODES el n1 id1 n2 id2 EDATA el ax ay az ax, ay, az are vector components in the global X, Y, Z directions. If n2 = 0, then a grounded spring is defined. For translational spring, specify id1 = 0 and id2 = 0. For torsional spring, specify id1 = 0 and id2 = 1.
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ENODES
Sec. 9.2 Element data
Option 3 (MNO): The 2 nodes of the spring are initially not coincident. The spring action is assumed to act always in the direction connecting the original positions of the two nodes. Figure ENODES-9 illustrates the use of this option. To use this spring option, specify ENODES el n1 id1 n2 id1 = 1 for translational spring and id1 = 4 for torsional spring. If OPTION=TRANSVERSE is specified in EGROUP SPRING command, then the spring action acts in the transverse directions to n1 to n2 direction. Option 4 (Geometric Nonlinear): The 2 nodes of the spring are initially not coincident. The spring action is assumed to act in the direction connecting the current positions of the two nodes. Hence, the spring direction changes as the position of the two nodes changes. Figure ENODES-10 illustrates the use of this option. To use this spring option, specify ENODES el n1 id1 n2 id1 = 1 for translational spring and id1 = 4 for torsional spring. Examples of input for options 1 to 3 are given in the following tables. Table ENODES-1 covers the translational spring elements, and the Table ENODES-2 covers the torsional spring elements. Auxiliary commands LIST ENODES DELETE ENODES
FIRST LAST SUBSTRUCTURE GROUP FIRST LAST SUBSTRUCTURE GROUP NODE-DELETE
NODE-DELETE {YES/NO} allows for the deletion of unattached nodes along with the element deletion. The default is YES.
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ENODES
3
3
l
3
l
l
6l 1l
l
1l
2
l l
5
6l 7 l l
l
4
2
l l
5 l
l
l
4
1
2
4
l
l
l
l
l
7
l
3
l
4
3
l
l
l
l
9
l
6
3
1
8
l
8
5 l
2
l
1
l
6
5
l
2
l
l
1
2l
l
(a) 3-, 6- & 7-node triangles
7
4
(b) 4-, 8- & 9-node quadrilaterals
Fig. ENODES-1: Node numbering of 2-D elements 3l
10
l
11l
26
19l
4l
8
1 14
l
l
l
25
l
27
l
2
9l
l
21l
7 l 15l
23
12
l
24 l 20 l
l
l
l
22
l l
13
l
l
11 26l 19 l l 23l 24 l l 21 l 14 7l l
l
17l
16
18
10
3l
6
1, 4, 12
l
l
l
27
15
l
9
l
l
2
l
18
22 l
6
l
13
l
5, 8, 16
17, 20, 25
l
5 Nodes 1 to 8 are at element vertices. Nodes 9 to 20 are on element edges. Node 21 is at the center of the element. Nodes 22 to 27 are on the element faces.
Figure ENODES-2: Node numbering convention for the 27-node brick element
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Sec. 9.2 Element data
ENODES
3l
l
3
2
l
l
1
4l
l
l1,2,3,4
2
l
1, 4 7l
7l
l
7
6
l
l
5, 8
8
10 l
l
5
19 l 7l
l
11l
l l
4
18
l
1, 4, 12 17, 20l l 14 l 15
6
15
8
l
l
19 l
18
20 l
l
14
l
6
l
8l
l
l
l
16
l
13
10
l
l
12
1
l
14
l
l
l l
16
20 l 15
l l
5
(g) 21-node brick
13
l
6
6
l l
l
13
l
7l
l
17
18
14
l
6
l
l
8l
l
1,2,3,4, 9,10,11,12
19 l
l
14
(f) 13-node pyramid l
17l
18
5
2
18
l
17
l
16
5
l
21 l
7
9l
l
l
7l
15
17l
l
l
1,2,3,4, 9,10,11,12
l
2
(e) 20-node brick
15 l
8
9l
1
l
3
l
12
7
(d) 15-node prism
20 l
(c) 5-node pyramid
l
l
20 l
5, 8, 16
19l
l
l
13
4l
5
19l
l
11l
l
10
3
9l
11
8l
(b) 8-node brick
2
l
6
l
6
l
l
(a) 6-node prism
3l
l
27
l
13
l
16
l
5
(h) 14-node pyramid
Figure ENODES-3: Node numbering of the elements derived from the 27-node brick
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ENODES
Chap. 9 Direct finite element data input
4
4
4
l
l
l
9
l
l
l
1l
l
10l
3
l
10l
8
l
7l l
1l
2
l l
5
l
6 l
1l
2
l
8
l
7l 5
l
3
6
l
2
(c) 11-node tetrahedron
(b) 10-node tetrahedron
(a) 4-node tetrahedron
11
3
9
Figure ENODES-4: Node numbering of tetrahedral elements 2 6
For the 9-node shell, the midsurface center node is local node number 13.
9 14
10
5
15
1
13
3
12
16
7
8
11 4
a) Midsurface nodes
2 6 22
10 26 3 19
9
18 14 30
15 31 16
25 13 29
7 32 23
11 27
b) Top-bottom nodes
4
8
5 21 12
For the 9-node shell, the top-bottom center nodes are local node numbers 13 and 29. 1 17
28
24
20
Figure ENODES-5: Node numbering conventions for the shell element 9-30
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ENODES
Sec. 9.2 Element data
2
2
2
l
l
l
6l 3
l
5
(a) 3-node triangular shell
3l
1, 4
7
3l
1, 4
l
l
l
l
l l
10
6l
(b) 6-node triangular shell
9 l
l
7
l
11
5 l
1, 4 (c) 9-node triangular shell
Figure ENODES-6: Node numbering for some triangular shell elements, midsurface nodes
Z, w
n1 and n2 initially coincident kx = f1(u), ky = f2(v), kz = f3(w) and always acting in global directions X, Y, Z. Here, 3 spring elements are defined for spring action in X, Y and Z directions.
kz n1(0)
n1
n2(0)
n2 ky
kx Y, v
X, u Figure ENODES-7: Nonlinear Spring, Option 1 Z, w ax, ay, az direction
d k n1 n1(0)
n2
n1 and n2 initially coincident k = f(d) spring stiffness between nodes always act in the specified direction ax, ay, az.
Y, v
n2(0) X, u
Figure ENODES-8: Nonlinear Spring, Option 2 ADINA R & D, Inc.
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ENODES
Chap. 9 Direct finite element data input
Z, w
n1(0) and n2(0) indicate the original positions of the two spring nodes. spring stiffness always acts in direction n1(0) to n2(0). line joining n1 to n2(p) is parallel to line joining n1(0) to n2(0).
n2(0) n1(0) n2(p) n1
Y, v
k n2
X, u
Figure ENODES-9: Nonlinear Spring, Option 3
Z, w
n2(0)
n1(0) n2 n1
Y, v
k
X, u Figure ENODES-10: Nonlinear Spring, Option 4
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ENODES
Sec. 9.2 Element data
Different node numbers and noncoincident coordinates
Different node numbers and initially coincident coordinates
Grounded node Z
Z Global direction
Y
X
X n1,n2
n2 U
Global direction
Y
2
2
U1 n1
U n2
id1 = 1
U
1
id1 = 1 n1 1
n1,n2 n1
1
U
U
2
id1 = 2
U
1
2
n1,n2
U U1
id1 = 2
n1
n1 n2
1
ENODES el n1 1 n2 (id2 not used)
U
n2 n1
U id1 = 3
id1 = 3
n1
ENODES el n1 id1 n2 (id2 not used)
ENODES el n1 id1 (id2 not used)
Arbitrary direction a n2 U2
Arbitrary direction n1 a
1
n1,n2
n1
U
ENODES el n1 0 n2 EDATA el ax ay az
0
U 0
1
ENODES el n1 0 0 0 EDATA el ax ay az
Table ENODES-1: Input cases for translational nonlinear spring elements
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ENODES
Chap. 9 Direct finite element data input
Different node numbers and noncoincident coordinates
Different node numbers and initially coincident coordinates
Grounded node Z
Z Global direction
Y
X
X 1
n1,n2
n2 U
Global direction
Y
U 2
2
U n2
n1
id1 = 4
U
1
id1 = 4
n1 1
n1,n2 n1
U
1
U
2
U
id1 = 5
U
ENODES el n1 4 n2 (id2 not used)
1
2
n1,n2
U U1
id1 = 5
n1
n1 n2
1
n2 n1
U id1 = 6
id1 = 6
n1
ENODES el n1 id1 n2 (id2 not used)
ENODES el n1 id1 (id2 not used)
Arbitrary direction a n2 U2
Arbitrary direction n1 a
1
n1,n2
n1
U
ENODES el n1 0 n2 EDATA el ax ay az
0
U 0
1
ENODES el n1 0 0 1 EDATA el ax ay az
Table ENODES-2: Input cases for torsional nonlinear spring elements
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Sec. 9.2 Element data
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MESH-CONVERT
Chap. 9 Direct finite element data input
MESH-CONVERT
IN OUT ELEMENT-TYPE GROUP SKEW LOAD-INIT NCOINCIDE
Converts 2-D solid, 3-D solid or shell elements by changing the number of nodes of the element. Element Type
Original Element
Converted Element
2-D Solid
8-node quadrilateral
9-node quadrilateral
6-node triangular
7-node triangular
Shell
8-node quadrilateral
9-node quadrilateral
3-D Solid
20-node brick
27-node brick
10-node tetrahedral
11-node tetrahedral
IN OUT
These parameters are currently not used. ELEMENT-TYPE [TWODSOLID] Selects the type of element to be converted. {TWODSOLID/THREEDSOLID/SHELL/ ALL} GROUP [ALL] Selects the element group to be converted. GROUP = ALL means all element groups will be converted. {ALL/>0} SKEW [NO] Indicates whether skew system is assigned to newly created nodes if all other nodes on the element face are assigned a skew system.{NO/YES} LOAD-INIT [NO] Indicates whether existing nodal-based prescribed loads (e.g., displacement, temperature, velocity) and initial conditions are applied on the newly created nodes.{NO/YES} Note:
- Load or initial condition will only be applied on a created mid-surface node if all the eight nodes on the element face have the load or initial condition applied. - If a load or initial condition is applied after this command, it will not be applied on the newly created nodes. Hence, this command should normally be used at the end of model creation.
NCOINCIDE [NEW] Indicates whether nodal coincidence is checked with newly generated nodes or all existing nodes. When a node already exists at a location, no new node will be created. {NEW/ALL} NEW ALL
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ENODES-INTERFACE
ENODES-INTERFACE
Sec. 9.2 Element data
SUBSTRUCTURE GROUP
(ENTRIES EL N1 N2 N3 ... NK) eli n1i n2i n3i ... nki Defines fluid-structure interface elements when potential-based fluid elements are connected to solid elements. SUBSTRUCTURE [currently active substructure] Label number for the substructure to which subsequent nodal and element data refer. GROUP Element group label number.
[currently active element group]
ENTRIES Defines, as column headings, the input for the subsequent tabular entries. Specifies the element nodes for which the global node numbers shall be input. The column heading EL must always be specified first, and the essential and optional nodal headings for each type of element are: eli n1i ... eli n1i ...
n3i n9i
FLUID2-interface elements FLUID3-interface elements
eli Element number within the current substructure and element group. n1i n2i n3i... nki The global node numbers defining the element in the order given by ENTRIES. Auxiliary commands LIST ENODES-INTERFACE DELETE ENODES-INTERFACE
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EDATA
EDATA
SUBSTRUCTURE GROUP UNDEFINED
eli materiali areai printi savei tbirthi tdeathi epsini gapwidthi intloci (for TRUSS elements) eli materiali thicki beti printi savei tbirthi tdeathi intloci betii itrii (for TWODSOLID elements) eli materiali ielxi printi savei tbirthi tdeathi intloci maxesi maxesii itrii (for THREEDSOLID elements) eli materiali sectioni endreleasei printi savei tbirthi tdeathi intloci epsini rigid1i rigid2i (for BEAM elements) eli materiali sectioni printi savei tbirthi tdeathi intloci epaxli ephoopi (for ISOBEAM elements) eli materiali thicki beti printi savei tbirthi tdeathi intloci betii meps11i meps22i meps12i flex11i flex22i flex12i (for PLATE elements) eli materiali beti printi savei tbirthi tdeathi intloci betii ithsi eps11i eps22i eps12i eps13i eps23i geps11i geps22i geps12i geps13i geps23i failurei (for SHELL elements) eli materiali sectioni printi savei tbirthi tdeathi intloci epsini (for PIPE elements) eli matrixseti printi savei (for GENERAL elements) eli propertyseti printi savei axi ayi azi tbirthi tdeathi (for SPRING elements) eli materiali printi savei tbirthi tdeathi intloci ifrei itrii (for FLUID2 elements) eli materiali ielxi printi savei tbirthi tdeathi intloci ifrei itrii (for FLUID3 elements) Specifies property data associated with individual elements in a group.
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EDATA
Sec. 9.2 Element data
SUBSTRUCTURE [currently active substructure] Label number for the substructure to which subsequent element data refer. GROUP Element group label number.
[currently active group]
UNDEFINED Indicates what action is taken if element specified in data line is not defined. {IGNORE/ERROR} IGNORE ERROR -
[IGNORE]
Program ignores any undefined element specified. Program issues input error for undefined element and continues.
eli Element label number. materiali [element group default] Material number. The material type must be the same as the default material type for the element group. printi [DEFAULT] Controls printout of element results. The value DEFAULT corresponds to that given for PRINTOUT PRINTDEFAULT. {YES/NO/DEFAULT} savei [DEFAULT] Controls saving of element results to porthole file. The value DEFAULT corresponds to that given for PORTHOLE SAVEDEFAULT. tbirthi tdeathi Element birth and death times, respectively.
[0.0] [0.0]
intloci Integration point coordinates printout flag.
[0]
0
No printing of integration point coordinates.
1
Print integration point global coordinates.
areai [0.0] Cross-sectional area. A 0.0 value indicates the element has the same cross-sectional area as the element with the lowest label number in the group.
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Chap. 9 Direct finite element data input
EDATA
thicki [0.0] Element thickness. A 0.0 value indicates the element has the same thickness as the element with the lowest label number in the group. ielxi This parameter is obsolete. ithsi [0] Indicates whether the transverse shear adjustment feature is used (1) or not (0). This feature is only available for elastic shells. {0/1} maxesi Material axes label number. See AXES-NODES. beti Material angle for orthotropic materials.
[0] [0.0]
sectioni Cross-section label number. See CROSS-SECTION.
[0]
endreleasei End release label number. See ENDRELEASE.
[0]
propertyseti Propertyset label number. See PROPERTYSET.
[element group default]
matrixseti Matrix set label number. See MATRIXSET.
gapwidthi [0.0] Initial gap width of element. The gap option is used only for the 2-node TRUSS element with a PLASTIC-BILINEAR or PLASTIC-MULTILINEAR material model. failurei Label number of failure model.
[0]
ifrei This option is not supported from Version 8.0 onwards.
[0]
itrii Collapsed element indicator.
[0]
0 -1
Collapsed quadrilateral or hexahedral element. True triangular or tetrahedral element.
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EDATA
axi ayi azi Direction of grounded spring element.
[0.0] [0.0] [0.0]
rigid1i [0.0] rigid2i [0.0] Length of rigid end zones at the start (rigid1) and/or end (rigid2) of a BEAM element. See EGROUP BEAM. Note:
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To define shell element thickness command ELTHICKNESS should be used.
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
COPY-ELEMENT-NODES
Sec. 9.2 Element data
COPY-ELEMENT-NODES
FROM TO
Copies over all elements and nodes from one finite element analysis program to another finite element analysis program, creating new element groups for the destination program. If, for a particular element group type, there is no equivalent group type available in the destination program the source group will not be copied. FROM The source finite element analysis program. {ADINA/ADINA-T/ADINA-F}
[ADINA]
TO The destination finite element analysis program. {ADINA/ADINA-T/ADINA-F} The following table indicates the source-destination element type mapping used by this command: SOURCE
DESTINATION
ADINA
ADINA-T
ADINA-F
TRUSS TWODSOLID THREEDSOLID BEAM ISOBEAM PLATE SHELL PIPE SPRING GENERAL FLUID2 FLUID3
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
DELETE-FE-MODEL
DELETE-FE-MODEL
Sec. 9.2 Element data
PROGRAM
Deletes all finite element data associated with a particular analysis program from the model database - including element groups, elements, nodes, contact groups, contact-surfaces, and contact segments. PROGRAM The finite element analysis program for which all data is to be deleted. ADINA-T/ADINA-F}
ADINA R & D, Inc.
[ADINA] {ADINA/
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REVOLVE
REVOLVE
NAME EGROUP XA YA ZA X0 Y0 Z0 ANGLE NEREV NODES NFIRST EFIRST NCOINCIDE NTOLERANCE DELETE-EGROUP LOADS-ELEMENT AXES-ORTHOTROPIC AXES-INITIAL BC-FIXITY RBAR-NODESET RBAR-ELEMSET RBAR-EGROUP RBAR-TYPE RBAR-SECTION RBAR-MATERIAL CGROUP CNAME DELETE-CGROUP RBAR-AREA ALL-GROUP
Generates THREEDSOLID or FLUID3 elements by revolving 2D elements about an axis. The rule for generating a new element group type is TWODSOLID
>
THREEDSOLID
FLUID2
>
FLUID3
NAME [current highest element group label + 1] Element group label number of the volume elements. If NAME already exists, it must be a THREEDSOLID or FLUID3 element group. EGROUP Previously defined 2D element group label. XA YA ZA Components of the rotation axis direction.
[0.0] [0.0] [0.0]
X0 Y0 Z0 Global coordinates of the origin of the axis of rotation.
[0.0] [0.0] [0.0]
ANGLE Angle of rotation (in degrees). Note: ANGLE must be in the range <-360,360>. The sign of the angle is given by considering the right hand rule. NEREV The number of elements in the direction of rotation.
[1]
NODES Number of nodes for the revolved 3D elements. {0/8/20/27}
[0]
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REVOLVE
Sec. 9.2 Element data
If NODES=0, then the following rule applies: Max. number of nodes in 2D element group 4 8 9
Number of nodes in 3D element group 8 20 27
NFIRST The starting node label for the generated nodes.
[1]
EFIRST The starting element label for the generated elements.
[1]
NCOINCIDE [NO] Indicates whether the locations of new nodes generated are compared with existing nodes. If NCOINCIDE=YES, then the location of generated generated nodes will be checked against existing nodes. For each generated node, if it lies within the tolerance (specified by NTOLERANCE) of an existing node, no new node will be created. {YES/NO} NTOLERANCE [1.0E-5] If NCOINCIDE=YES parameter provides a tolerance for checking the global coordinates of a location againts existing nodes. DELETE-EGROUP [YES] Allows to preserve or delete original 2D element group, after the volume element group is generated. {YES/NO} LOADS-ELEMENT [NO] Indicates whether element loading acting on the edges of the 2D elements will be converted to element loadings on the faces of the 3D elements. {NO/YES} AXES-ORTHOTROPIC [NO] Indicates whether the material axis systems of the 2D elements will be converted to initial strain axis systems for 3D elements. {NO/YES} AXES-INITIALSTRAIN [NO] Indicates whether the initial strain axis systems of the 2D elements to 3D elements will be converted to initial strain axis systems for the 3D elements. {NO/YES} BC-FIXITY [NO] Indicates whether fixity boundary conditions will be assigned to the generated nodes corresponding to the fixity conditions on the original nodes. {NO/YES} ADINA R & D, Inc.
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Chap. 9 Direct finite element data input
REVOLVE
RBAR-NODESET [0] Label number of a node set defined by the command NODESET. If this parameter references a node set that is defined, truss or beam elements (as specified by parameter RBAR-TYPE) will be generated by connecting the nodes along the revolved direction. RBAR-ELEMSET [0] Label number of an element set defined by the command ELEMENTSET. If this parameter references an element set that is defined, the elements in the element set will be duplicated in the revolved direction. RBAR-EGROUP [(current highest element group label number) + 1] Label number of an element group for the elements generated from parameter RBARNODESET. Note that elements generated from parameter RBAR-ELEMSET are appended to the existing element group. RBAR-TYPE Specifies the type of element to be generated from parameter RBAR-NODESET. BEAM}
[TRUSS] {TRUSS/
RBAR-SECTION [1] Label number of a cross section to be assigned to beam elements generated from parameter RBAR-NODESET. Note that cross sections can be defined by the command CROSS-SECTION. RBAR-MATERIAL [1] Label number of a material to be assigned to elements generated from parameter RBARNODESET. CGROUP Specifies a 2-D contact group to be used for generating 3-D contact surfaces. Note that only 2-D contact surface elements which are attached to the mesh to be revolved will be used for generating 3-D contact surface elements. CNAME [(current highest contact group label number) + 1] Label number of 3-D contact group that will contain the generated 3-D contact surface elements. If CNAME already exists (it must be a 3-D contact group), the generated contact surface elements will be added to the existing contact group. DELETE-CGROUP [NO] Indicates whether the 2-D contact group will be deleted after the 3-D contact surface elements are generated. When all the contact surfaces in the 2-D contact group has been used to generate the necessary 3-D contact surfaces, the parameter should be set to YES. {YES/ NO}
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REVOLVE
Sec. 9.2 Element data
RBAR-AREA [1.0] Specifies the cross-section area for truss elements generated from parameter RBARNODESET. ALL-GROUP Defines whether all groups are acted upon by this command. {NO/YES}
[NO]
NO
Revolve only the specified group
YES
Revolve all applicable element groups and contact groups. Parameters NAME, EGROUP, CGROUP and CNAME are ignored.
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SWEEP
Chap. 9 Direct finite element data input
SWEEP
NAME EGROUP DX DY DZ NESWP NODES NFIRST EFIRST NCOINCIDE NTOLERANCE DELETE-EGROUP LOADS-ELEMENT AXES-ORTHOTROPIC AXES-INITIAL BC-FIXITY RBAR-NODESET RBAR-ELEMSET RBAR-EGROUP RBAR-TYPE RBAR-SECTION RBAR-MATERIAL CGROUP CNAME DELETE-CGROUP RBAR-AREA LINE ALIGNMENT ALL-GROUP
Generates a volume of 3D elements by extruding 2D elements along a vector or a line. The rule for generating a new element group type is TWODSOLID
>
THREEDSOLID
FLUID2
>
FLUID3
NAME [current highest element group label + 1] Element group label number of the volume elements. If NAME already exists, it must be a THREEDSOLID or FLUID3 element group. EGROUP Previously defined 2D element group label. DX DY DZ Vector components defining the direction of extrusion.
[0.0] [0.0] [0.0]
NESWP The number of elements in the direction of extrusion.
[1]
NODES Number of nodes for the extruded 3D elements. {0/8/20/27} If NODES=0, then the following rule applies
[0]
Max. number of nodes in 2D element group 4 8 9 NFIRST The starting node label for the generated nodes.
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Number of nodes in 3D element group 8 20 27 [1]
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
SWEEP
Sec. 9.2 Element data
EFIRST The starting element label for the generated elements.
[1]
NCOINCIDE [NO] Indicates whether the locations of new nodes generated are compared with existing nodes. If NCOINCIDE=YES, then the location of generated generated nodes will be checked against existing nodes. For each generated node, if it lies within the tolerance (specified by NTOLERANCE) of an existing node, no new node will be created. {YES/NO} NTOLERANCE [1.0E-5] If NCOINCIDE=YES parameter provides a tolerance for checking the global coordinates of a location againts existing nodes. DELETE-EGROUP [YES] Allows to preserve or delete original 2D element group, after the volume element group is generated. {YES/NO} LOADS-ELEMENT [NO] Indicates whether element loading acting on the edges of the 2D elements will be converted to element loadings on the faces of the 3D elements. {NO/YES} AXES-ORTHOTROPIC [NO] Indicates whether the material axis systems of the 2D elements will be converted to initial strain axis systems for 3D elements. {NO/YES} AXES-INITIALSTRAIN [NO] Indicates whether the initial strain axis systems of the 2D elements to 3D elements will be converted to initial strain axis systems for the 3D elements. {NO/YES} Note:
We use the command SWEEP to be consistent with BODY SWEEP command for extrusion along a vector or sweeping along a line. Using the more general term SWEEP allows this command to be extended for sweeping 2D elements along a line to form 3D elements.
BC-FIXITY [NO] Indicates whether fixity boundary conditions will be assigned to the generated nodes corresponding to the fixity conditions on the original nodes. {NO/YES} RBAR-NODESET [0] Label number of a node set defined by the command NODESET. If this parameter references a node set that is defined, truss or beam elements (as specified by parameter RBAR-TYPE) will be generated by connecting the nodes along the swept direction.
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SWEEP
RBAR-ELEMSET [0] Label number of an element set defined by the command ELEMENTSET. If this parameter references an element set that is defined, the elements in the element set will be duplicated in the swept direction. RBAR-EGROUP [(current highest element group label number) + 1] Label number of an element group for the elements generated from parameter RBARNODESET. Note that elements generated from parameter RBAR-ELEMSET are appended to the existing element group. RBAR-TYPE [TRUSS] Specifies the type of element to be generated from parameter RBAR-NODESET. {TRUSS/ BEAM} RBAR-SECTION [1] Label number of a cross section to be assigned to beam elements generated from parameter RBAR-NODESET. Note that cross sections can be defined by the command CROSS-SECTION. RBAR-MATERIAL [1] Label number of a material to be assigned to elements generated from parameter RBARNODESET. CGROUP Specifies a 2-D contact group to be used for generating 3-D contact surfaces. Note that only 2-D contact surface elements which are attached to the mesh to be swept will be used for generating 3-D contact surface elements. CNAME [(current highest contact group label number) + 1] Label number of 3-D contact group that will contain the generated 3-D contact surface elements. If CNAME already exists (it must be a 3-D contact group), the generated contact surface elements will be added to the existing contact group. DELETE-CGROUP [NO] Indicates whether the 2-D contact group will be deleted after the 3-D contact surface elements are generated. When all the contact surfaces in the 2-D contact group has been used to generate the necessary 3-D contact surfaces, the parameter should be set to YES. {NO/ YES} RBAR-AREA [1.0] Specifies the cross-section area for truss elements generated from parameter RBARNODESET.
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SWEEP
Sec. 9.3 Boundary conditions
LINE Line label of the line used for sweeping. ALIGNMENT Specifies the alignment of the 2D meshed face during sweeping. NORMAL PARALLEL
[NORMAL]
: 2D face normal is at fixed angle to line tangent. : 2D face normal always points to the same direction.
ALL-GROUP Defines whether all groups are acted upon by this command. {NO/YES}
[NO]
NO
Revolve only the specified group
YES
Revolve all applicable element groups and contact groups. Parameters NAME, EGROUP, CGROUP and CNAME are ignored.
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BOUNDARIES
BOUNDARIES
SUBSTRUCTURE
nodei uxi uyi uzi rxi ryi rzi phii ovalizationi warpingi porei temperaturei beam-warpi Assigns fixed/free boundary conditions to nodes. All of the nodes belong to the specified substructure. SUBSTRUCTURE Substructure label number.
[current substructure]
nodei Node label number. uxi [FREE] uyi [FREE] uzi [FREE] Boundary conditions applied to displacement degrees of freedom. {FIXED/FREE} rxi ryi rzi Boundary conditions applied to rotation degrees of freedom. {FIXED/FREE}
[FREE] [FREE] [FREE]
phii [FREE] Boundary conditions applied to the fluid potential degree of freedom. {FIXED/FREE} ovalizationi [FREE] warpingi [FREE] Boundary conditions applied to the pipe ovalization and warping degrees of freedom. {FIXED/FREE} porei [FREE] Boundary conditions applied to pore pressure degree of freedom. {FIXED/FREE} temperaturei [FREE] Boundary conditions applied to temperature degree of freedom. Temperature degree of freedom applies only to heat transfer or thermo-mechanical coupled analysis. {FIXED/ FREE}
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BOUNDARIES
Sec. 9.3 Boundary conditions
beam-warpi Boundary conditions applied to beam-warp degree of freedom. {FIXED/FREE}
[FREE]
Auxiliary commands LIST BOUNDARIES FIRST LAST SUBSTRUCTURE OPTION Option defines listing nodes: input nodes or all model nodes. {INPUT/MODEL} DELETE BOUNDARIES
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FIRST LAST SUBSTRUCTURE
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CONSTRAINT-NODE
CONSTRAINT-NODE
Sec. 9.3 Boundary conditions
NAME SLAVENODE SLAVEDOF GENERALIZEDCONSTRAINT
masternodei masterdofi betai slavenodei slavedofi Specifies a constraint equation which expresses a slave (dependent) degree of freedom as a linear combination of a set of master (independent) degrees of freedom. A constraint equation can only reference nodes in the main structure. NAME [(highest constraint equation label number) + 1] The label number of the constraint equation. SLAVENODE The label number of the slave node. SLAVEDOF The degree of freedom associated with the slave node. {X-TRANSLATION/Y-TRANSLATION/Z-TRANSLATION/X-ROTATION/ Y-ROTATION/Z-ROTATION/FLUID-POTENTIAL/TEMPERATURE} SLAVEDOF = TEMPERATURE is only available when MASTER TMC = YES. GENERALIZED-CONSTRAINT Generate generalized constraints instead of standard constraints. {NO/YES}
[NO]
masternodei The label number of the master node for the “i”th independent term of the constraint equation. masterdofi The degree of freedom of the master node for the “i”th independent term of the constraint equation. Allowable values are the same as for SLAVEDOF. betai The coefficient of the “i”th independent term of the constraint equation.
[1.0]
slavenodei The label number of the slave node. slavedofi The degree of freedom associated with the slave node.
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Auxiliary commands LIST CONSTRAINT-NODE DELETE CONSTRAINT-NODE
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FIRST LAST FIRST LAST
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
RIGIDLINK-NODE
RIGIDLINK-NODE
Sec. 9.3 Boundary conditions
NAME SLAVENODE MASTERNODE DISPLACEMENTS DOFSI
slavenodei masternodei displacementsi Specifies a rigid link between two nodes. A rigid link can only be specified between nodes in the main structure. NAME [(highest rigid link label number) + 1] The label number of the rigid link. SLAVENODE The label number of the slave node. MASTERNODE The label number of the master node. DISPLACEMENTS [DEFAULT] Selects kinematic formulation for rigid link. See the Theory and Modeling Guide. SMALL
Small displacement formulation.
LARGE
Large displacement formulation.
DEFAULT
As set by KINEMATICS.
slavenodei The label number of the slave node. masternodei The label number of the master node. displacementsi [DEFAULT] Selects kinematic formulation for rigid link. Note that displacementi = DEFAULT means that the formulation specified in the KINEMATICS command is used. See the Theory and Modeling Guide. {DEFAULT/SMALL/LARGE} DOFSI [123456] Specifies the slave degrees of freedom (dof) to be constrained to the master node. DOFSI must contain 1 to 6 digits ranging from 1 to 6. Dofs 1, 2, 3 indicate X, Y, Z translations and 4, 5, 6 indicate X, Y, Z rotations. Auxiliary commands LIST RIGIDLINK-NODE DELETE RIGIDLINK-NODE ADINA R & D, Inc.
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Chap. 9 Direct finite element data input
OVALIZATION-CONSTRAINT NODE
OVALIZATION-CONSTRAINT NODE
TYPE GROUP
nodei elementi Enforces the zero-slope-of-pipe-skin condition in the longitudinal direction for pipe element nodes. This condition is applicable in the case of a rigid flange (TYPE = FLANGE) or when symmetry is to be enforced (TYPE = SYMMETRY). These conditions apply to pipe element nodes for the element group specified. See the Theory and Modeling Guide. TYPE
[FLANGE]
FLANGE
The flange condition is applied at the specified nodes. Both ovalization and warping at these nodes are suppressed.
SYMMETRY
The symmetry condition is applied at the specified nodes. The ovalization at these nodes is left free but the warping is suppressed.
GROUP [currently active group] The element group for each pipe element node specified in this command. nodei Label number of a node. elementi Label number of the element that contains the node. Auxiliary commands LIST OVALIZATION-CONSTRAINT NODE DELETE OVALIZATION-CONSTRAINT NODE
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FIRST LAST TYPE GROUP FIRST LAST TYPE GROUP
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
FSI-FACE
Sec. 9.3 Boundary conditions
FSI-FACE celli n1i n2i
NAME DIMENSION …
n16i
Defines fsi boundary using element face node for ADINA. NAME [(current highest fsi boundary label number) + 1] Label number of the fluid-structure-boundary to be defined. DIMENSION Dimension of FSI boundary. {3/2}
[3]
celli Label of a cell on FSI boundary. n1i…n16i Cell’s node numbers. Auxiliary commands LIST FSI-FACE DELETE FSI-FACE
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FIRST LAST FIRST LAST
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APPLY CONCENTRATED-LOADS
APPLY CONCENTRATED-LOADS
SUBSTRUCTURE REUSE
nodei directioni factori ncuri artmi nodauxi Applies concentrated loads to nodes. The magnitude of the load is given by entry “factori”, which may be modified (except when load cases are employed) via a timefunction given by entry “ncuri”. Several concentrated loads can be defined for the same node and direction. In this case the loads are added. SUBSTRUCTURE [currently active substructure] Identifying number for the substructure to which subsequent nodes refer. REUSE [currently active reuse] Identifying number for the reuse to which subsequent nodes refer. nodei The label number of a node to which the load is to be applied. directioni The direction in which the load acts. 1 2 3 4 5 6 7 8
x-translation force (global or skew). y-translation force (global or skew). z-translation force (global or skew). x-rotation moment (global or skew). y-rotation moment (global or skew). z-rotation moment (global or skew). Follower force acting from nodauxi to nodei. Follower moment about the direction from nodauxi to nodei.
factori Multiplying factor, giving load intensity. ncuri The label number of a time function.
[1.0] [1]
artmi [0.0] The arrival time associated with time dependent loads. See the Theory and Modeling Guide.
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APPLY CONCENTRATED-LOADS
Sec. 9.4 Loads
nodauxi Auxiliary node used to control follower loads. See the Theory and Modeling Guide.
nodei directioni factori ncuri artmi iddli unloadi timeui forceui ncurui Specifies prescribed displacements applied to nodes. The magnitude of the displacement is given by entry “factori”, which may be modified (except when load cases are employed) via a timefunction given by entry “ncuri”. Several prescribed displacements can be defined for the same node and direction; in this case the displacements are averaged. SUBSTRUCTURE [currently active substructure] Identifying number for the substructure to which subsequent nodes refer. REUSE [currently active reuse] Identifying number for the reuse to which subsequent nodes refer. nodei The label number of the node for which the displacement is to be prescribed. directioni The direction in which the displacement is prescribed. See the Theory and Modeling Guide. 1 2 3 4 5 6 11 - 16 21 - 26
x-translation (global or skew) y-translation (global or skew) z-translation (global or skew) x-rotation (global or skew) y-rotation (global or skew) z-rotation (global or skew) Ovalization degrees of freedom. Warping degrees of freedom.
factori Multiplying factor, giving displacement magnitude. ncuri The label number of a time function. artmi The arrival time associated with time dependent prescribed displacements.
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AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
APPLY DISPLACEMENTS
Sec. 9.4 Loads
iddli [0] Specifies whether the prescribed displacement is applied to the original configuration or the deformed configuration for a restart analysis. 0 1
original configuration deformed configuration
unloadi Specifies the type of unloadng for prescribed displacement.{TIME/FORCE/NO}
[NO]
timeui [0.0] If unloadi=TIME, this specifies the time at which unloading of prescribed displacement starts. forceui If unloadi=FORCE, this specifies the force (or reaction) value at the prescribed displacement at which unloading starts. ncurui Label number of a time function for the unloading of prescribed displacement.
APPLY ELECTROMAGNETIC-LOADS node1i node2i ncuri artmi iddli Applies electromagnetic loads to nodes. The nodes must be part of the main structure. The load corresponds to electromagnetic forces induced by short-circuit currents flowing between pairs of nodes. The magnitude of the short-circuit current is governed by a timefunction given by entry “ncuri”. node1i node2i A pair of nodes between which a short-circuit current flows. ncuri [1] The label number of a time function, giving the time dependent value of the short-circuit current. artmi The arrival time associated with time dependent loads. iddli Indicator for deformation-dependent loading. {0/1} 0
Deformation-independent.
1
Deformation-dependent.
[0.0] [0]
Auxiliary commands LIST APPLY ELECTROMAGNETIC-LOADS DELETE APPLY ELECTROMAGNETIC-LOADS
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APPLY PIPE-INTERNAL-PRESSURES
Sec. 9.4 Loads
APPLY PIPE-INTERNAL-PRESSURES nodei factori ncuri artmi Applies internal pressures to pipe element nodes. The nodes must be part of the main structure. The magnitude of the pipe internal pressure is given by entry “factori”, which may be modified by a time function given by entry “ncuri”. Pipe internal pressure loading cannot be used in a load case, nor when automatic load displacement control is employed. Several pipe internal pressure loads can be defined for the same node; in this case the loads are averaged. nodei The label number of the node to which the load is to be applied. factori Multiplying factor giving the internal pressure magnitude. ncuri The label number of a time function. artmi The arrival time associated with time dependent loads.
[1.0] [1] [0.0]
Auxiliary commands LIST APPLY PIPE-INTERNAL-PRESSURES DELETE APPLY PIPE-INTERNAL-PRESSURES
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APPLY TEMPERATURES
APPLY TEMPERATURES nodei factori ncuri artmi This command defines temperatures applied to nodes. The actual applied temperature is the reference temperature plus the temperature applied in this command. The reference temperature is defined in command TEMPERATURE-REFERENCE.. Several temperatures can be defined for the same node; in this case the temperatures are averaged. nodei The label number of the node at which the temperature is to be prescribed. factori Multiplying factor. ncuri The label number of a time function. artmi The arrival time associated with time dependent temperatures.
[1.0] [1] [0.0]
Auxiliary commands LIST APPLY TEMPERATURES DELETE APPLY TEMPERATURES
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APPLY TGRADIENTS
Sec. 9.4 Loads
APPLY TGRADIENTS nodei factori ncuri artmi Prescribes temperature gradients at shell element midsurface nodes of the main structure. The magnitude of the temperature gradient (degrees/unit length) is given by entry “factori”, and may be modified by a time function given by entry “ncuri”. Shell midsurface nodes which have no temperature gradient specified will take the value given by TEMPERATUREREFERENCE. Several temperature gradients can be defined for the same node; in this case the temperature gradients are averaged. nodei The label number of a shell midsurface node at which the temperature gradient is prescribed. factori Multiplying factor, giving the temperature gradient at the node. ncuri The label number of a time function. artmi The arrival time associated with time dependent temperature gradients.
[1.0] [1] [0.0]
Auxiliary commands LIST APPLY TGRADIENTS DELETE APPLY TGRADIENTS
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APPLY USER-SUPPLIED-LOADS
Chap. 9 Direct finite element data input
APPLY USER-SUPPLIED-LOADS
NODE-DEPENDENCE NICONS NRCONS
iconsi rconsi Establishes the presence of user-supplied loads, which are computed using the user-supplied subroutines USERSL and IUSER. See the Theory and Modeling Guide for details regarding these subroutines. NODE-DEPENDENCE
[1]
1
Load contribution calculated in the user-supplied load subroutine for a node depends only on nodal quantities at that node.
2
Load contribution calculated in the user-supplied load subroutine may depend on nodal quantities at other nodes.
NICONS Number of integer constants to be input in the accompanying data lines.
[0]
NRCONS Number of real constants to be input in the accompanying data lines.
[0]
iconsi Integer constant passed to user-supplied subroutine USERSL.
[0]
rconsi Real constant passed to user-supplied subroutine USERSL.
[0.0]
Auxiliary commands LIST APPLY USER-SUPPLIED-LOADS DELETE APPLY USER-SUPPLIED-LOADS
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LOADS-ELEMENT
LOADS-ELEMENT
Sec. 9.4 Loads
SUBSTRUCTURE REUSE GROUP LOAD-TYPE
eli facei p1i p2i ncuri artmi idirni iddli (TWODSOLID elements, LOAD-TYPE = IN-PLANE) eli facei p1i p2i p3i p4i ncuri artmi idirni iddli (TWODSOLID elements, LOAD-TYPE = OUT-PLANE) eli facei p1i p2i p3i p4i ncuri artmi idirni iddli (THREEDSOLID elements) eli facei p1i p2i ncuri artmi idirni iddli (BEAM elements) eli facei p1i p2i p3i p4i ncuri artmi idirni iddli (ISOBEAM elements) eli facei p1i p2i p3i ncuri artmi idirni iddli (PLATE elements) eli facei p1i p2i p3i p4i ncuri artmi idirni iddli (SHELL elements, LOAD-TYPE = SURFACE) eli facei p1i p2i p3i p4i ncuri artmi idirni iddli nodauxi (SHELL elements, LOAD-TYPE = LINE) eli facei p1i p2i p3i p4i ncuri artmi idirni iddli (PIPE elements) eli facei p1i p2i ncuri artmi idirni iddli (FLUID2 elements) eli facei p1i p2i p3i p4i ncuri artmi idirni iddli (FLUID3 elements) Applies distributed loads onto elements, either line loads or pressure loads. SUBSTRUCTURE [currently active substructure] The substructure number for all elements referenced by this command. REUSE [currently active reuse] The reuse number for all elements referenced by this command.
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LOADS-ELEMENT
GROUP [currently active element group] The element group number for all elements referenced by this command. LOAD-TYPE
[IN-PLANE (TWODSOLID elements)] [SURFACE (SHELL elements)] A subtype load indicator for TWODSOLID elements and SHELL elements. IN-PLANE
In-plane line loads for TWODSOLID elements edges.
OUT-PLANE
Out-of-plane surface loads for TWODSOLID elements.
SURFACE
Surface loads for SHELL elements.
LINE
Line loads for SHELL element edges.
eli The label number of the element to which the load is applied. facei A number giving the location onto which the load is applied. See Tables 1 and 2 below. p1i [0.0] p2i [0.0] p3i [0.0] p4i [0.0] Load magnitude at element vertex nodes. The sign convention used is such that the load is positive if directed into/toward the element. ncuri The label number of a time function. artmi The arrival time associated with time dependent loads. idirni Load direction filter.
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0
Total load is applied.
1
x-component of load is applied.
2
y-component of load is applied.
3
z-component of load is applied.
[1] [0.0] [0]
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
LOADS-ELEMENT
Sec. 9.4 Loads
iddli Deformation dependent loading flag. 0
Load is independent of structural deformation.
1
Load depends on structural deformation.
[0]
nodauxi [0] An auxiliary node used when a line load is applied to shell elements, giving the plane of line load application. Auxiliary commands LIST LOADS-ELEMENT
SUBSTRUCTURE REUSE GROUP LOAD-TYPE DELETE LOADS-ELEMENT SUBSTRUCTURE REUSE GROUP LOAD-TYPE
Face parameter conventions: Table 1:
True triangular and tetrahedral elements
Face
Applicable element types
Location
1
TWODSOLID, THREEDSOLID
opposite node 1
2
TWODSOLID, THREEDSOLID
opposite node 2
3
TWODSOLID, THREEDSOLID
opposite node 3
4
THREEDSOLID
opposite node 4
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Chap. 9 Direct finite element data input
Table 2: Elements including degenerated elements, but excluding true triangular and true hexahedron elements (r, s, t refer to local element coordinates) Face
AUI Command Reference Manual: Vol. I — ADINA Structures Model Definition
INITIAL ACCELERATIONS
INITIAL ACCELERATIONS
Sec. 9.5 Initial conditions
SUBSTRUCTURE REUSE
nodei uxi uyi uzi rxi ryi rzi fi Specifies initial accelerations at nodes. Only nonzero initial accelerations need be assigned. SUBSTRUCTURE [current substructure] The substructure for each node specified in this command. REUSE The reuse for each node specified in this command.
[current reuse]
nodei Label number of a node at which initial accelerations are given. uxi uyi uzi The initial accelerations for the displacement degrees of freedom at nodei.
[0.0] [0.0] [0.0]
rxi ryi rzi The initial accelerations for the rotational degrees of freedom at nodei.
[0.0] [0.0] [0.0]
fi The initial 2nd time derivative of fluid potential or hydrostatic pressure at nodei.
[0.0]
Auxiliary commands LIST INITIAL ACCELERATIONS DELETE INITIAL ACCELERATIONS
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Chap. 9 Direct finite element data input
INITIAL DISPLACEMENTS
SUBSTRUCTURE REUSE
nodei uxi uyi uzi rxi ryi rzi fi Specifies initial displacements to nodes. Only nonzero initial displacements need be assigned. SUBSTRUCTURE [current substructure] The substructure for each node specified in this command. REUSE The reuse for each node specified in this command.
[current reuse]
nodei Label number of a node at which initial displacements are given. uxi uyi uzi The initial displacements for the translational degrees of freedom at nodei.
[0.0] [0.0] [0.0]
rxi ryi rzi The initial displacements for the rotational degrees of freedom at nodei.
[0.0] [0.0] [0.0]
fi The initial fluid potential or hydrostatic pressure at nodei.
[0.0]
Auxiliary commands LIST INITIAL DISPLACEMENTS DELETE INITIAL DISPLACEMENTS
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INITIAL FLEXURALSTRAINS
Sec. 9.5 Initial conditions
INITIAL FLEXURALSTRAINS nodei kappa-11i kappa-22i kappa-12i Specifies initial flexural strains at plate element nodes. Only nonzero flexural strains need be assigned. nodei Label number of a plate element at which initial flexural strains are given. kappa-11i [0.0] kappa-22i [0.0] kappa-12i [0.0] Flexural strain components kappa11, kappa22, kappa12. See the Theory and Modeling Guide. Auxiliary commands LIST INITIAL FLEXURALSTRAINS DELETE INITIAL FLEXURALSTRAINS
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INITIAL OVALIZATIONS
INITIAL OVALIZATIONS
SUBSTRUCTURE REUSE
nodei ov1i ov2i ov3i ov4i ov5i ov6i Specifies initial ovalizations at pipe element nodes. Only nonzero ovalizations need be assigned. SUBSTRUCTURE [current substructure] The substructure for each node specified in this command. REUSE The reuse for each node specified in this command.
[current reuse]
nodei Label number of a pipe element node at which initial ovalizations are given. ov1i ov2i ov3i ov4i ov5i ov6i The initial ovalization magnitudes at nodei. See the Theory and Modeling Guide.
[0.0] [0.0] [0.0] [0.0] [0.0] [0.0]
Auxiliary commands LIST INITIAL OVALIZATIONS DELETE INITIAL OVALIZATIONS
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INITIAL PINTERNALPRESSURES
Sec. 9.5 Initial conditions
INITIAL PINTERNALPRESSURES nodei pini Specifies initial pipe internal pressures at pipe element nodes. Only nonzero pipe internal pressures need be assigned. nodei Label number of a pipe element node at which initial internal pressure is given. pini The initial pipe internal pressure at nodei.
[0.0]
Auxiliary commands LIST INITIAL PINTERNALPRESSURES DELETE INITIAL PINTERNALPRESSURES
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INITIAL STRAINS
INITIAL STRAINS nodei stran-11i stran-22i stran-33i stran-12i stran-13i stran-23i Specifies initial strains at nodes. Only nonzero initial strains need be assigned. Orientation of initial strain axes is defined by command AXES-INITIALSTRAIN. nodei Label number of a node at which initial strains are given. stran-11i [0.0] stran-22i [0.0] stran-33i [0.0] stran-12i [0.0] stran-13i [0.0] stran-23i [0.0] The strain components at nodei, in the coordinate system of the element(s) to which nodei is attached. See the Theory and Modeling Guide. Auxiliary commands LIST INITIAL STRAINS DELETE INITIAL STRAINS
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INITIAL SGRADIENTS
Sec. 9.5 Initial conditions
INITIAL SGRADIENTS nodei sgrad-11i sgrad-22i sgrad-12i sgrad-13i sgrad-23i Specifies initial strain gradients at shell element midsurface nodes. Only nonzero strain gradients need be assigned. Orientation of initial strain gradient axes is defined by command AXES-INITIALSTRAIN. nodei Label number of a shell element midsurface node at which initial strain gradients are given. sgrad-11i sgrad-22i sgrad-12i sgrad-13i sgrad-23i The strain gradient components at nodei. See the Theory and Modeling Guide.
[0.0] [0.0] [0.0] [0.0] [0.0]
Auxiliary commands LIST INITIAL SGRADIENTS DELETE INITIAL SGRADIENTS
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INITIAL TEMPERATURES
INITIAL TEMPERATURES nodei tempi Specifies initial temperatures at nodes. Only temperatures that are different from the initial reference temperature, defined by TEMPERATURE REFERENCE, need be assigned. nodei Label number of a node at which initial temperature is given. tempi The initial temperature at nodei.
[0.0]
Auxiliary commands LIST INITIAL TEMPERATURES DELETE INITIAL TEMPERATURES
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INITIAL TGRADIENTS
Sec. 9.5 Initial conditions
INITIAL TGRADIENTS nodei tgradienti Specifies initial temperature gradients at shell element midsurface nodes. Only initial temperature gradients that are different than the reference temperature gradient, defined by TEMPERATURE-REFERENCE, need be assigned. nodei Label number of a shell element midsurface node at which initial temperature gradient is given. tgradienti [0.0] The initial temperature gradient at nodei, measured in degrees/unit length in the shell normal direction. Auxiliary commands LIST INITIAL TGRADIENTS DELETE INITIAL TGRADIENTS
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INITIALVELOCITIES
INITIAL VELOCITIES
SUBSTRUCTURE REUSE
nodei uxi uyi uzi rxi ryi rzi fi Specifies initial velocities at nodes. Only nonzero initial velocities need be assigned. SUBSTRUCTURE [current substructure] The substructure for each node specified in this command. REUSE The reuse for each node specified in this command.
[current reuse]
nodei Label number of a node at which initial velocities are given. uxi uyi uzi The initial velocities for the displacement degrees of freedom at nodei.
[0.0] [0.0] [0.0]
rxi ryi rzi The initial velocities for the rotational degrees of freedom at nodei.
[0.0] [0.0] [0.0]
fi The initial 1st time derivative of fluid potential or hydrostatic pressure at nodei.
[0.0]
Auxiliary commands LIST INITIAL VELOCITIES DELETE INITIAL VELOCITIES
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INITIAL WARPINGS
INITIAL WARPINGS
Sec. 9.5 Initial conditions
SUBSTRUCTURE REUSE
nodei warp1i warp2i warp3i warp4i warp5i warp6i Specifies initial warpings at pipe element nodes. Only nonzero warpings need be assigned. SUBSTRUCTURE [current substructure] The substructure for each node specified in this command. REUSE The reuse for each node specified in this command.
[current reuse]
nodei Label number of a pipe element node at which initial warpings are given. warp1i warp2i warp3i warp4i warp5i warp6i The initial warping magnitudes at nodei. See the Theory and Modeling Guide.
[0.0] [0.0] [0.0] [0.0] [0.0] [0.0]
Auxiliary commands LIST INITIAL WARPINGS DELETE INITIAL WARPINGS
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IMPERFECTION NODES
IMPERFECTION NODES bucklingmodei nodei directioni displacementi Specifies imperfections based on buckling mode shapes which have been calculated in a previous run. The total imperfection applied to the nodal coordinates is a superposition of the imperfections from each specified buckling mode. List of buckling modes has to be continous - all buckling modes between the first and last mode have to be specified. For modes which are not significant, displacementi should be set to 0. bucklingmodei The number of the buckling mode shape. nodei Node label number where the magnitude of the imperfection associated with bucklingmodei is specified. directioni Translational degree of freedom for nodei. 1
X-translation (global or skew).
2
Y-translation (global or skew).
3
Z-translation (global or skew).
displacementi [0.0] Magnitude of imperfection in the same length unit as the global coordinates. ADINA scales bucklingmodei to have this value at the node and in the direction specified. Auxiliary commands LIST IMPERFECTION NODES DELETE IMPERFECTION NODES
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CONTACT-ELEMSET
Sec. 9.6 Contact
CONTACT-ELEMSET
NAME PRINT SAVE
eledgeseti sensei
(2-D contact groups)
elfaceseti sensei
(3-D contact groups)
Defines a contact surface using element edge or face set defined by the ELEDGESET or ELFACESET command. NAME [(current highest contact surface label number) + 1] Label number of the contact surface to be defined. Note that the contact surface names are unique only within a contact group, i.e. two different contact groups may each define its own contact surface "1". PRINT [DEFAULT] Flag controlling printout of the results of the contact analysis as determined by the FORCES and TRACTIONS parameters of the CGROUP command. If DEFAULT is specified, printout is controlled by PRINTOUT PRINTDEFAULT. {YES/NO/DEFAULT} SAVE [DEFAULT] Flag controlling saving (to the porthole file) of the results of the contact analysis as determined by the FORCES and TRACTIONS parameters of the CGROUP command. If DEFAULT is specified, saving is controlled by the PORTHOLE SAVEDEFAULT parameter. {YES/NO/ DEFAULT} eledgeseti Element edge set label number. elfaceseti Element face set label number. sensei Orientation flag.
[+1]
+1 contact surface follows the orientation of the element edges or faces. -1 contact surface uses opposite orientation to the element edges or faces. Auxiliary commands LIST CONTACT-EELEMSET DELETE CONTACT-EELEMSET
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CONTACT-FACENODES
Chap. 9 Direct finite element data input
CONTACT-FACENODES
NAME PRINT SAVE
segi n1i n2i n3i n4i n5i n6i n7i n8i n9i This command defines a contact surface within the current contact group using face node numbers. Command can be applied only to 3-D contact. NAME Label number of the contact surface to be defined. PRINT Flag controlling printout of the results, see command CONTACTSURFACE. SAVE Flag controlling saving of the results, see command CONTACTSURFACE. segi Label number of segment i. n1i...n4i The corner nodes for segment i. n5i...n8i The midside nodes for segment i. n9i The midsurface node for segment i. Auxiliary commands LIST CONTACT-FACENODES DELETE CONTACT-FACENODES
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CONTACT-NODES
CONTACT-NODES
Sec. 9.6 Contact
NAME PRINT SAVE MODE MASTER
ni
(2-D contact groups)
segi n1i n2i n3i n4i
(3-D contact groups)
Defines a contact surface within the current contact group. Contact surfaces are defined by the end-nodes of the segments. NAME [(current highest contact-surface label number) + 1] Label number of the contact-surface to be defined. Contact-surface numbering is shared with CONTACTSURFACE, CONTACTPOINT and CONTACT-FACENODES. PRINT [DEFAULT] Controls printout of results for the contact-surface. Input of DEFAULT implies the setting of PRINTOUT PRINTDEFAULT is used. {YES/NO/DEFAULT} SAVE [DEFAULT] Controls saving of results (to the porthole file) for the contact-surface. Input of DEFAULT implies the setting of PORTHOLE SAVEDEFAULT is used. {YES/NO/DEFAULT} MODE
[INPUT]
INPUT
The contact segments are defined exactly as input.
REVERSE
The contact segments are reversed.
ALIGN
The contact segments are aligned to have the same sense as the first segment.
MASTER Master Point Label used for creating rigid link between this Master Point and all these contact nodes.
[0]
ni Label numbers of nodes on a 2-D contact-surface, see the Theory and Modeling Guide for the orientation convention used. Segments are defined by successive node numbers; that is, segment 1 is defined by the first two nodes, segment 2 is defined by the second and third node, etc. segi Label number of an area-segment on a 3-D contact surface. Each data input line defines a new segment.
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CONTACT-NODES
n1i,...,n4i Label numbers of nodes defining the area segment, see the Theory and Modeling Guide for the orientation convention used. Auxiliary commands LIST CONTACT-NODES FIRST LAST GROUP LIST CONTACT-NODES lists the definitions of contactsurfaces with label numbers in a given range. If no range is specified a list of all contactsurfaces label numbers within the given contact group is listed. GROUP is set to the current active contact group if no value is input for this parameter. DELETE CONTACT-NODES FIRST LAST GROUP DELETE CONTACT-NODES deletes the contactsurfaces with label numbers in a given range. Note that a contactsurface will not be deleted if it is referenced by a contactpair definition (see command CONTACTPAIR ). GROUP is set to the current active contact group if no value is input for this parameter.
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CRACK-PROPAGATION NODES
CRACK-PROPAGATION NODES
Sec. 9.7 Fracture
NAME NCRACK
node-1i ... node-NCRACKi nvshfti factori Defines the initial crack front position and/or the virtual/actual crack propagation path along which a crack would propagate. For 2-D analysis, the crack front corresponds to a single node - the crack tip node. the virtual crack propagation path corresponds to a single line of nodes starting at the crack tip node. For 3-D analysis, the crack front corresponds to a line of nodes - the first node given for each “generator” line of nodes. The virtual/actual crack propagation path corresponds to a surface developed from the crack front along generator lines originating at the crack front nodes. NAME [1] The label number of the crack propagation surface. At present only one crack surface is allowed. NCRACK The number of vertex nodes along the generator lines. {1 ≤ NCRACK ≤ 999}
[1]
node-1i ... node-NCRACKi Label numbers of nodes along generator line “i” of the crack propagation surface. nvshfti [0] Virtual material shift associated with generator line “i” of the crack propagation surface: For a fixed virtual material shift, this is the label number of a virtual shift defined by command J-VIRTUAL-SHIFT. For a moving virtual material shift, this is the number of “rings” of elements about the (moving) crack tip on the generator line. Parameter nvshfti is used only in crack propagation analysis (FRACTURE TYPE =PROPAGATION). factori Resistance factor. See the Theory and Modeling Guide.
[0.0]
Auxiliary commands LIST CRACK-PROPAGATION DELETE CRACK-PROPAGATION
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J-VIRTUAL-SHIFT NODE
Chap. 9 Direct finite element data input
J-VIRTUAL-SHIFT NODE
NAME VECTOR VX VY VZ N3DSH
nodei Defines a fixed virtual-crack-extension material shift via a set of nodes. NAME [(current highest virtual shift label number) + 1] Label number of the virtual shift to be defined. VECTOR
[AUTOMATIC]
AUTOMATIC
The shift vector is calculated automatically, from the crack surface definition (see CRACK-PROPAGATION). In the case of a 3-D crack, N3DSH is used to select a generator line associated with the automatic shift vector calculation.
INPUT
The shift vector is input directly via VX, VY and VZ.
VX VY VZ The global components of the material shift vector.
[0.0] [0.0] [0.0]
N3DSH [0] Generator line number of the crack surface for automatic shift vector calculation (for a 3-D crack). nodei The label number of a node contained within the virtual material shift. Auxiliary commands LIST J-VIRTUAL-SHIFT NODE DELETE J-VIRTUAL-SHIFT NODE
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J-VIRTUAL-SHIFT ELEMENT
J-VIRTUAL-SHIFT ELEMENT
Sec. 9.7 Fracture
NAME GROUP VECTOR VX VY VZ N3DSH
elementi groupi Defines a fixed virtual-crack-extension material shift via a set of elements. NAME [(current highest virtual shift label number) + 1] Label number of the virtual shift to be defined. GROUP Element group label number.
[current active group]
VECTOR
[AUTOMATIC]
AUTOMATIC
The shift vector is calculated automatically, from the crack surface definition (see CRACK-PROPAGATION ). In the case of a 3-D crack, N3DSH is used to select a generator line associated with the automatic shift vector calculation.
INPUT
The shift vector is input directly via VX, VY and VZ.
VX VY VZ The global components of the material shift vector.
[0.0] [0.0] [0.0]
N3DSH Generator line number of the crack surface for automatic shift vector calculation, (for a 3-D crack).
[0]
elementi The label number of an element contained in the virtual material shift. groupi The label number of the element group, containing elementi.
[GROUP]
Auxiliary commands LIST J-VIRTUAL-SHIFT ELEMENT DELETE J-VIRTUAL-SHIFTELEMENT
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J-LINE ELEMENT
Chap. 9 Direct finite element data input
J-LINE ELEMENT
NAME GROUP PRINT SAVE START-FACE END-FACE
elementi groupi Defines a line contour connected by a series of element faces. NAME [(current highest line contour label number) + 1] Label number of the line contour to be defined. GROUP Element group label number.
[currently active group]
PRINT SAVE START-FACE [0] Determines which face of the first element is selected to start the contour, if the element has more than one boundary face. 0 1 2 3 4
Face number automatically selected. Face N1-N2. Face N2-N3. Face N3-N4. Face N4-N1.
where N1, N2, N3, N4 are the element vertex nodes. END-FACE [0] Determines which face of the last element is selected to terminate the contour, if the element has more than one boundary face. 0 1 2 3 4
Face number automatically selected. Face N1-N2. Face N2-N3. Face N3-N4. Face N4-N1.
elementi The label number of an element which forms the line contour. groupi The label number of the element group, containing elementi.
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J-LINE ELEMENT
Sec. 9.7 Fracture
Auxiliary commands LIST J-LINE ELEMENT DELETE J-LINE ELEMENT
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SINGULAR NODES
SINGULAR NODES
Q-POINT
nodei Defines a set of vertex nodes whose adjacent non-vertex nodes are to be moved to form singularities. See the Theory and Modeling Guide. Q-POINT [QUARTER] Selects whether non-vertex nodes adjacent to the desired vertex nodes are moved to the “1/4 point”, or the opposite action is taken. QUARTER
Nodes are moved to the “1/4 point”.
MID
Nodes are moved from the “1/4 point” back to the relevant midside/face position.
nodei Label number of a singular node. Auxiliary commands LIST SINGULAR NODES FIRST LAST DELETE SINGULAR NODES FIRST LAST
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REUSE-NODES
Sec. 9.8 Substructures and cyclic symmetry
REUSE-NODES
SUBSTRUCTURE REUSE LOAD-REUSE
iconai iretni Defines the nodal connectivity between a substructure and the main structure. Each substructure can be used several times and this command sets the current “reuse” label identifying number for the active substructure. SUBSTRUCTURE [currently active substructure] Identifying number for the substructure to which subsequent reuse data refer. REUSE Label number of the reuse to be defined.
[currently active reuse]
LOAD-REUSE Reuse loading indicator.
[SAME]
SAME
The loading for this reuse is the same as for the previous reuse, REUSE-1, of the same substructure.
DIFFERENT
The loading for this reuse is specified by subsequent loading commands, e.g., APPLY-LOAD.
iconai The main structure connection node for the substructure reuse. Note that the same number of data input lines must be entered for each reuse of the substructure. iretni The substructure connection node for the substructure reuse.
[0]
Auxiliary commands LIST REUSE-NODES DELETE REUSE-NODES
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CYCLICBOUNDARIES NODES
CYCLICBOUNDARIES NODES sbnodei mbnodei Specifies the cyclic boundary nodes of the fundamental part of a cyclic symmetric structure. The cyclic boundaries of the fundamental part consist of two boundaries, namely, the master and slave cyclic boundaries. When the nodes on the master cyclic boundary are rotated 360/M (where M is the number of cyclic parts) degrees counter clockwise about the cyclic symmetry axis, they should coincide with the nodes on the slave cyclic boundary. sbnodei Label number of a node on the slave cyclic boundary. mbnodei Label number of the corresponding node on the master cyclic boundary. Auxilary commands LIST CYCLICBOUNDARIES NODES DELETE CYCLICBOUNDARIES NODES
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B BCELL, 7-366 BLAYER, 8-59 BODY BLEND, 6-102 BODY BLOCK, 6-104 BODY CHAMFER, 6-107 BODY CONE, 6-109 BODY CYLINDER, 6-112 BODY HOLLOW, 6-115 BODY INTERSECT, 6-116 BODY LOFTED, 6-117 BODY MERGE, 6-118 BODY MID-SURFACE, 6-119 BODY OPTION, 6-120 BODY PARTITION, 6-121
Index-1
Command index
BODY PIPE, 6-122 BODY PRISM, 6-125 BODY PROJECT, 6-128 BODY REVOLVED, 6-129 BODY SECTION, 6-132 BODY SEW, 6-133 BODY SHEET, 6-134 BODY SPHERE, 6-135 BODY SUBTRACT, 6-137 BODY SURFACES, 6-63 BODY SWEEP, 6-138 BODY TORUS, 6-141 BODY TRANSFORMED, 6-144 BODY VOLUMES, 6-64 BODY-CLEANUP, 6-74 BODY-DEFEATURE, 6-71 BODY-DISCREP, 6-70 BODY-DSCADAP, 6-76 BODY-ELEMDATA FLUID3, 7-211 BODY-ELEMDATA GENERAL, 7-206 BODY-ELEMDATA THREEDSOLID, 7-192 BODY-RESTORE, 6-75 BOLT-OPTIONS, 8-56 BOLT-TABLE, 8-57 BOUNDARIES, 9-54 BOUNDARY-SURFACE SURFACE-TENSION, 7-362 BUCKLING-LOADS, 5-30
Appendix 1 Error Messages General errors Error Number
Description
1002
Stiffness matrix not positive definite, boundary conditions or model collapsed
1003
Either the ADINA input file (*.dat) is missing or is incorrect
1004
Program not able to open the restart file, please check your input
1005
Not enough memory on the system to be allocated for the ADINA program
1006
Not enough memory allocated, sparse matrix indexes cannot fit into memory
1007
Node label cannot be zero or larger that the maximum label number
1008
Wrong input data, this is ADINA-F input data
1009
Wrong input data, this is ADINA-T input data
1010
Input data from an unsupported program version
1011
Restart from static to dynamic cannot be used if factorized K is reused
1012
Restart from dynamic analysis to static cannot be used if LDC is used
1013
Number of time functions in restart cannot be smaller than in the previous run
1014
Temperature loading used in a previous run but not in restart
1015
Model contains features not available in explicit time integrations
1016
Number of nonlinear element groups changed in the restart run
1017
Number of substructures changed in restart analysis
1018
Incorrect number of substructure stiffness blocks in the restart run
1019
Errors in reading restart file
1020
Element group data is changed in restart analysis
1021
Material model is changed in restart analysis
1022
Substructure reused different number of times in restart analysis
1023
The total number of DOFs changed for restart and substructure analysis
1024
Zero effective mass input in explicit time integration
1025
Restart time mismatch, please check your input data
1026
Temperature file cannot be opened
1027
Temperature gradient file cannot be opened
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A-1
Appendix 1
A-2
1028
External force file (IT58) cannot be opened
1029
Automatic time stepping not available for options used
1030
Program cannot find a license file or is not allowed to run on this platform
1031
Density cannot be set to zero in explicit time integration
1032
ISOBEAM, only 2-node elements can be used in explicit time integration
1033
Pipe elements cannot be used in explicit time integration
1034
Explicit time integration, material model cannot be used in this element group
1035
Potential based fluid elements cannot be used in explicit time integration
1036
User-supplied material model cannot be used in explicit time integration
1037
Material model in this element group cannot be used with initial stresses
1038
Number of nodal points equal to zero is not allowed
1039
The restricted number of nodes exceeded - 900 nodes maximum allowed
1040
Incorrect entry for temperatures, pipe pressure or forces read from a file
1041
Nodal forces provided on an external file cannot be used with substructures
1042
Wrong input for extended results printout for large strains
1043
Wrong input data for file provided forces, see DISK-STORAGE
1044
Fracture flag out of range, please check your input data
1045
Rigid beam-bolts cannot be used with cyclic symmetry
1046
Static correction for response spectrum can be used in linear analysis only
1047
Wrong formulation used, fluid potential and response spectrum
1048
Wrong formulation used, fluid potential and mode- superposition
1049
Solution (iteration) method is out of range, please see ITERATION METHOD
1050
Wrong flag for the automatic time-stepping method
1051
Input for number of subdivisions is wrong (negative!), see AUTOMATIC TIME-ST
1052
Large strains extended printing flag is wrong see PRINTOUT LARGESTRAINS
1053
Automatic load displacement (LDC) method cannot be used in crack propagation
1054
Incorrect main fracture input flags (see FRACTURE...)
1055
Frequency calculation cannot be done in static analysis
1056
Determinant search cannot be used to calculate frequencies within interval
1057
Frequency file is missing, it is required to perform modal analysis
AUI Command Reference Manual: Vol. I − ADINA- Model Definition
Error messages
1058
Number of frequencies and mode shapes stored on file is smaller than requested
1059
Response spectrum analysis cannot be used with cyclic symmetry
1060
Number of frequencies requested is larger than number frequencies calculated
1061
Response spectrum analysis cannot be performed without translational DOFs
1062
Automatic load-displacement (LDC) method can only be used in static analysis
1063
Automatic load-displacement (LDC) method can only be used in nonlinear analysis
1064
Automatic load-displacement (LDC) method cannot be used in linearized buckling
1065
LDC method, wrong node label used in the first step loading
1066
LDC method – DOF used for the prescribed first step displacement is incorrect
1067
LDC method – maximum allowable displacement(DISPMAX) cannot be negative
1068
Incorrect input data for fluid-structure analysis (FSI)
1069
Error in STIFFNESS-STEPS or EQUILIBRIUM-STEPS input data
1070
Error in printing or saving block input data
1071
Number of linear, nonlinear and substructure element groups is equal to zero
1072
Potential based fluid element flag is incorrect
1073
Potential based fluid elements cannot be used with substructures
1074
Potential based fluid elements cannot be used with lumped damping
1075
Potential based fluids cannot be used with the subspace iteration method. Only determinant search or Lanczos method can be used. Note: For large problems or mid-size problems with a large number of frequencies requested, the Lanczos method should be used.
1076
Potential based fluid elements can not be used with lumped mass matrix
1077
Input error, time step cannot be equal to or smaller than zero
1078
Flag to request reaction calculations is incorrect
1079
Damping can only be included in dynamic analysis
1080
Wilson method cannot be used with the automatic time stepping (ATS) method
1081
Lumped mass has to be used for the explicit time integration
1082
Frequency calculation cannot be used with explicit time integration
1083
Damping flag is incorrect
ADINA R & D, Inc.
A-3
Appendix 1
A-4
1084
Only lumped damping can be used in explicit time integration
1085
Consistent mass matrix cannot be used with substructures
1086
Damping cannot be used with substructuring
1087
Mode superposition analysis cannot be used with substructuring
1088
Linearized buckling cannot be used in dynamic analysis
1089
Frequency calculation cannot be requested when substructuring is used
1090
Initial imperfections cannot be used with substructures
1091
Explicit time integration cannot be used with substructures
1092
Mode superposition can be performed if mass matrix assemblage is requested
1093
Automatic load-displacement (LDC) method cannot be used with thermal loading
1094
User-supplied loading cannot be used with automatic load-displacement method
1095
Contact surfaces cannot be present in mode superposition analysis
1096
Factorized stiffness matrix cannot be stored, explicit time integration used
1097
Displacements cannot be prescribed in mode superposition analysis
1098
Linearized buckling cannot be performed in linear analysis
1099
Centrifugal loading cannot be used with substructures
1101
Mesh too distorted, Jacobian determinant not positive
1102
Contact conditions inadmissible (either wrong contact orientation or divergence)
1103
No convergence, concrete material model, stresses outside the failure curve
1104
Mixed (u/p) formulation – an internal matrix cannot be inverted
1105
No convergence in the iterative solver
1106
No convergence in plasticity (bisection algorithm)
1107
No convergence in the Drucker-Prager material model
1108
No convergence in the creep material model
1109
No convergence in orthotropic plasticity (bisection)
1110
No convergence in rubber-like material model
1111
Green-Lagrange strains beyond theoretical limit
1112
No convergence in the moment-curvature material model
1113
Strains out-of-range – nonlinear elastic material model
1114
No stress convergence in the Gurson material model
AUI Command Reference Manual: Vol. I − ADINA- Model Definition
Error messages
1115
FSI load calculation problem, time step reduced
1116
Insufficient memory for double-sided contact (could be due to divergence)
1117
Mesh too distorted – BEAM distributed load calculation
1118
Zero pivot – probably wrong boundary conditions
1119
No convergence in Mohr-Coulomb material model
1120
Divergence, energy greater than 1.E30, model crushed, time step probably too large
1121
Rigid contact, time step reduced due to tensile contact
1122
BEAM elements, program stopped in material model calculations
1123
Solution is diverging, time step reduced, solution continues
1124
No convergence in the concrete material model
1125
Invalid energy value (either NaN or Inf) in the convergence check
1126
A division by zero in the BEAM element, program might be diverging
1127
3-D solid elements, ULH – eigenvector cannot be calculated
1128
Incompatible mode elements – an internal matrix cannot be inverted
1130
No convergence in the foam material model (bisection algorithm)
1131
No convergence in element pressure calculations, mixed u/p elements
1132
SHELL elements – mesh too distorted
1133
Rigid target contact algorithm, time step reduced due to excessive penetration
1197
Probably too many nodes suddenly in contact, program takes a smaller step
Not enough memory to store nodal coordinates, probably gaps in node numbering
1202
Total number of constraint equations is incorrect
1203
Constraint equations are out of order
1204
Node numbers input for constraints is incorrect
1205
Constraint equations – Incorrect number of degrees of freedom
1206
Constraint equations – incorrect number of independent degrees of freedom
1207
An independent degree of freedom is used as a dependent in constraints
1208
Fluid DOF can only be constrained to another fluid DOF
1209
An independent DOF has to be an active DOF, i.e., cannot be a "fixed" DOF
1210
Rigid links must be input in ascending order
ADINA R & D, Inc.
A-5
Appendix 1
A-6
1211
Incorrect input for a rigid link number
1212
Flag indicating type of rigid link (linear or nonlinear) is incorrect
1213
Nonlinear rigid links cannot be used in linear analysis
1214
Linear rigid links must be input before nonlinear links
1215
Rigid links cannot be used with SHELL having 5 DOFs
1216
Independent DOFs are not allowed on slave rigid links nodes
1217
Master rigid link nodes must have all independent DOFs
1218
Number of constraint equations with bolts is incorrect
1219
Rigid bolts cannot be connected to shell elements with 5 DOFs
1220
Slave nodes of rigid bolts must have all DOFs constrained
1221
A constrained degree of freedom (DOF) by a rigid bolt must be free
1222
Bolt constraints cannot be generated, independent DOFs are missing
1223
There are no potential fluid degrees of freedom for marked structural DOFs
1224
Allocated memory too small to store stiffness matrix
1225
Insufficient allocated memory
1226
Insufficient allocated memory. More than 1000 blocks need to be created.
1227
Rigid bolt, translational DOFs are constrained
1228
SHELL elements, an averaged director vector has zero magnitude
1229
Rigid bolt, translational DOFs are constrained
1230
Incorrect flag for convergence criteria, see TOLERANCES ITERATION CONVERGENCE
1231
Incorrect convergence criteria in mode superposition, only energy can be used
1232
Reference force in force convergence criteria must be greater than zero
1233
Reference translation in displacement convergence must be greater than zero
1234
Reference moment in force convergence criteria must be greater than zero
1235
Reference rotation in displacement convergence must be greater than zero
1236
Reference value of initial imperfections cannot be specified on constrained DOF
1237
Initial strain flag is incorrect
1238
Time on temperature tape does not match solution starting time
1239
Temperature tape steps do not match steps in ADINA, use DISK-S TEMP=INTERPOLATE
1240
Director vectors can only be generated if Euler angles are used
AUI Command Reference Manual: Vol. I − ADINA- Model Definition
Error messages
1241
Incorrect input for SHELL director vectors
1242
Skew system number in nodal input data is incorrect
1243
Coordinate system type is incorrect
1244
Mid-surface vector number is greater than total number of director vectors
1245
Number of degrees of freedom allowed in analysis is incorrect
1246
The fluid DOF is incorrect, it can be free, fixed or constrained
1247
SHELL 5/6 DOF indicator is incorrect. It should be 0 or 1.
1248
End-of-file when reading, temperature or pipe pressure external file
1249
No fluid (PHI) DOF for marked structural degrees of freedom
1250
Total number of equations is zero. At least one equation is required.
1251
Incorrect element type input, please check your data
1252
Contact element groups must be input after ALL element group data
1253
Specified number of element groups is different than the number read from input
1254
Specified number of contact groups is different than the number read from input
1255
Crack growth, stiffness must be reformed every step
1256
A node with assigned pressure DOF has not been used in any element group
1257
Incorrect input data for rigid-bolt element
1258
Number of elements connected to 1 node exceeds the value specified in input
1259
LDC-initial displacement imposed on a deleted or constrained DOF
1260
Substructure identification number incorrect
1261
Substructures – local X vector has zero length, please check your input
1262
Substructures – local Y vector has zero length, please check your input
1263
Substructures – local X&Y vectors are not orthogonal, please check your input
1264
Substructures – incorrect connectivity array, please check your input
1265
Substructures – error in printing or saving block input data
1266
Time integration method incorrect, can be implicit or explicit
1267
Wilson-theta method, theta incorrect, see ANALYSIS DYNAMIC METHOD
1268
Newmark method, incorrect parameters, see ANALYSIS DYNAMIC METHOD
1269
Dynamic analysis, time step too small
1270
An unsuccessful attempt has been made to read a direct access file
ADINA R & D, Inc.
A-7
Appendix 1
A-8
1271
An unsuccessful attempt has been made to write into a direct access file
1272
Incorrect maximum number of DOF per node, input probably is not correct
1273
Mode superposition analysis requires number of modes greater than zero
1274
Program internal error, very likely memory corrupted
1275
Slave DOFs cannot be connected to multiple rigid links
1276
Incompatible options for centrifugal force calculation Element-based centrifugal force calculation option cannot be used if a lumped mass matrix is specified for the problem.
1277
Incompatible options for centrifugal force calculation. Deformation-dependent centrifugal loading cannot be used with element-based centrifugal force calculation option.
1278
PHI massflux loads can only be used with potential-based elements
1279
The number of elements in the restart run is different than in the previous run
1280
Explicit analysis TOTALTIME option, can only be used with one time step block
1281
Explicit time integration method cannot be used with potential fluid elements
1282
Constraint equation cannot be defined along prescribed direction
1283
Incompatibility between time functions in the fluid and structural models
1284
Rigid target, different number of processors used in restart than in a previous run
1285
No active degrees of freedom (DOF) are present
1286
The number of time step blocks limit has been exceeded
1287
Error in the reading of time function input data. Please check your input.
1288
Error in the skew coordinate system input (inadmissible direction cosines)
1289
Incorrect input data for substructures
1290
Substructure – no. of condensed and retained nodes is not equal to total no. of nodes
1291
No convergence. Invalid energy value (either NaN or Inf) in the convergence check
1292
Incorrect displacement vector, invalid displacement values (either NaN or Inf entries)
1293
Error in closing a porthole file (porthole splitting option)
1294
Explicit time integration cannot be used with thermal loading provided via tape
1295
Damping elements can only be used if damping is requested in the master input
AUI Command Reference Manual: Vol. I − ADINA- Model Definition
Error messages
1296
TMC, different meshes for heat transfer and structure analysis cannot be used
1297
Nodal mass input, non-existing node numbers(labels) are used
1298
Nodal damping input, non-existing node numbers(labels) are used
1299
Incorrect domain decomposition, contact nodes belong to a wrong subdomain
ADINA R & D, Inc.
A-9
Appendix 1
Element error messages (during element group input) Error Number
Description
1301
Incorrect kinematic formulation used for element group
1302
Element death/birth option flag is out of range
1303
Truss element type out-of-range
1304
Truss-gap element flag is incorrect
1305
Incorrect maximum number of nodes per element
1306
Incorrect number of element integration points
1307
Incorrect material model number for an element group
1308
Incorrect number of material constants
1309
The total number of elements in an element group is ZERO
1310
Element death/birth cannot be used with linear elements
1311
Gap elements cannot be used as linear elements
1312
Material model used requires nonlinear element groups
1313
Truss-ring element cannot have more than 1 node
1314
Truss-ring element cannot be used with skew systems
1315
Truss-ring element cannot have gap options
1316
Incompatible (bubble function) elements cannot be defined as mixed (u/p) elements
1317
No skew system defined, elements cannot have nodes referred to a skew systems
1318
Temperature is required for the specified material model
1319
The gap option can only be used with 2-node elements
1320
Input error in element group control parameters
1321
Young’s modulus must be greater than zero
1322
Young’s modulus must be greater than zero for all temperatures
1323
Incorrect material properties, nonlinear elastic model
1324
Incorrect material constants for a plastic material model
1325
Incorrect input data for plastic-multilinear material
1326
Incorrect input for strain rate effects
1327
Incorrect input for creep material model
1328
Material type number is out of range
A-10
AUI Command Reference Manual: Vol. I − ADINA- Model Definition
Error messages
1329
Element birth time must be smaller than death time
1330
Incorrect flag for spatial isotropy correction
1331
Energy release rate cannot be performed with fracture mechanics
1332
Mixed formulation cannot be used for some material models
1333
Wrong number of pressure points for mixed elements
1334
Incorrect number of temperature points-creep/plasticity
1335
Stress table flag out of range
1336
Soil material models cannot be used in plane stress analysis
1337
Incorrect number of curve points- user-supplied material
1338
Large strain analysis is not allowed for material model used
1339
Energy release rate can only be calculated in linear analysis
1340
Fabric material model can only be used in plane stress analysis
1341
Mixed elements cannot be used for plane stress analysis
1342
Temperature flag incorrect for concrete material model
1343
Stress tables cannot be used with the specified material
1344
Initial strains/stresses cannot be used in linear analysis or flags are incorrect
1345
Incorrect flags for user-supplied creep coefficients
1346
Incorrect flag to calculate strain energy densities
1347
Incorrect number (negative) of axes of orthotropy sets
1348
SHELLs - incorrect number of nodes in the surface direction
1349
Incorrect number of integration points through the thickness
1350
Total number of nodes must be greater or equal than number of midsurface nodes
1351
Multi-layer SHELL can only have mid-surface nodes
1352
Improper section type specified for a BEAM element group
1353
Incorrect flag for stress output tables
1354
Moment-curvature law cannot be used with this material model
1355
Incorrect ISOBEAM element cross section type
1356
Incorrect thickness table number for ISOBEAM elements
1357
PLATE element – requested material model is not available
1358
PLATE element – initial flexural strains input is required
1359
Elements require nodal initial strain/stress input which is not provided
ADINA R & D, Inc.
A-11
Appendix 1
1360
PIPE internal pressure cannot be used with linear pipe elements
1361
PIPE with ovalization is requested but ovalization DOFs are specified
1362
Improper input for a PIPE element
1363
Flange conditions used, which requires Newton-Cotes integration along PIPE axis
1364
Only 4-node PIPE element can be used with warping/ovalization DOFs
1365
Full Newton iteration must be used in contact analysis
1366
CONTACT – at least three contact surface nodes must be specified
1367
CONTACT – at least one contact surface must be specified
1368
CONTACT – at least one contact surface pair must be specified
1369
Total number of contact nodes must be GT or EQ to the number of contactor nodes
1370
2-D CONTACT can only be: plane stress, plane strain or axisymmetric
1371
No skew system defined, contact surface nodes cannot refer to skew systems
1372
CONTACT model out-of-range, can be: frictionless or with friction
1373
Friction in explicit analysis cannot be used with selected contact algorithm
1374
3-D CONTACT – number of contactor nodes must be greater or equal to 1
1375
3-D CONTACT – total number of contact nodes must be greater or equal to 5
1376
3-D CONTACT – at least one segment must be attached to a contact surface node
1377
Generalized plane strain-skew system cannot allow rotations around the X-axis
1378
Incorrect number of material data sets, please check your material input data
1379
Incorrect node number input for strain energy release calculation
1380
Triangular elements can only have 3 or 6 or 7 nodes
1381
Maximum number of nodes exceeded for a 2-D element
1382
Incorrect material data set number, please check your input data
1383
Element birth time must be smaller than element death time
1384
Porous solid elements cannot be used with explicit time integration
1385
SHELL – maximum number of nodes per element exceeded
1386
Nonsymmetric moment-curvature cannot be used with this beam model
1387
Cyclic elastic rigidity not permitted for this beam model
1388
Cannot use more than one pressure DOF in 3-node triangular elements
A-12
AUI Command Reference Manual: Vol. I − ADINA- Model Definition
Error messages
1389
Cannot use more than one pressure DOF in 4-node tetrahedral elements
1390
Rigid target contact can only be used with ATS method
1391
Errors in contact segment definitions
1392
Consistent contact linearization cannot be used with direct solver
1392
Tied contact is not available in explicit time integration
1394
Large strain formulation cannot be used with multilayered shell element
1395
Incompatible modes elements: integration order must be greater than 1
1396
Error in the shell element group data, please see the *.out file for details
1397
Error in the element group control parameters, skew systems not indicated
1398
One (or more) of the element node numbers is either negative or undefined
1399
Incorrect number of nodes in a TRUSS element, program stops
ADINA R & D, Inc.
A-13
Appendix 1
Temperature error messages, rigid links, loadings, etc. Error Number
Description
1401
Time mismatch between temperature file and program, use option interpolate
1402
Time mismatch between temperature gradient file and the program, use option interpolate
1403
Time mismatch, pipe internal pressure file, use option interpolate
1404
Time mismatch between nodal force file and the program, use option interpolate
1405
Rigid links – fixities applied to a slave node conflicts with a motion of a master node
1406
Pipe internal pressure is either missing or should not be present in the restart file Note: if pipe internal pressure is present in the first run, the it has to be present in subsequent restart runs. The opposite also holds. I f there is no pipe internal pressure in the first rune, then the pipe internal pressure cannot be applied in subsequent runs.
1407
Empty
1408
Program internal error – true cyclic symmetry and computing nonlinear constraints
1409
Rigid links – one rotation free and different skew systems used for M&S nodes
1410
Rigid links – only 2 translations free and different skew systems for M&S nodes
1411
Rigid links – only 1 translation free and different skew systems for M&S nodes
1412
Temperature outside range of material property temperatures
Concentrated load input data, loading cannot be generated
1415
BEAM pressure loading input error, zero length between nodes
1416
FSI, temperature file incorrect. Time span for structure is smaller than for fluid. The time span is equal to the total number of time steps multiplied by the time step value.
1417
FSI, temperature gradient file incorrect. Time span for structure is smaller than for fluid
1418
FSI, pipe int. pr. file incorrect. Time span for structure is smaller than for fluid
A-14
AUI Command Reference Manual: Vol. I − ADINA- Model Definition
Error messages
1419
Fracture, ratio of J-integral/(nodal displacement) is larger than the resistant curve
1420
Fracture, the crack increment is negative, program stops
1421
Fracture, the J-integral number is out of range, program stops
1422
Fracture – internal error, please see *.out file for more information
1423
Fracture, the number of crack nodes or rings is negative
1424
Fracture, the flag for virtual vector calculation is out of range
1425
Fracture, a crack node cannot be smaller or equal to zero
1426
Fracture, a crack node degree of freedom cannot be smaller or equal to zero
1427
Fracture, no J-integral specified for crack growth control
1428
Fracture, the number of nodes in the material shift is too small
1429
Fracture, no temperature input for temperature-dependent resistance curves
1430
Fracture, temperature at crack tip node out-of-range of resistance curves
1431
Fracture, nodes on the crack propagation surface cannot be constrained
1432
Fracture, a negative crack increment, please check the resistance curve
1433
Fracture, the end of propagation surface has been reached
1434
Fracture, crack increment is zero, please check your input
1435
Mixed-interpolated (u/p) elements cannot be used with incompatible modes
1436
Shells - element temperatures are outside material property parameters
1437
Initial temperature is outside the range of material property temperatures
1438
Fracture mechanics, incorrect crack front node number
1439
Concrete model, initial temperature must be equal to reference temperature
1440
Curve description material, gravitational strain is outside the material curve
1441
Curve description material, error in pressure-volumetric strain calculations
1442
Curve description material model cannot be used with plane stress elements
1443
Crack front node number is out of range, please check your input data
1444
Zooming, incorrect solution starting time for the zoomed model
1445
Unit containing pipe internal pressure can not be opened as requested by input
1446
Input error in temperature loading data
1447
A file unit could not be opened as requested by the input
1448
Temperature gradients can only be specified on SHELL midsurface nodes
1449
BEAM pressure load cannot be generated. Incorrect input.
ADINA R & D, Inc.
A-15
Appendix 1
1450
Deformation dependent loading cannot be imposed on substructures
1451
Pressure (distributed) load is applied on non-existing nodes
1452
Pressure (distributed) loading, illegal face number
1453
Incorrect time function number specified for a load
1454
A distance between points defining an axis of rotation is zero or too small
1455
Contact slip load, contact surface, on which load is applied, does not exist
1456
Incorrectly applied contact slip load
1457
Input error in contact slip load
1458
Input error in concentrated load data
1459
Follower concentrated loading, incorrect input data
1460
Input error in electromagnetic load
1461
Ground motion loading is used with conflicting options
1462
Incorrectly applied load on a generalized plane strain element
1463
Prescribed displacements cannot be generated between two load sets
1464
A prescribed displacement is applied on a non-existing node
1465
Isobeam pressure load, incompatibility between face and auxiliary node numbers
1466
Incorrect pressure load data
1467
Pressure loading, incorrect load direction (x-axis) for y-z plane elements
1468
Input error in pipe internal pressure loading data
1469
Input error in pressure loading data
1470
FSI stress loading – FSI boundaries cannot be applied on substructures
1471
FSI (Fluid-Structure-Interaction) cannot be used with cyclic symmetry
1472
Input error in FSI boundaries (structural model)
1473
FSI forces, incorrect FSI boundaries in the structural model
1474
Potential-based fluid elements, loading used with conflicting options
1475
Potential-based fluids, error in load calculations due to mass fluxes
1476
Potential fluids, error in load calculations due to element face pressure
1477
Constrain equations cannot be applied to non-existing nodes
1478
Constrain equations, degree of freedom not marked as constrained
1479
Constrains, the independent degree of freedom is either fixed or constrained
1480
Rigid links cannot be applied to non-existing nodes
A-16
AUI Command Reference Manual: Vol. I − ADINA- Model Definition
Error messages
1481
A potential-based fluid interface element is not attached to a fluid element
1482
Incorrect input for 2-D flow load data
1483
Incorrect input for 3-D flow load data
1484
Input error in user-supplied loading data
1485
Incorrect input for fracture mechanics data
1486
A temperature file is requested but is either missing or not correct
1487
Error in shell element stress calculations
1488
Error in TMC analysis, only 2D and 3D elements are allowed
1489
Some of the master nodes used in constraints should be retained (shared) nodes
ADINA R & D, Inc.
A-17
Appendix 1
Initial stress & element group error messages Error Number
Description
1501
TRUSS-initial stresses can be used for linear elastic material only
1502
2-D SOLID – initial stresses can only be used for elastic & soil materials
1503
3-D SOLID – initial stresses can only be used for elastic & soil materials
1504
BEAM – initial stresses can only be used for linear elastic material model
1505
ISOBEAM – initial stresses can only be used for linear elastic material model
1506
PLATE – initial stresses can only be used for linear elastic material model
1507
SHELL – initial stresses can only be used for linear (iso & ortho) materials
1508
PIPE – initial stresses can only be used for linear elastic material model
1509
2-D POROUS – initial stresses can only be used with elastic and soil materials
1510
3-D POROUS – initial stresses can only be used with elastic and soil materials
1511
PLATE – initial strains cannot be used with the Ilyushin material model
1512
Material model used is not permitted in CDM with mixed u/p elements
1513
Program internal error, KPP matrix is not invertible, mixed u/p elements
1514
Program internal error, a matrix is not invertible, mixed nonlinear u/p elements
1515
2-D solid elements, incorrectly collapsed nodes, numbering sequence should be changed
1516
Plane stress elements have to have thickness provided via input(positive value)
1517
Energy release rate cannot be requested for more than three nodes
1518
Node numbers cannot be negative, please check your input data
1519
Incorrect 3-D transition element, nodes 22 & 27 can only be used in 27-node bricks
1520
Incorrect 3-D transition element, node 21 can only be used in 21-node bricks
1521
Axes of orthotropy and initial strains axes have to be orthogonal
1522
Maximum number of nodes exceeded for a 3-D solid (or fluid) element
1523
Incorrect number of nodes describing a 3-D solid (or fluid) element
1524
A transition elements cannot be a true tetrahedral element
1525
BEAM elements – incorrect input for a stress table
A-18
AUI Command Reference Manual: Vol. I − ADINA- Model Definition
Error messages
1526
BEAM elements – incorrect input for rigid end offsets
1527
BEAM (or ISOBEAM or PIPE) elements- incorrect auxiliary node number
1528
BEAM elements – zero cross-sectional area
1529
BEAM elements-negative rigidity input, the value must be greater or equal zero
1530
BEAM elements – incorrect input in the nonlinear elastic material data
1531
3-D solid elements, ULH – eigenvector cannot be computed
1532
Curve-description material, gravitational strain is too large
1533
Incompatible mode elements – a matrix is not invertible
1534
Ogden material model, initial strains are too large
1535
Mooney-Rivlin model, initial strains are larger than a maximum allowable value
1536
Foam material model, initial strains are larger than a maximum allowable value
1537
Invalid contact algorithm type
1538
Curve-description material model, incorrect volumetric pressure
1539
Curve-description material, current volumetric strain is outside the table input
1540
2D contact surface offsets cannot be based on shell thickness
1541
Layered shell elements, incorrect input for a layer number
1542
Layered shells, incorrect input data, pleas see the *.out file for details
1543
Specified material model or failure criterion is not used by any layered shell
1544
Error in the layered-shell input data, please see the *.out file for details
1545
Incorrect number of shell thickness tables for layered-shell elements
1546
Truss elements with gap, gap width cannot be negative
1547
Initial strains are too large
1548
BEAM element, error in the end release, very likely rigid body motion
1549
Incorrect thickness for isobeam axisymmetric or plane stress or strain elements
1550
Incorrect number of nodes describing an ISOBEAM (or PIPE) element
1551
ISOBEAM or PIPE elements – incorrect input for a stress table
1552
Stress printing or saving flag is incorrect
1553
isobeam(axisymmetric, plane stress/strain) elements must lie in the y-z plane
1554
Incorrect element configuration, the length cannot be smaller than zero
ADINA R & D, Inc.
A-19
Appendix 1
1555
ISOBEAM, both section dimensions have to have values greater than zero
1556
BEAM, ISOBEAM or PIPE elements – auxiliary node is not specified
1557
Element is not in a plane as required
1558
Auxiliary node cannot coincide or lie on a straight line with element nodes
1559
BEAM, ISOBEAM or PIPE – element nodes cannot have the same coordinates
1560
Incorrect number of nodes describing PIPE element
1561
Incorrect kinematic formulation requested for surface tension elements
1562
Surface tension elements, zero distance between nodes
1563
Incorrect number of composite shell failure sets
1564
SHELL elements, incorrect stress table input data
1565
Incorrect composite shell failure criterion number
1566
Incorrect number of nodes specified for a SHELL element
1567
Incorrect thickness table number for a SHELL element
1568
Incorrect transition SHELL element
1569
Error in the pressure-load shell-stiffness option
1570
Input error in shell stress resultant calculations
1571
Incorrect node definition for a SHELL element
1572
SHELL – director vectors cannot be created, incorrect element nodal data
1573
Incorrect bend radius for a PIPE element
1574
Incorrect input for a PIPE flange data
1575
Incorrect PIPE cross section dimensions
1576
Incorrect input data for 2-D contact elements
1577
Variable contact friction requested for contact pair & not specified for CGROUP
1578
Contact nodes refer to skew systems which is not indicated in control input
1579
Node-to-node cont, prescribed displacements cannot be applied to contactor nodes
1580
Zero mass on contact nodes is not allowed in explicit time integration
1581
Post-impact calculation, zero mass on contact nodes is not allowed
1582
Incorrect input data for 2-D rigid target contact
1583
Incorrect input data for 3-D contact elements
1584
3-D contact, incorrect contact segment number
A-20
AUI Command Reference Manual: Vol. I − ADINA- Model Definition
Error messages
1585
3-D contact, program internal error
1586
Incorrect input data for 3-D rigid-target contact
1587
General spring elements – input data errors
1588
Input error in 2-D fluid elements, please see *.out for details
1589
Input error in 3-D fluid elements, please see *.out for details
1590
Memory corrupted in 2-D fluid elements
1591
Memory corrupted in 3-D fluid elements
1592
Incorrect number of nodes for a spring element
1593
Potential-based infinite elements cannot be triangular
1594
Potential-based interface elements, incorrect number of nodes in an element
1595
Potential-based fluid elements, input error in material data
1596
General (spring, damping or mass) elements, incorrect property set number
1597
Incorrect input data for general (spring, damping or mass) elements
1598
Incorrect input data for a user-supplied general element
1599
Incorrect input data for a CGAP element
ADINA R & D, Inc.
A-21
Appendix 1
Frequency solution and element group error messages Error Number
Description
1601
Frequency – negative/zero diagonal element before decomposition. Incorrect model.
1602
Frequency – too many negative diagonal elements, please check your model
1603
Number of mass DOFs is smaller than the number of requested frequencies
1604
Frequency – rigid body shift input must be negative (FREQUENCIES...RSHIFT=-...)
1605
Frequency – zero pivot after decomposition, rigid body shift should be applied
1606
Frequency cannot be calculated for a single DOF, mass is not greater than zero.
1607
Frequency, determinant search method – rigid body mode found
1608
Determinant search method – lower bound of the first frequency not found, incorrect model
1609
Determinant search method – non-positive calculated shift, probably incorrect model
1610
Frequency calculation – no eigenvalue computed, please check your model
1611
Frequency-no eigenvalue computed, check for rigid body without fluid effects
1612
Determinant search method – upper bound of current eigenvalue not found, incorrect model
1613
Frequency – non-positive or too small calculated shift, probably incorrect model
1614
Frequency, potential based fluids – no convergence to rigid body mode
1615
Multi-block solution cannot be used if mass/stiffness are imported from file
1616
Could not factorize A*F=B – frequency and potential based fluid elements
1617
No convergence in eigensolver, please check your model or solution parameters
1618
Solution for linearized buckling failed, please check your model
1619
No convergence, subspace iteration, increase no. of iterations/starting vectors
1620
Upper bound for the first critical buckling load not found
1621
FREQUENCIES, interval too narrow, use higher value for FMAX or lower for FMIN
1622
Sturm sequence failed, no eigenvalue found, please check your model
1623
Frequencies, matrices not positive and no shift applied
A-22
AUI Command Reference Manual: Vol. I − ADINA- Model Definition
Error messages
1624
Frequency calculations failed, matrices not positive
1625
Frequencies, matrices not positive after a sweep or no shift applied
1626
Frequencies, JACOBI iteration could not converge, please check your model
1627
Lanczos method, stiffness matrix not positive definite, please check your model
1628
Lanczos method, not enough memory, please increase allocation for ADINA
1629
Lanczos method – internal error, please check your model
1630
Mode superposition, potential based fluid elements- program internal error
1631
Sturm sequence shows that incorrect number of frequencies has been calculated
1632
Mode superposition cannot be done with rigid body motions and potential fluids
1650
Estimated storage less than actual storage for element group - internal error
ADINA R & D, Inc.
A-23
Appendix 1
Material data errors Error Number
Description
1701
BEAM – bending table (R-T plane) input data cannot have negative values
1702
BEAM – bending table (R-T plane) input data cannot have zero values
1703
BEAM – multiplier used to compute stiffness of rigid end zones is negative
1704
BEAM – axial force table input data cannot have negative values
1705
BEAM – axial force table input data cannot have zero values
1706
BEAM – torsion table input data cannot have negative values
1706
BEAM – torsion table input data cannot have zero values
1708
BEAM – bending table (R-T plane) input data is not in ascending order
1709
BEAM – axial force table input data is not in ascending order
1710
BEAM – torsion table input data is not in ascending order
1711
BEAM – bending table (R-S plane) input data cannot have negative values
1712
BEAM – bending table (R-S plane) input data cannot have zero values
1713
BEAM – bending table (R-S plane) input data is not in ascending order
1714
BEAM – axial, bending, torsional cyclic factors must be greater or equal to 1.0
1715
Isotropic elastic material, Young's modulus and/or Poisson ratio is incorrect
1716
BEAM, rigidity, FORCE-AXIAL table, curve n-th slope is larger than the n-1 slope
1717
BEAM, rigidity, MOMENT-R (twist) table, n-th slope is larger than the n-1 slope
1718
BEAM, rigidity, MOMENT-S table, curve n-th slope is larger than the n-1 slope
1719
BEAM, rigidity, MOMENT-T table, curve n-th slope is larger than the n-1 slope
1720
Material creep-variable, effective stress is out of the stress range input
1721
Material creep-variable, yield curve cannot be interpolated, incorrect input
1722
Integration point temperature is outside material temperature range
1723
Material creep, integration point initial temperature is outside material temperature
1724
Material concrete, cut-off tensile stress SIGMAT has to be greater than zero
A-24
AUI Command Reference Manual: Vol. I − ADINA- Model Definition
Error messages
1725
Material concrete, incorrect input for SIGMAC, SIGMAU and/or EPSC, EPSU
1726
Zero point in axial force table not found
1727
Zero point in torsion table not found
1728
Position of zero point in torsion table varies with axial force
1729
Zero point in bending (R-T plane) table not found
1730
Position of zero point in bending (R-T) table varies with axial force
1731
Zero point in bending (R-S plane) table not found
1732
Position of zero point in bending (R-S) table varies with axial force
1733
Insufficient data points in axial force table (positive side)
1734
Insufficient data points in axial force table (negative side)
1735
Insufficient data points in torsion table (positive side)
1736
Insufficient data points in torsion table (negative side)
1737
Insufficient data points in bending (R-T plane) table (positive side)
1738
Insufficient data points in bending (R-T plane) table (negative side)
1739
Insufficient data points in bending (R-S plane) table (positive side)
1740
Insufficient data points in bending (R-S plane) table (negative side)
1741
Visco-elastic shear model, decay constants in Prony series cannot be equal to zero
1742
Visco-elastic shear model, number of terms in Prony series cannot be greater than 5
1743
Visco-elastic bulk mass, decay constants in Prony series cannot be equal to zero
1744
Visco-elastic bulk mass, number of terms in Prony series cannot be greater than 5
1745
User-supplied material, no convergence in effective plastic strain
1746
No convergence in plasticity. Using automatic time stepping might help.
1747
No convergence in the creep model. Using automatic time stepping might help.
1748
Strains outside input data, nonlinear elastic material model, truss elements
1749
Input error in irradiation creep property table input
1750
Input of mixed hardening parameters for von-Mises plasticity is incorrect
1751
Error in the optional printing for the large strain (ULH) formulation
1752
Input error in the material property data for 2-D solid elements
ADINA R & D, Inc.
A-25
Appendix 1
1753
Input error in the gasket material property data set
1754
Input error in the material property data for 3-D solid elements
1755
BEAM elements – error in the elasto-plastic moment- curvature input
1756
BEAM elements – error in the user-supplied material data
1757
BEAM elements – incorrect cross-section input data
1758
Orthotropic material model, incorrect material data
1759
Error in the truss material data input
1760
Fabric material model, material axis angle larger than 2*PI
1761
Incorrect material data input for the fabric model
1762
Incorrect material properties for a thermo-orthotropic material model
1763
BEAM element, plasticity, shear reduction factor must be smaller than 1.0
1764
Isotropic elastic material, coefficient of thermal expansion is negative
1765
Input error in the material property data for isobeam elements
1766
Input error in the material property data for plate elements
1767
Input error in the material property data for SHELL elements
1768
Input error in (composite) shell failure criteria
1769
Input error in the material property data for pipe elements
1770
Input error, SHELL orthotropic plasticity, constituent matrix not positive definite
1771
User-supplied material model, material axis angle larger than 2*PI
1772
thermo-orthotropic material model, material axis angle larger than 2*PI
1773
Orthotropic material model, material axis angle larger than 2*PI
1774
Porous elements, porous properties not available for material model used
1775
Input error in the material property data for 2-D porous elements
1776
Input error in the material property data for 3-D porous elements
1777
Incorrect material model for the gap element
1778
No initial stress input for Cam-Clay material model
A-26
AUI Command Reference Manual: Vol. I − ADINA- Model Definition
Error messages
General errors, messages Error Number
Description
1801
No convergence, iteration limit reached, automatic time stepping might help
1802
No convergence, out-of-balance load too large, automatic time stepping might help
1803
Zero (or almost zero) length between element nodes
1804
Zero (or almost zero) length of the orthotropic material axes vector
1805
Number of nodes exceeds the limit (900)
1806
Mapping Interface error, please contact ADINA R&D, Inc.
1807
Mapping program internal error, please contact ADINA R&D, Inc.
1808
Incorrect displacement boundary conditions for cyclic symmetry
1809
Incorrectly prescribed displacements on cyclic parts
1810
the number of prescribed displacements is greater than requested in the input
1811
Prescribed displacement unloading option cannot be used in linear analysis
1812
Incorrect degree of freedom (DOF) entry in the prescribed displacement input
1813
Arrival time cannot be negative. This holds for all load cases.
1814
Incorrectly prescribed displacements in cyclic symmetry analysis
1815
Internal error in cyclic symmetry, program stops
1816
A shell node on the cyclic boundary cannot have 5 degrees of freedom
1817
Cyclic symmetry, Y direction for nodes on the center line is not constrained
1818
Error(s) in cyclic symmetry
1819
Number of prescribed displacements is changed from one cyclic part to another
1820
Skyline solver (COLSOL) cannot be used with consistent contact algorithm
1821
Periodic symmetry cannot be used with explicit dynamic analysis
1822
Insufficient memory for double-sided contact algorithm
1823
Insufficient memory - FSI analysis. Use -R option (maximum memory for solution).
1824
Internal error in GASKET material, program stops
1825
Master degrees of freedom are modified in the restart run, which cannot be done
1826
Error in user-supplied friction model calculations
ADINA R & D, Inc.
A-27
Appendix 1
1827
Internal error in surface tension boundary, program stops
1828
Bad key in NASTRAN-OP2 stress output, program stops
1829
Error in NASTRAN-OP2 principal stress calculations, program stops
1830
EXP( ) is too large in Mooney-Rivlin material
1831
Non-positiveitive stretch in Ogden material
1832
Non-positiveitive stretch in hyper-foam material
1833
Bad isotropic model number in rubber
1834
Non-positive volume in 3-D rubber
1835
Bad orthotropic model number in rubber
1836
Zero pivot in stress-strain matrix for viscoelastic rubber
1837
Could not determine eigenvalues for viscoelastic rubber
1838
Could not determine actual J3 for Arruda-Boyce material
1839
Actual J3 out of range for Arruda-Boyce material
1840
Cannot use U/P formulation with hyper-foam material
1841
Bad isotropic model number in rubber
1842
Thermal strain less than -1.0 in rubber
1843
Too many orthotropic directions for orthotropic viscoelastic rubber
1844
EXP( ) is too large in orthotropic rubber
1845
Non-positive in-plane area in compressive plane stress rubber
1846
Bad isotropic model number in rubber
1847
Bad orthotropic model number in rubber
1848
Cannot find bounding out-of-plane stretches in rubber
1849
Cannot begin Newton iterations in rubber
1850
Zero slope in Newton iterations in rubber
1851
No convergence in Newton iterations in rubber
1852
Bad isotropic model number in rubber
1853
Non-positive stretch in compressive plane stress rubber
1854
Zero denominator in WLF shift function in rubber
1855
Bad isotropic model number in rubber
1856
Bad isotropic model number in rubber
1857
Bad isotropic model number in rubber
1858
Bad isotropic model number in rubber
A-28
AUI Command Reference Manual: Vol. I − ADINA- Model Definition
Error messages
1859
Non-positive in-plane area in incompressible plane stress rubber
1860
Invalid value for element STYPE in axisymmetric/plane strain rubber
1861
Non-positive volume in axisymmetric/plane strain rubber
1862
Non-positive stretch in incompressible plane stress rubber
1863
Non-positive in-plane area in incompressible plane stress rubber
1864
Invalid value for element STYPE in axisymmetric/plane strain rubber
1865
Non-positive stretch in axisymmetric/plane strain rubber
1866
Non-positive in-plane area in axisymmetric/plane strain rubber
1867
Non-positive volume in axisymmetric/plane strain rubber
1868
Non-positive in-plane area in orthotropic compressible plane stress rubber
1869
Excessive penetration in rigid target contact algorithm
1870
Fracture mechanics cannot be used in a distributed memory parallel processing
1871
ADINA trap error, program stops
1872
Excessive displacements in explicit analysis, probably due to unstable time step
1873
Material model not allowed in explicit analysis
1874
Mismatch of element parameters in 3-D restart analysis
1875
Mismatch of element parameters in 2-D restart analysis
1876
Mismatch of element parameters in shell restart analysis
1877
General constrains (or mesh gluing) cannot be used in explicit time integration
1878
Number of components in a general constraint equation is larger than the maximum specified value by the input
1879
Non-positive elastic Finger tensor in ULH shells
1880
Non-positive Finger tensor in ULH shells
1881
Invalid deformation tensor (from displacements) in ULH shells
1882
Invalid deformation tensor in ULH shells
1883
Non-positive volume in ULH shells
1884
Non-positive updated Jacobian determinant in ULH shells
ADINA R & D, Inc.
A-29
Appendix 1
Sparse solver messages Error Number
Description
1901
Problem too large for the 32-bit version, no. of matrix elements larger than 2E31
1902
Sparse solver could not open a file, please check your write permission
1903
Sparse solver, write file failed, please check your disk space
1904
Reading the L-matrix failed, please check the disk space the file size
1905
Sparse solver, write file failed, please check the disk space
1906
Sparse solver, write file failed, please check the disk space
1907
Sparse solver, read file failed, please check the disk space
1908
Sparse solver, read file failed, please check the disk space
1909
Not enough memory for in-core analysis, solver switches to out-of-core
1911
Sparse solver internal error, please contact ADINA R&D, Inc.
1940
Not enough memory on the system to be allocated for the solver
1941
Error in the multi-grid solver, program stops
1942
AMG iterative solver failed, please check your model or use another solver
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AUI Command Reference Manual: Vol. I − ADINA- Model Definition
Error messages
Errors with specific information Error Number
Description
2001
BEAM: group=… element=…, nodes 1 and 2 are too close to each other
2002
BEAM: group=… element=…, auxiliary node is not positioned correctly
2003
Error in closing a file (file probably does not exist), file=…
2004
No convergence in Gurson model, element group=…, element number=…
2005
Input ERROR, element group number=…, material property set number=…
2009
Stiffness matrix not positive definite, eqn=…, pivot=…
2010
Duplicate input in electromagnetic loading, nodes …
