MSC Laminate Modeler Version 2008 User's Guide

MSC Laminate Modeler

Version 2008 User’s Guide

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MSC.Software Corporation 2 MacArthur Place Santa Ana, CA 92707 USA Telephone: (800) 345-2078 Fax: (714) 784-4056

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Disclaimer This documentation, as well as the software described in it, is furnished under license and may be used only in accordance with the terms of such license. MSC.Software Corporation Corpor ation reserves the right to make changes in specifications and other information contained in this document without prior notice. The concepts, methods, and examples presented in this text are for illustrative and educational purposes only, and are not intended to be exhaustive or to apply to any particular engineering problem or design. MSC.Software Corporation assumes no liability or responsibility to any person or company for direct or indirect damages resulting from the use of any information contained herein. User Documentation: Copyright ©2008 MSC.Software Corporation. Printed in U.S.A. All Rights Reserved. This notice shall be marked on any reproduction of this documentation, in whole or in part. Any reproduction or distribution of this document, in whole or in part, without the prior written consent of MSC.Software Corporation is prohibited. The software described herein may contain certain third-party software that is protected by copyright and licensed from MSC.Software suppliers. Contains IBM XL Fortran for AIX V8.1, Runtime Modules, (c) Copyright IBM Corporation 1990-2002, All Rights Reserved. MSC, MSC/, MSC Nastran, MD Nastran, MSC Fatigue, Marc, Mar c, Patran, Dytran, and Laminate Modeler are trademarks trademar ks or registered trademarks of MSC.Software Corporation in the United States and/or other countries. NASTRAN is a registered trademark of NASA. PAM-CRASH is a trademark or registered trademark of ESI Group. SAMCEF is a trademark or registered trademark of Samtech SA. LS-DYNA is a trademark or registered trademark of Livermore Software Technology Corporation. ANSYS is a registered trademark of SAS IP, Inc., a wholly owned subsidiary of ANSYS Inc. ACIS is a registered trademark of Spatial Technology, Inc. ABAQUS, and CATIA are registered trademark of Dassault Systemes, SA. EUCLID is a registered trademark of Matra Datavision Corporation. FLEX lm is a registered trademark of Macrovision Corporation. HPGL is a trademark of Hewlett Packard. PostScr ipt is a registered trademark of Adobe Systems, Inc. PTC, CADDS and Pro/ENGINEER are trademarks or registered trademarks of Parametric Technology Corporation or its subsidiaries in the United States and/or other countries. Unigraphics, Parasolid and I-DEAS are registered trademarks of UGS Corp. a Siemens Group Company. All other brand names, product names or trademarks belong to their respective owners.

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Contents MSC Laminate Modeler User’s Guide

1

Overview Purpose

2

MSC.Laminate Modeler Product Information What is Included with this Product?

3

4

MSC.Laminate Modeler Integration with MSC.Patran What is MSC.Laminate Modeler?

2

5

6

Tutorial Introduction

10

Composite Materials and Manufacturing Processes Composite Materials 11 Common Material Forms 11 Common Manufacturing Forms 12

11

Composites Design, Analysis and Manufacture 15 The Development Process 15 Requirements of CAE Tools for Composites Development 15 Composites Development Within the MSC.Patran Environment Draping Simulation (Developable Surfaces) Definition of Developable Surfaces 21 Example of Waffle Plate 21 Benefits of MSC.Laminate Modeler 23

21

Draping Simulation (Non-Developable Surfaces) Definition of Non-Developable Surfaces 24 Benefits of MSC.Laminate Modeler 29 Building Models using Global Layers 30 Global Layer Description of Layup 30 Example of a Top Hat Section 31 Benefits of MSC.Laminate Modeler 33

24

19

iv MSC Laminate Modeler User’s Guide

Results Processing 34 Recovering Results by Global Layer Example of a Top Hat Section 34 Benefits of MSC.Laminate Modeler

34 37

Structural Optimization 38 Introducing Iteration to the Development Process Example of a Torque Tube with a Cutout 38 Benefits of MSC.Laminate Modeler 41 Glossary

3

42

Using MSC.Laminate Modeler Procedure

44

Element Library 46 46 Supported Element Topologies Supported Element Types 46 Supported Element Property Words 46 Initialization

48

Creating Materials 49 Create LM_Material Add Form Modify LM_Material Form 52 Show LM_Material Form 53 Delete LM_Material Select Form

51

54

Creating Plies 55 Create LM_Ply Add Form (Draping) Create LM_Ply Add Form (Projection) Modify LM_Ply Form 69 Show LM_Ply Graphics Form 70 Delete LM_Ply Select Form 71

56 68

Creating a Layup and an Analysis Model Create LM_Layup Add Form 73 Modify LM_Layup Add Form 80 Show LM_Layup Exploded View Form 81 Show LM_Layup Cross Section Form 82 Show LM_Layup Element Form 83 Show LM_Layup Element Info Form 84 Transform LM_Layup Mirror Form 85 Delete LM_Layup Select Form 86

72

38

CONTENTS

Creating Solid Elements and an Analysis Model 88 Create Solid Elements LM_Layup Form

87

Creating Laminate Materials 89 Create Laminate LM_Layup Form 90 Show Laminate Form 92 Delete Laminate Select Form 93 Delete Property Set Select Form 94 Creating Sorted Results 95 Create LM_Results LM_Ply Sort Form 96 Create LM_Results Material ID Sort Form 97 Creating Failure Results 98 Create LM_Results Failure Calc Form

99

Creating Design and Manufacturing Data Create Ply Book Layup Form 102 Importing Plies and Models Import Plies File Form 104 Import Model File Form 105

103

Importing and Exporting Laminate Materials Import Laminate LAP Form 107 108 Export Laminate LAP Form Setting Options 109 Set Export Options Form Set Display Options Form Session File Support Public PCL Functions Data Files

4

110 112 116 117

125

Example:Laminated Plate Overview

128

Model Description Modeling Procedure Step-By-Step

132

129 130

101

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vi MSC Laminate Modeler User’s Guide

5

Theory The Geometry of Surfaces

140

The Fabric Draping Process Results for Global Plies Composite Failure Criteria

A

Bibliography

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151 155

Chapter 1: Overvie Chapter Overview w MSC Laminate Modeler User’s Guide

1

Overview



Purpose



MSC.Laminate Modeler Product Information



What is Included with this Product?



MSC.Laminate Modeler Integration with Patran



What is MSC.Laminate Modeler?

2 3

4

6

5

2 MSC Laminate Modeler User’s Guide Purpose

Purpose Patran comprises a suite of products written and maintained by MSC.Software Corporation. The core of the product suite is Patran, a finite element analysis pre and postprocessor. Patran also includes several optional products such as application modules, advanced postprocessing programs, tightly coupled solvers, and interfaces to third party solvers. s olvers. This document describes one of these applicati on modules. For more information on the Patran suite of products, see the Patran Reference Manual. MSC.Laminate Modeler is a Patran module for aiding the design, analysis, and manufacture of laminated composite structures. The user can simulate the application of layers of reinforcing materials to selected areas of a surface to ensure that a design is realizable. Layers are then used to build up the composite construction in a manner that reflects the t he manufacture of the structure. Finite element properties and laminated materials are automatically generated so that accurate models of the structure can be evaluated rapidly. rapidly. Alternative solutions can be compared to optimize the structure at an early earl y stage of the development process.

Chapter Chapter 1: Overvie Overview w 3 MSC.Laminate Modeler Product Information

MSC.Laminate Modeler Product Information MSC.Laminate Modeler is a product of MSC.Softwa re Corporation. The program is available on all Patran supported platforms and allows identical functionality and file support across these platforms.

4 MSC Laminate Modeler User’s Guide What is Included with this Product?

What is Included with this Product? The MSC.Laminate Modeler product includes all of the following items: 1. PCL command command and library files which add the MSC.Laminate MSC.Laminate Modeler functionalit functionality y definitions definitions into Patran. 2. An external executable program for Layup manipulation and composite ply generation. 3. This Application Preference User’s Guide is included as part of the product. An online version is also provided to allow the user direct access to this information from within Patran.

Chapter Chapter 1: Overvie Overview w 5 MSC.Laminate Modeler Integration with Patran

MSC.Laminate Modeler Integration with Patran Figu Fi gure re 11-1 1 indicates how the MSC.Laminate Modeler library and associated programs fit into the Patran

environment.

Figure 1-1

MSC.Laminate MSC.Laminate Modeler Integration Integration with Patran Environment Environment

6 MSC Laminate Modeler User’s Guide What is MSC.Laminate Modeler?

What is MSC.Laminate Modeler? MSC.Laminate Modeler is a Patran module for aiding the design, analysis, and manufacture of laminated composite structures. By enabling the concept of concurrent engineering, MS C.Laminate Modeler allows the production of structures which take full advantage of these materials in the aerospace, automotive, marine, and other markets. The quality of the development process can be greatly improved because of the rigorous and repeatable manner in which MSC.Laminate Modeler defines fibre orientations. MSC.Laminate Modeler incorporates two key functionalities: simulation of the manufacturing process, and storage and manipulation of composite data on the basis of global layers.

Process Simulation Process simulation methods include draping of fabrics using various material and manufacturing options, in addition to the more conventional techniques of projecting fibre angles onto a surface. These options allow the use of MSC.Laminate Modeler for various production methods including manual layup of prepreg materials, Resin Transfer Moulding (RTM) (RTM) and filament winding. wi nding. Furthermore, MSC.Laminate Modeler reflects the open systems philosophy of Patran and can cater to customized simulation methods developed by customers.

Composite Data Management All data produced by the manufacturing simulation are s tored together and referenced as a single data entity. This structured representation allows efficient data handling in the actual design environment. For example, to apply predefined layers to an analysis model, the user simply adds them to a table in a process which reflects the real-world manufacture of the finished component. Alternative layups can be generated and evaluated rapidly to allow the designer to optimize the composite structure using existing structural analysis tools. The process of defining layups is inherently traceable, unlike the situation in conventional composites analysis where data is reduced to an unstructured element-based level which has no physical analogy. analogy. The functions available within MSC.Laminate Modeler allows the designer to visualize the manufacturing process and estimate the quantity of material involved. Representative analysis models of the component can be produced very rapidly to t o allow effective layup optimization. Finally, a “ply book” and other manufacturing data can be produced. These functions promise a significant increase in the efficiency of the development process for highperformance composite structures.

Chapter Chapter 1: Overvie Overview w 7 What is MSC.Laminate Modeler?

8 MSC Laminate Modeler User’s Guide What is MSC.Laminate Modeler?

Chapter 2: Tutoria Chapter Tutoriall MSC Laminate Modeler User’s Guide

2

Tutorial



Introduction



Composite Materials and Manufacturing Processes

11



Composite Materials and Manufacturing Processes

11



Composites Design, Analysis and Manufacture



Draping Simulation (Developable Surfaces)



Draping Simulation (Non-Developable Surfaces)



Building Models using Global Layers



Results Processing



Structural Optimization



Glossary

10

42

34 38

30

15

21 24

10 MSC Laminate Modeler User’s Guide Introduction

Introduction This manual is intended to introduce the reader to the most common methods of composite manufacture, and define what is required of an effective tool for simultaneous composites engineering. Thereafter, some examples of the use of the MSC.Laminate MS C.Laminate Modeler are presented to illustrate the us efulness of this module in the composites development process.

Chapter Chapter 2: Tutoria Tutoriall 11 Composite Materials and Manufacturing Processes

Composite Materials and Manufacturing Processes Composite Materials Composite materials are composed of a mixture of two or more constit uents, giving them mechanical and thermal properties which can be significantly better than those of homogeneous metals, polymers and ceramics. An important class of composite materials are filamentary composites which consist of long fibres embedded in a tough matrix. Materials of this type include graphite fibre/epoxy resin composites widely used in the aerospace industry, and glass fibre/polyester mixtures which have wide applicability in the marine and automotive markets. Because of their predominance in high-quality structures which need to be analyzed before manufacture, the term composite material will refer to a filamentary composite having a resin matrix in this document. Furthermore, it will be as sumed that the composite is manufactured in distinct layers, which is appropriate for almost all filamentary composite materials. By decreasing the characteristic size of the microstructure and providing large interface areas, the toughness of the composite material is i s improved significantly compared with that of a homogeneous solid made of the same material as the fibres. In addition, the manufacturing m anufacturing processes of many components can be simplified by applying the fibres t o the component in a manner which is compatible with its geometry. These and other considerations mean that composite materials are an effective engineering material for many types of structure. However, filamentary composite materials are often characteri zed by strongly anisotropic behavior and wide variations in mechanical properties which are a direct result of the manufacturing route for a component. In addition, the cost of a composite component is highly dependent on the w ay the fibres are applied to a surface. This means that designers must be aware of the consequences of manufacturing considerations from the beginning of the development phase.

Common Material Forms Filamentary composite materials are usually placed in components as tows (bundles of individual fibres) or as fabrics which have been processed in a separate operation.

Tows A large proportion of commercially-produced components are built up from layers of fibre tows laid parallel to each other. Each tow consists of a large number of individual fibres as each fiber is usually usual ly too thin to process effectively. For example, graphite tows typically contain between 1000 to 10000 fibres. Tows containing many fibres result in cheaper components at some expense of mechanical properties. Composite structures built up from tows have the greatest volume fraction of fibres which usually lead to the most favorable theoretical mechanical properties. They are also characterized by extreme anisotropy. For example, the strength and stiffness of a resulting layer may be ten times greater in the direction of the fibres compared with an orthogonal direction.

12 MSC Laminate Modeler User’s Guide Composite Materials and Manufacturing Processes

Fabrics Individual tows may also be woven or stitched into fabrics which are used to form the component. This method effectively allows much of the fibre preparation to be completed under controlled conditions, while components can be rapidly built up from fabric during the final stage of manufacture. Composite structures built up from fabrics are generally easier to manufacture and exhibit superior toughness compared with those built up from tows, with some loss in ultimate mechanical properties.

Mixed Some processing methods allow the user to mix tows and fabrics to achieve optimum performance. An example of this is a composite I-beam, where the shear-loaded web consists of a fabric, while the axiallyloaded flanges have a high proportion of fibres oriented along the beam.

Common Manufacturing Forms Composite structures are manufactured using a wide variet y of manufacturing routes. The ideal processing route for a particular structure will depend on the chosen fiber and matrix type, processing volume, quality required, and the form of the component. All these issues should be addressed right from the beginning of the development cycle for a component or structure. A feature of almost all the manufacturing processes is that the fibres are formed into the final structure in layers. The thickness of each layer typically ranges between 0.125 mm (0.005”) for aerospace-grade pre-pregs up to several millimeters for woven rovings (say, 0.25”). This means that a component is usually built up of a large number of layers which may be oriented in different directions to achieve the desired structural response. Another consequence of layer-based manufacturing is that a laminated area is usually thin compared with its area. This means that the dominant loads are in the plane of the fibres, and that classical lamination theory (which assumes that through-thickness stresses are negligible) and shell finite elements can be used to conduct representative analyses. In contrast, in particularly thick or curved skins, inter-laminar tensile and shear stresses can be significant. This can seriously compromise static and fatigue strength and may require the use of through-thickness reinforcement. Another consequence of thi ck laminates is that the analyst must use special thick shell or solid elements to model the stress fields correctly.

Wet Layup In the wet layup process, fibres are placed on a mould surface in fabric form and manually wetted-out with resin. Wet layup is widely used to make large structures, like the hulls of small ships. This process is amenable to high production rates but results in wide variations in quality. In particular, the inability to control the ratio of fibres to resin means that the mechanical properties of the laminate will vary from point-to-point and structure-to-structure.

Chapter Chapter 2: Tutoria Tutoriall 13 Composite Materials and Manufacturing Processes

Pre-Preg Layup In this process, tows or fabrics are impregnated wit h controlled quantities of resin before being placed on a mould. Pre-preg layup is typically used to t o make high-quality components for the aerospace industry. This process results in particularly consistent components and structures. Because of this, pre-preg techniques are often associated with sophisticated resin s ystems which require curing in autoclaves under conditions of high temperature and pressure. However, the application of pre-preg layers to a surface is highly labor-intensive, and can only be automated for a small class of simple structures.

Compression Moulding Compression moulding describes the process whereby a stack of pre-impregnated layers are compressed between a set matched dies using a powerful press, and then cured while under compression. This method is often used to manufacture small quantities of high-quality components such as crash helmets and bicycle frames. Due to the use of matched dies, the dimensional tolerances and mechanical properties of the finished component are extremely consistent. However, the requirement to trim the component after curing and the need for a large press means that this method me thod is extremely expensive. Also, it is very difficult to make components where the plies drop off consistently within the component.

Resin Transfer Moulding (RTM) / Structural Reaction Injection Moulding (SRIM) Here, dry fibres are built up into intermediate preforms using tows and fabric held together by a thermoplastic binder. One or more preforms are then placed into a closed mould, after which res in is injected and cured to form a fully-shaped component of high quality and consistency. The in-mould cycle time for RTM is of the order of several minutes, while that for SRIM is measured in seconds. As fibres are manipulated in a dry state, these processes provide unmatched design flexibility. RTM produces good-quality components efficiently but incurs high initial costs for tooling and development. As a result, there is often a cross-over point between pre-preg layup and RTM for the manufacture of high-quality components like spinners for aero engines. At a lower level, SRIM is used for the manufacture of automotive parts which have a lower volume fraction of fibres.

Filament Winding In this method, tows are wet-out with resin before being wound onto a mandrel which is rotated in space. This process is used for cylindrical and spherical components such as pipes and pressure vessels. Winding is inherently automated, so it allows consistent components to be manufactured cheaply. However, the range of component geometries amenable to this method is somewhat limited.

Automated Tow Placement This development of filament winding utilizes a computer-controlled 5-axis head to apply individual tows to a mandrel rotating in space. This allows the manufacture of complex surfaces, such as entire helicopter body shells with speed and precision.

14 MSC Laminate Modeler User’s Guide Composite Materials and Manufacturing Processes

Of course, the equipment required for manufacture is extremely expensive, being of the order of $1 million. In addition, the possibilities for fibre placement are so controllable that no component can possibly make use of the capabilities capabilit ies of the process at present. However, the development of CAE tools for optimized design of composite structures will increase its usefulness in the future.

Chapter Chapter 2: Tutoria Tutoriall 15 Composites Design, Analysis and Manufacture

Composites Design, Analysis and Manufacture The Development Process The development process for any component consists of design, analysis and manufacturing phases, which are sometimes undertaken by separate groups within large organizations. However, for composites, these functions are inextricably linked and must be undertaken simultaneously if the component is to be manufactured economically. Thus, the principles of concurrent engineering must be followed particularly closely for composites development. In general, the development process incorporates three phases: Conceptual Development - here, the development team generates a number of conceptual solutions based

on their interpretation of the requirements and knowledge of composite materials and processes. Outline Development - thereafter, surface geometry is defined, a preliminary layup determined and

analysis undertaken. Based on the interpretation of analysis results, the outline design may be modified through several iterations before an acceptable solution is reached. Detailed Development - detailed drawings of the structure and required tooling are prepared together with

plans for production.

Requirements of CAE Tools for Composites Development The outline development process is the most critical phase in refining a design solution. Composite components and structures can be an order of magnitude more complex than items made of homogeneous materials. It is, therefore, essential to automate many repetitive tasks using computer-based tools. Depending on the application, these tools should have one or more of the features defined below.

Integration of CAD/CAE/CAM Systems It is important to integrate all tools for composites engineering within a single environment to allow Figure ure 2-1). simultaneous development of a product (see Fig Furthermore, all design and manufacturing information should be readily transferable to and from a CAD system so that the intent of an optimized design can be realized.

16 MSC Laminate Modeler User’s Guide Composites Design, Analysis and Manufacture

Figure 2-1

Integrated Integrated Composites Composites Development Development Environment Environment

Layer-Based Modeling The fundamental requirement is that the CAE CA E tools treat the composite structure in a manner which reflects the real-world structure. In particular, many conventional CAE tools store and manipulate data on the basis of laminate materials as shown in Fig Figure ure 2-2. This representation means that the model becomes extremely complicated as soon as the layers making up the structure overlap. In contrast, all CAE tools should store the data describing the structure in terms of its constituent layers. This ensures that the construction is always representative of the manufacturing method, making the model easy to understand. Furthermore, changes are easily effected by adding and removing layers.


Figure 2-2

Comparison Comparison of Global Layer and Laminate Material Descriptions Descriptions for a Simple Structure

Layer-Based Results Processing Any optimization during the development process is likely to involve the interpretation of results for various analyses. These results should be interpreted on the basis of layers, in the same way that the component is manufactured. Furthermore, it should be possible to visualize results in the reference system of the material making up a layer, even where this reference system changes constantly over a surface.

Mass and Cost Calculation The cost of composites materials are generally high. A CAE tool should allow all ow the designer to interrogate the materials usage and approximate cost at any point in the development cycle.

Visualization Tools Sufficient visualization tools should be provided to ensure that the form of the structure is easily checked and communicated. Such tools would include the ability to interrogate the extent and orientation of


layers, generate core samples at various points, generate cross sections along arbitrary lines, and generate a layer sequence table.

Manufacturing Guides Any CAE tool should produce fool-proof manufacturing guides, so that the design and analyses components are actually manufactured. For structures manufactured from sheet materials, this could take the form of a “ply-book” which has a page for every layer. This should present the cutout shape, views of the three-dimensional moulded shape and other essential information.

Mould Surface and Insert Shape Definition Typically, layers will be placed on a male or female mould surface. If the mould tool is closed. The software should calculate the exact thickness of the laminate stack which has been defined. This should include the effect of thickening which can occur as woven material is sheared to conform to a surface. Thereafter, a second mould surface should be defined which is offset from the original surface by the correct amount. It should also be possible to define a secondary mould surface, and automatically define the cutout shapes of individual plies required to fill the entire mould.

Materials Data Management Because composite materials are generally anisotropic, and have more variability in their properties than homogeneous materials, it is important to store and manipulate materials data in a consistent manner throughout the design process. In particular, the same data should be used for all subsequent analyses, s o that any change is reflected throughout the entire cycle. The state of composite materials can also be highly dependent on temperature, moisture content, and even the degree of shear which might be induced in a manufacturing process. This means that all data should be stored as a function of state, stat e, and the correct information retrieved for any analysis. Because of the wide variety of states possible, material property data will only be available for a few states. It is, therefore, necessary to interpolate material property data for intermediate states in a rational and repeatable manner. For example, if the properties of fabric a re known when the warp and fill fibers are 90 and 60 degrees apart, the software should also calculate equivalent properties for 75 degrees separation.

Drape Analysis A large proportion of composite structures are manufactured by placing essentially two-dimensional sheets of fabric onto three-dimensional surfaces. If the surface has curvature, then the shape of the sheet cannot be inferred directly from a projection of the surface onto a plane. Therefore, the draping simulation software must produce the cutout shape of the layer before it is applied to the surface. If the surface is doubly-curved at any point, it is non-developable. In this case, the sheet s heet material must shear in its plane to allow it to conform to the surface. The software must illustrate the degree of shearing in the sheet, and update the material materia l property references to account for the changed material state. The


shearing also means that the orientation of the material changes dramatically over a curved surface. The correct orientations must therefore be passed through transparently t o all relevant analysis codes. Sheet material can be extremely expensive. Therefore, so-called nesting software should be used to minimize the material required by aligning and placing the cutouts in an optimum way.

Structural Analysis Any composite part must be thoroughly analyzed to ensure that it will withst and service loads. Many composite components are relatively thin so that through-thickness stresses are low. This means that shell elements can be used to model the structure adequately. However, to model through-thickness stresses, solid elements must be used. For some problems, such as investigating through-thickness stresses at edges, many high-order elements will be required through the thickness of t he laminate to model stresses at all reasonably. reasonably. A major concern with composite materials are their resistance to damage, as the degradation of the material is very complex and not well understood. It is, therefore, important that the structural analysis codes provide for modelling the initiation, growth and effects of defects.

Resin Flow Analysis Resin flow should be analyzed for processes such as RTM to ensure that pockets of air are not trapped in the moulding, causing defects. In addition, resin flow has a dominant effect on cycle time, with its i ts ongoing effect on manufacturing cost.

Cure Analysis The curing of a composite component should be analyzed to dete rmine the cycle time of the process. process . Also, it is essential to determine the extent of springback in the cured component.

Mould Tool Analysis Mould tool analysis is required to estimate deflections in the tool where small tolerances are required. The thermal behavior of the mould can also have a significant effect on the cutting of a composite component.

Composites Development Within the Patran Environment The Patran environment provides a rich core environment for the development of composite structures. Existing links are readily used to import geometry from leading CAD systems including CATDirect, CADDS 5, Unigraphics, Unigraphics, Pro/ENGINEE Pro/ENGINEER R and Euclid 3. Meshing and and other general general pre and postprocessing functions are available within Patran itself. Finally, the preference system enables the seamless use of a variety of analysis systems which would be useful for composites development.

MSC.Mvision MSC.Mvision allows the user to t o store and handle complex materials data such su ch as that required for composites development.


MSC.Laminate Modeler The MSC.Laminate Modeler adds dedicated layer-based modeling and results processing functionality to Patran. This support greatly improves the ability of the user to define and modify representative composite structures, and then analyze their behavior using analysis packages supported by preferences. The module also includes a drape simulation simulati on facility which can handle non-developable surfaces. This allows the user to understand the deformation required of a sheet of fabric to cover a s urface, predicts realistic material orientations over individual elements, and produces cutout shapes for use by CAM systems.

Patran FEA This general-purpose finite element analysis solver includes QUAD4/8 and TRI3/6 laminates shell elements which account for bending and extension deformation of a shell. The linear strain elements also model the transverse shear flexibility of the laminate. HEX8/20 and WEDGE6/15 elements are available to model the flexibility of a laminate in all directions. All composite elements provide the facility for inputting nonlinear material properties.

Patran Composite This specialized finite element analysis solver is used for detailed analysis of laminates with complex fibre geometry or unusual material behavior. It utilizes a family of elements with tri-cubic interpolation functions, with up to HEX64 topology t opology.. These allow the calculation calculati on of high stress gradients, such as occur at free edges or in components which suffer severe thermal stress during processing.

Chapter Chapter 2: Tutoria Tutoriall 21 Draping Simulation (Developable Surfaces)

Draping Simulation (Developable Surfaces) Definition of Developable Surfaces An important subset of curved surfaces is developable surfaces. These surfaces can always be manufactured using sheet materials without the material needing to shear. At any point, there will be no curvature in one direction and maximum curvature in the orthogonal direction. Mathematically, this means that these surfaces are characterized by zero Gaussian curvature over their entire area. Cylinders are one example of developable surfaces found in many structures. Note that all developable surfaces are ruled surfaces. However, not all ruled surfaces are developable. For example, a hyperbola of one sheet (such as a cooling tower shape) is not developable. Although many CAD systems have provision for developing flat patterns from developable surfaces, the definition of material orientation is not trivial, particularly when the curvature is great. The draping process for development is unique. That means that the cutout profile is always the same, and that definition of fibre orientation at any point uniquely describe the fibre orientations at all other points on the surface.

Example of Waffle Plate One example of a developable surface with complex fibre orientations is a waffle plate used as a core for sandwich structures. A typical geometry for a circular sandwich structure is shown in Fig Figure ure 2-3. As the core is predominantly loaded in shear, it would be if the majority of fibres lay in the +/-45 directions directi ons along the webs. However, if these directions are ideal for one web, they will obviously not be the same for other webs.

22 MSC Laminate Modeler User’s Guide Draping Simulation (Developable Surfaces)

Figure 2-3

Geometry of a Curved Waffle Plate

The MSC.Laminate Modeler can be used to quantify the effect of varying fibre orientation both qualitatively and quantitatively. For example, if a piece of woven fabric is draped from the middle rib so that the average angle is +/-45 + /-45 along the webs of the central rib, we see that the angle on the webs near the edge of the plate are more like 0/90. This latter direction will obviously result in poor shear s tiffness and strength in this direction. Having understood this limitation, the designer can then make an informed decision whether to specify a quai-isotropic layup for the whole of the waffle plate, or to make the waffle plate out of several different plies oriented in different directions. Both alternatives can be modeled and analyzed rapidly using the MSC.Laminate Modeler, and an informed choice made on the basis of analysis results.

Chapter Chapter 2: Tutoria Tutoriall 23 Draping Simulation (Developable Surfaces)

Figure 2-4

Variation of Fibre Angles over Waffle Plate

Benefits of MSC.Laminate Modeler 1. Visual feedba feedback ck of fibre fibre orientat orientation. ion. 2. Accurate Accurate orientation orientation data data for analysis analysis model. model. 3. Exact flat-pattern flat-pattern generation. generation.

24 MSC Laminate Modeler User’s Guide Draping Simulation (Non-Developable Surfaces)

Draping Simulation (Non-Developable Surfaces) Definition of Non-Developable Surfaces Non-developable surfaces are those which cannot be formed from sheet material without the material shearing in its plane. Surfaces of this type have curvatures in two different directions (they are therefore often called doubly-curved surfaces). Although these surfaces are usually more difficult to manufacture than flat or developable surfaces, their form gives them great stiffness and strength. Because composite materials can often shear during the manufacturing process, they are more suitable for manufacturing these shapes than conventional materials like aluminium. This magnifies the advantage of laminated composite materials for many classes of structure.

Gaussian Curvature The extent of double curvature at any point is reflected in a value called the Gaussian curvature. This is the product of the curvatures in the principal princi pal directions at any point on a surface. su rface. The Gaussian curvature reveals many of the characteristics of a surface. Positive Gaussian curvature means that the surface is locally dome-shaped, with the curvatures in the same direction with respect to the surface normal. In contrast, negative Gaussian curvature implies saddle-shaped topology, with curvatures in opposite directions. Finally, zero Gaussian curvature is characteristic of a developable area. Note that surfaces often have varying Gaussian curvature over their extent. As an example, a torus (donut) is saddle-shaped on the inside (negative Gauss ian curvature) but dome-shaped on the outside (positive Gaussian curvature). Gaussian curvature can be given a physical significance by drawing geodesic lines on a surface. (Geodesic lines are straight in the plane of the surface at any point; meridians are geodesic, but lines of latitude are constantly turning in one direction with respect to the surface.) A pair of lines which are initially parallel will t end to converge on surfaces of positive Gaussian curvature, but will diverge on a surface of negative Gaussian curvature. In contrast, the lines will remain parallel on the surface until they reach an edge if the surface is developable. Another interpretation of Gaussian curvature is the extent of misfit in the surface. Consider a circular disk made up of several flat segments. This necessarily has zero Gaussian curvature even if it is bent along the joints between segments. However, if one of the segments is removed and the neighboring segments joined, the disk will adopt a dome-like shape which is indicative of positive Gaussian curvature. In contrast, adding a segment will result in the disk forming a saddle-like shape with negative Gaussian curvature.

Drape Simulation for Non-Developable Surfaces Draping of non-developable surfaces is an extremely difficult task. Essentially, this process involves extremely large geometric and, perhaps, material nonlinearities. A direct consequence of this is that there is no unique solution for the draping process . The draped shape is highly dependent on the point at which the draping starts, the directions in which the draping proceeds and the properties of the material itself. In addition, if there is interaction between different layers, friction between them would have a

Chapter Chapter 2: Tutoria Tutoriall 25 Draping Simulation (Non-Developable Surfaces)

significant effect. A detailed analysis of the draping process for arbitrary geometries is therefore a considerable analysis task in itself. This difficulty in analysis reflects a real-world difficulty in manufacturing complex composite components consistently. Engineering drawings of composite components typically specify fibre angles within a tolerance of 3 degrees. In practice, practi ce, if there is significant curvature in a surface, the manufacturing tolerance could easily reach 15 degrees or more. These problems can be mitigated to a large extent by limiting the degree of shear developed wi thin reinforcing layers during the manufacturing process. The degree of shear is primarily dependent on the Gaussian curvature and the area of a layer. Therefore, a design incorporating two layers of excessive shear can be replaced by three smaller layers with less shear and greater quality. The MSC.Laminate Modeler employs a rapid draping module which allows the designer to investigate the likely degree of shear, and make rational engineering decisions on the basis of manufacturing simulations. Whatever simulation process is used, two different levels of draping should be considered. Local Draping reflects the behavior of an infinitesimal material element applied to a point on a surface having general curvature. This is a material characteristic and is determined from tests on material s. In contrast, Global Draping considers how the many material elements are placed on a surface, and is dependent on the manufacturing process used.

Local Draping Models Local draping is concerned with fitting a small s mall section of material to a generally-curved surface. If the surface has nonzero Gaussian curvature, the material element must shear in its plane to conform to the surface. This deformation is highly dependent on the microstructure of the material. As a result, local shearing behavior can be regarded as a layer material property.

Figure 2-5

Scissor Draping Mechanism Mechanism


Figure 2-6

Slide Draping Mechanism Mechanism

MSC.Laminate Modeler currently supports two local draping algorithms: scissor and slide draping. For Figu gure re 22-5 5), an element of material which is originally square shears in a trellis-like scissor draping (Fi mode about its vertices to form a rhombus. In particular, the sides of the material element remain of constant length. This type of deformation behavior is characteristic of woven fabrics which are widely used to manufacture highly-curved composite components. For slide draping ( Fi Figu gure re 22-6 6), two opposite sides of a square material element can slide parallel to each other while their separation remains constant. This is intended to model the application of parallel strips of material to a surface. It can c an also model, very simply, the relative sliding of adjacent tows making up a strip of unidirectional material. When draping a given surface using the two different local draping algorithms, the shear in the layer builds up far more rapidly for the slide s lide draping mechanism than for the scissor sciss or draping mechanism. This observation is compatible with actual manufacturing experience that woven fabrics are more suitable for draping curved surfaces than unidirectional pre-pregs. For small deformations, the predictions of the different algorithms are practically identical. Therefore, it is suggested that the scissor draping algorithm be used in the first instance.

Global Draping Models Global draping is concerned with placing a real s heet of material onto a surface of general curvature. This is not a trivial task as there are infinite ways of doing this if the surface has nonzero Gaussian curvature at any point. Therefore, it is important to define procedures for the global draping simulation which are reproducible and reflect what can be manufactured in a production sit uation. As a result, global draping behavior can be regarded as a manufacturing, rather than material , property. property. The MSC.Laminate Modeler currently supports three different global draping algorithms: Geodesic, Planar and Energy. Energy. For the Geodesic global draping option, principal axes are drawn away from the starting point along geodesic paths on the surface (i.e., the lines are always straight with respect to the surface). Once these principal axes are defined, there is then a unique solution for draping the remainder of the surface. This may be considered the most “natural” method and appropriate for conventional laminating methods. However, for highly-curved surfaces, the paths of geodesic lines are highly dependent on initial conditions and so the drape simulation must be handled with care.


For the Planar global draping option, the principal axes may be defined by the intersecti on of warp (and weft for scissor draping) planes which pass through the viewing direction. This method is appropriate where the body has some symmetry, or where the layup is defined on a space-centered rather than a surface-centered basis. Finally, the Energy global draping option is provided for draping highly-curved surfaces where the t he manufacturing tolerances are necessarily greater. Here, the draping proceeds outwards from the start point, while the direction of draping is controlled by minimizing the shear strain energy along each edge.

Example of a Pressure Vessel Many pressure vessels are made of composite materials, particularly via the filament winding process. However, it is often necessary to add woven reinforcements to the shell. In this case, it is vital to understand the mechanics of the draping process because the curvature of the surface varies so much. In particular, the body of a pressure vessel is developable and has zero gaussian curvature. In contrast, the ends have constant positive Gaussian curvature. Figure ure 2-7), the shear in the material increases rapidly away If draping begins at the pole of the vessel ( Fig from the start point due to the severe s evere curvature. The amount of shearing is indicated by the color of the draping pattern lines. Note that the degree of shear is zero along the principal axes, which are defined by geodesic lines.

The draping algorithm stops where the shear reaches the cutoff value for the material, or the override value defined in the Additional Controls form. This gives an indication of where the material would fold when being formed.


Figure 2-7

Fibre Directions Directions for Draping Starting at the Pole of the Vessel

To cover the same area, it is also possible to begin draping on the cylindrical part of the surface (Fig Figure ure 2-8). Because this region is developable, there is no shear deformation until the end cap is reached. This means that the average degree of shear on the surface is much lower, lowe r, which should lead to better quality and better mechanical performance.


Figure 2-8

Fiber Directions Directions for Draping Starting on the Cylindrical Cylindrical Part of the Vessel

Benefits of MSC.Laminate Modeler 1. Visual feedba feedback ck of fibre fibre orientat orientation. ion. 2. Visual feedback feedback of material material shear. shear. 3. Orientation Orientation data for for analysis analysis model. 4. Flat patte pattern rn genera generation tion..

30 MSC Laminate Modeler User’s Guide Building Models using Global Layers

Building Models using Global Layers Global Layer Description of Layup The model is built up from predefined layers using a spreadsheet. This mirrors the use of layup tables in the final drawings of a component. The models are easily modified by defining, adding and deleting new layers to or from the layup.

Figure 2-9

Spreadsheet Spreadsheet For Defining the Layup Using Predefined Predefined Layers

Chapter Chapter 2: Tutoria Tutoriall 31 Building Models using Global Layers

Example of a Top Hat Section A typical top-hat section subjected to pressure and bending load will be used to illustrate the building of models using global layers. The model itself it self consists of a total of 52 global layers arranged in 4 different laminates. To model this structure properly, using conventional methods, would require the definition of 11 different property regions containing between 16 and 48 layers each. This would be tedious to define, and almost impossible to modify if the user wished to conduct a rapid sensitivity analysis.

Figure 2-10

Geometry Geometry of the Top Hat Section

32 MSC Laminate Modeler User’s Guide Building Models using Global Layers

Figure 2-11

Lamination Specification Specification of the Top Hat Section

In contrast, the MSC.Laminate Modeler user simply needs to define four layers which cover the areas of each laminate. Then, multiples of these layers are added to the model, using the layup spreadsheet. Because the surface is developable, it is permissible to use the Angular Offset option to modify the orientation of the plies at 45, 90 and -45 to the original layers. All the generation of representative property regions would be handled completely automatically by the software.

Chapter Chapter 2: Tutoria Tutoriall 33 Building Models using Global Layers

Figure 2-12

Visualization Visualization of Geometry Covered by Layer_3

The greatest benefit would, of course, accrue if the model needed to be changed after a preliminary analysis. For example, the user may wish to define localized reinforcement at the attachment end of the section. This could be completed in a matter m atter of minutes by defining additional layers and adding them to the layup.

Benefits of MSC.Laminate Modeler 1. Rapid layer-ba layer-based sed generation generation and modificat modification ion of model.

34 MSC Laminate Modeler User’s Guide Results Processing

Results Processing Recovering Results by Global Layer Conventional systems present stresses on the basis of a particular layer on individual elements. If any element is reversed, or there are ply drop-offs on the surface, the produced results cannot be interpreted meaningfully. In contrast, the MSC.Laminate Modeler rearranges analysis results stored in the database so that they refer to global layers defined in the layup spreadsheet. This means that the results for a physically meaningful piece of fabric are presented together. This is a unique capability for the maj ority of codes that store composite data on the basis of laminate materials.

Example of a Top Hat Section Fringe plots for stresses along the fibres are presented for global layers 1, 17, 21 and 33 for the top-hat section model. Using conventional post-processors, this would give misleading results due to the variation of layup over the model. In contrast, all stresses presented here are continuous, indicating that the correct results have been grouped for each global layer.

Figur Figure e 2-13 2-13

Chapter Chapter 2: Tutoria Tutoriall 35 Results Processing

Figure 2-14

Layer Results

36 MSC Laminate Modeler User’s Guide Results Processing

Figure 2-15

Layer Results

Chapter Chapter 2: Tutoria Tutoriall 37 Results Processing

Figure 2-16

Layer Results

Benefits of MSC.Laminate Modeler 1. Flexible Flexible layer-base layer-based d results results processing. processing.

38 MSC Laminate Modeler User’s Guide Structural Optimization

Structural Optimization Introducing Iteration to the Development Process The ability to modify a composite model rapidly and asses results on a realistic basis opens up many opportunities for the optimization of composite structures. This is essential to compete with highlyoptimized structures made of conventional materials, and bring the cost of composite structures down to a competitive level.

Example of a Torque Tube with a Cutout A tube subject to torsional loading and having a l arge cutout is representative of a number of structures, including the chassis of a single-seater racing raci ng car. A layup was defined, using two global layers covering Figure ure 2-1 2-17 7 and Fig Figure ure 2-1 2-18 8. the entire surface, and the rim around the cutout respectively as shown in Fig

Figure 2-17

Analysis Model of Torsion Tube

Chapter Chapter 2: Tutoria Tutoriall 39 Structural Optimization

Figure 2-18

Stiffened Collar

Models were built with a uniform layup, and including layer_2 reinforcement around the cutout. Figure ure 2-1 2-19 9, Analyses were then conducted for both configurations. As shown in the deformation plot in Fig the torsional load generates substantial out-of-plane deflections around the cutout. Therefore, it is to be expected that reinforcing the cutout edge will have a significant effect on the structural performance of the tube.

40 MSC Laminate Modeler User’s Guide Structural Optimization

Figure 2-19

Deformed Shape of Analysis Model

The analysis results for both models are summarized in the table below.

Property

Uniform Layup

Reinforced Layup

Difference

Layup

layer_1 (0/45/-45/90) layer_1 (90/-45/45/0)

layer_2 (0/45/-45/90) layer_1 (0/45/-45/90) layer_1 (90/-45/45/0) layer_2 (90/-45/45/0)

layer_2 (0/45/-45/90) layer_2 (90/-45/45/0)

Ma ss

4.826 kg

5.035 kg

0.209 kg (+4.3%)

Rotation

0.143

0.118

-0.025 (-18%)

Max. Deflection

2.817 mm

1.800 mm

-1.017 mm(-36%)

Max. Tensile Fiber Stress

165 MPa

122 MPa

43 MPa (-26%)

Max. Compressive Fiber Stress

186 MPa

121 MPa

65 MPa (-35%)

This clearly shows that the addition of local reinforcing in highly-loaded areas can have an extremely significant effect on overall structural performance. By allowing the designer to quantify the effects of localized reinforcement, the MSC.Laminate Modeler will enable the development of more efficient structures.

Chapter Chapter 2: Tutoria Tutoriall 41 Structural Optimization

Benefits of MSC.Laminate Modeler 1. Rapid modify-ana modify-analyze-i lyze-interpr nterpret et cycle allows optimization. optimization.

42 MSC Laminate Modeler User’s Guide Glossary

Glossary (ISO 10303 equivalent terms in parentheses) layer (Ply)

An area on a surface having consistent material properties, fiber orientation and thickness. A layer is analogous to one or more pieces of fabric which are applied to a surface adjacent to each other and in a similar way.

layup sequence (Layup_ply_table)

An assembly table which provides an ordered list of layers.

layup (Ply_laminate)

A collection of one or more layers which mate with one another.

Chapter 3: Using Using MSC.Laminate MSC.Laminate Modeler Modeler MSC Laminate Modeler User’s Guide

3

Using MSC.Laminate Modeler



Procedure



Element Library



Initialization



Creating Materials



Creating Plies



Creating a Layup and an Analysis Model



Creating Solid Elements and an Analysis Model



Creating Laminate Materials



Creating Sorted Results

95



Creating Failure Results

98



Creating Design and Manufacturing Data



Importing Plies and Models



Importing and Exporting Laminate Materials



Setting Options



Session File Support



Public PCL Functions



Data Files

44 46

48

125

49

55

109 116 117

72

89

101

103 106

87

44 MSC Laminate Modeler User’s Guide Procedure

Procedure The MSC.Laminate Modeler is a specialized tool for the creation and visualization of a ply-based laminated composite model. An analysis model consisting of appropriate laminate materials and element properties can be generated automatically for a number of different analysis codes. Following analysis, specific composite results can be calculated to verify the performance of the model. The general process for generating a laminate composite model is as follows: 1. Create Homogeneous Homogeneous Materials Materials (Patran) (Patran) Materials are typically orthotropic, and the user should specify failure coefficients when defining materials. 2. Create Create Mesh (Patran (Patran)) The surface on which the composite layup is to be built is defined by the shell elements of the finite element mesh in the Patran database. The user should generate a mesh of sufficient resolution for both drape simulation and analysis purposes. It is a requirement that the meshing is completed before starting a session. Use the tools in the Finite Element application to verify the element normals and the free edges of the model before creating a new Layup file. 3. Create Ply Materials Materials (MSC.La (MSC.Laminate minate Modeler) Modeler) These materials are analogous to raw ply materials and include a reference to a homogeneous material for specifying mechanical properties, as well as manufacturing related information like thickness. 4. Create Plies (MSC.Laminate (MSC.Laminate Modeler) Modeler) Create plies in a manner which reflects the manufacturing process. 5. Create a LM_Layup LM_Layup and an Analysis Analysis Model (MSC.Lamin (MSC.Laminate ate Modeler) Modeler) A layup, or sequence of plies, is defined, allowing the creation of corresponding laminate materials and element properties required to define an analysis mode.. 6. Analyze Analyze (Patran (Patran and and analysis analysis code) code) The analysis is submitted in the usual way. The user may have to explicitly request layered composites results from the analysis code. 7. Create Results Results (MSC.Lamin (MSC.Laminate ate Modeler) Modeler) The user may sort results on the basis of physical plies or define new ones based on a failure analysis. These operations are summarized schematically overleaf.

Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 45 Procedure

Overview

Figure 3-1

Overview Overview of MSC.Laminate MSC.Laminate Modeler Process

46 MSC Laminate Modeler User’s Guide Element Library

Element Library Standard shell elements define the surfaces used in the MSC.Laminate Modeler module. The standard Patran geometry and mesh generation commands can be used to create a valid model. The elements in the Patran database are used to t o define the draping surface in addition to acting as analysis elements

Supported Element Topologies

Figure 3-2

Element Types

After the laminate descriptions have been generated they are applied to the Finite Element model in a controlled manner. The user is allowed to select the type of element for the currently selected analysis preference.

Supported Element Types 1. Property selection and generation has been significantly enhanced from previous versions. MSC.Laminate Modeler is no longer restricted to generati ng the data for MSC’s own preferences. Any suitably customized database will allow the generation of the required laminate materials and properties. 2. Selection Selection of the thermal composite composite elements elements is now possible possible because of the redesign. redesign. 3. SAMCEF is supported supported by writing writing an external external file for inclusion inclusion into the BACON BANQUE BANQUE file.

Supported Element Property Words The routine for creating properties extracts the data from the database and compares it against values that are consistently used for the type of data required by MSC.Laminate Modeler. The PROP_IDS that are recognized are:

Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 47 Element Library

PROP IDS

DESCRIPTION

DATA TYPE

ID_PROP_MATERIAL_NAME(13)

Laminated material name generated by MSC.Laminate Modeler.

MATERIAL_ID(5)

ID_PROP_ORIENTATION_ANG(20)

This will be set to 0.0. The Laminate materials are built to reflect the t he different relative angles.

REAL_SCALAR(1)

ID_PROP_ORIENTATION_SYS(21)

This prop_id is used to allow the creation of additional reference coordinate frames. Users are prompted whether or not they wish to create the frames.

COORD_ID(9)

ID_PROP_ORIENTATION_AXIS(1079)

The property call is made reflecting the occurrence of this prop_id.

INTEGER_SCALAR(3)

If the applicable data type for the prop_ids described is not available, then the MSC.Laminate Modeler cannot generate the required property cards.

48 MSC Laminate Modeler User’s Guide Initialization

Initialization The initialization form controls the opening of t he current MSC.Laminate Modeler database (Layup) file and the resultant display of the main Action Object Method control forms. To display the initialization form, select MSC.Laminate Modeler from the Tools menu.

Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 49 Creating Materials

Creating Materials When using MSC.Laminate Modeler there are three levels of material generation. 1. Patran homogeneous materials should be be generated using standard Patran functionality. These contain mechanical, thermal or physical data which can be manually input or imported Using the Patran Materials Enterprise. Patran Materials (p. 10) in the 1. MSC.Laminate MSC.Laminate Modeler Modeler ply materials. These ply materials materials have thickness and manufacturing manufacturing data in addition to a reference to an appropriate material in the Patran database. These ply materials are used to create plies in the MSC.Laminate Modeler module. 1. Patran laminate laminate materials materials which are built up from Patran homogeneou homogeneouss materials by the MSC.Laminate Modeler software on the basis of the user-specified layup sequence, offsets and tolerances.

Patran Homogeneous Material Definition The main description of the materials is done using the standard Patran methods of definition. The Materials form can be used to generate the required materials. Methods available include user input, external definition and Patran Materials.

MSC.Laminate Modeler Ply Material Definition The homogeneous materials created, within the standard Patran form, are referenced within the MSC.Laminate Modeler Create LM_Material Add form to generate ply materials with extended property sets which include thickness and manufacturing data, such as the maximum strain allowable during draping.

Material Application Types Ply materials are categorized by the way in which they are applied to a selected surface. They reference particular types of Patran homogeneous materials. • Painted

Isotropic materials are supported for Painting. • Projected

2D/3D orthotropic and anisotropic materials are supported for Projecting. • Scissor Draped

2D/3D orthotropic and anisotropic materials are supported for Scissor Draping. • Slide Draped

2D/3D orthotropic and anisotropic materials are supported for Slide Draping.

50 MSC Laminate Modeler User’s Guide Creating Materials

Additional Ply Material Parameters • Thickness • The thickness of a single ply of the material before it is sheared. • Maximum Strain

The allowable strain value before the material “locks” (i.e., the material can no longer conform to the surface by shearing). This is measured in degrees. • Initial Warp/Weft Angle

This value describes the original undeformed angle bet ween warp and weft yarns in a fabric. This value can be overridden on the Create LM_Ply Add, Additional Parameters form. This allows deformation of the fabric before it is placed on the model, which may achieve better draping. This angle is measured in degrees.

Paint

Project

Scissor

Slide

Thickness

Yes

Yes

Yes

Yes

Maximum Strain

No

No

Yes

Yes

Initial Warp/Weft Angle

No

No

Yes

No


Create LM_Material Add Form This form allows the user to generate MSC.Laminate Modeler ply materials which reference Patran homogenous materials and contain additional thickness and manufacturing data.


Modify LM_Material Form


Show LM_Material Form


Delete LM_Material Select Form

Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 55 Creating Plies

Creating Plies What is a Ply? A ply is an area of LM_Material which is stored and manipulated as a single entity. A ply represents a piece of reinforcing fabric which is cut from sheet stock and placed on a mould during the manufacturing process. A ply is fully characterized by the LM_Material it is made of, the area it covers, and the way in which it is applied to the surface. The latter is particularly important for non-developable surfaces where there are many different ways of placing the fabric on a surface.

Figure 3-3

LM_Ply Description Description

Why use Plies? Plies allow easy manipulation of complex data when you assemble and/or modify the layers to form the complete layup. The physical representation of a ply is a piece of fabric.

56 MSC Laminate Modeler User’s Guide Creating Plies

Create LM_Ply Add Form (Draping)

Note:

When a ply is created, a group of the same name and containing the Area Definition enti ties is created.


Input Data Definitions Start Point

This defines the starting point of the drape simulation process. It is analogous to the point at which a ply is first attached to a mould surface during manufacture. As the distortion usually increases away from the starting point, it is best to begin draping near the center of a region to minimize shear distortion. If the start point coordinates do not lie on the selected surface, the coordinates are projected onto the surface along the application direction vector. The start point must lie on the s elected area. Application Direction

The application direction defines the side of the surface area on which a ply is subsequently added when the final layup is defined. The “Top” of the surface covered by the ply is defined as the s ide on which the ply is originally applied when created. When defining a layup, the ply can be added to the “Top” “Top” or “Bottom” side of the mesh. It follows that the “Top” side is the same side as the application direction used to define the ply, whereas the “Bottom” side is the side opposit e the application direction.

The concept of side is very important as composite structures are often built using molds or forms, limiting the side of application to a single direction. The plies of reinforcing fabric can be added to either the outside of a male mould or the inside of a female mould. When defining plies and a l ayup, it is useful to consider the manufacturing process. The application direction is also used to project the start point and reference direction onto the surface. Reference Direction

The reference direction is used to specify the initial direction of the fabric. The input vector is projected onto the surface along the application direction to define the principal warp axis of the material at the


start point. Note that the direction of the material wi ll usually change away from the starting point if the surface is curved. Reference Angle

The principal warp axis of the material on the surface can be rotated from the reference direction by inputting a non-zero reference angle. This rotation is counterclockwise when viewed along the application direction.

Figure 3-4

Effect of Application Application Direction Direction on Warp Orientation Orientation

Note that the application direction is used to project the start point and reference direction vector onto the selected surface. This means that the same start point and reference direction vector results in different values when projected onto the surface along different application directions, as shown in Fig Figure ure 3-4. It follows that the start point and reference direction should be defined as close to the surface as practical, while the application direction should be defined as perpendicular to the surface as possible.


Figure 3-5

Projection Projection of Reference Reference Direction Direction

Example of Starting Definitions


This example shows the view as it would appear in the viewport in addition to the input that would appear on the Create LM_Ply Add form.

Axis Type The principal warp and weft axes are the paths the warp and weft fibers follow along the surface away from the start point. By defining the paths of the principal axes, it is possible to constrain the ply uniquely in the region bounded by the principal axes.

The principal axes can be defined in different ways: • None

No principal axes are defined, draping proceeds using the extension method only. • Geodesic

The principal axes are defined by geodesic lines from the start point.


• Planar

The principal axes are defined by the intersection of planes defined by the start point, application direction and reference direction rotated about the application direction through the reference angle. Extension Type

The extension type controls the draping process i f no axis type is defined, or the draping extends beyond the region uniquely defined by the principal axes. In this case, the material cells on each edge are kinematically unconstrained, and so some extension type must be specified to control the extension of the fabric.

The extension mechanism can be defined in different ways: • Geodesic

The fiber closest to the principal axis is identified and extended along the surface along a geodesic path. The adjacent fabric cells are then uniquely constrained. Note that the geodesic extension method yields an identical result to that produced using geodesic principal axes, followed by geodesic extension where necessary. • Energy

The mechanism defined by the free edge cells is rotated in such a way as to minimize the shear strain energy in that free edge, using the assumption that the shear load-deflection behavior is linear (this could be extended for nonlinear response). • Maximum

The mechanism defined by the free edge cells is rotated in such a way as to minimize the maximum shear strain in that free edge.


Additional Controls Form - Geometry


Additional Controls Form - Material


Additional Controls Form - Boundaries


Figure Figure 3-6

Note:

Split Example Example

Avoid starting to drape near split definitions to prevent ambiguous draping results.


Additional Controls Form - Order of Draping


Note:

This capability is particularly useful when draping over a series of conical sections. First drape the most critical section, ensuring minimal shear. Thereafter, drape peripheral areas.


Create LM_Ply Add Form (Projection)


Modify LM_Ply Form


Show LM_Ply Graphics Form


Delete LM_Ply Select Form

Note:

When an LM_Ply is deleted, the group of the same name created at LM_Ply creation time will also be deleted.

72 MSC Laminate Modeler User’s Guide Creating a Layup and an Analysis Model

Creating a Layup and an Analysis Model The individual LM_Plies are used to define the model LM_Layup using the Create LM_Layup Add form. When this form is selected, a spreadsheet for the Layup definition and forms for the relevant tolerances can be accessed. The forms are described on the following pages. These forms are used to create and maintain the analysis layup. As well as providing tools to modify and redefine the layup, the forms will generate the correct laminate materials and apply the correct c orrect properties to the model. If all other operations are complete (i.e., Loads/BC addition), the model is ready for analysis after these forms have been applied.

Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 73 Creating a Layup and an Analysis Model

Create LM_Layup Add Form


Layup Definition Form

The spreadsheet is used to specify which of the previously defined LM_Plies are used in the generation of the model LM_Layup. The form allows the selection and ordering of the required LM_Plies. Manipulation of the LM_Plies within the spreadsheet is used to create different stacking sequences and layups. Select the specific LM_Ply from the definitions in the Existing LM_Plies frame The method of application of that LM_Ply to the existing layup is controlled by the LM_Layup Controls. Continue by Adding, Inserting, and Deleting LM_Plies until the LM_Layup is finished. LM_Plies can be added to the layup at any time to reinforce the model between analyses. The ability to redefine laminates rapidly is one of the key features of the MSC.Laminate Modeler. The spreadsheet works in two distinct but connected modes. They are called “Expanded” and “Compressed.” In expanded mode, the multiplier column on the spreadsheet is always set equal to 1. This enables you to work at the level of single LM_Plies and the Delete D elete and Replace commands will only act on the single LM_Ply selected. In compressed mode, the Delete and Replace commands can be used to


do multiple “single actions” at the same time. For example, if a row is specified as having a multiplier of 10, then a replace instruction will replace all 10 rows with the new LM_Ply. The same is true for delete. You can switch between the two methods at any time and take advantage of the quicker set up time of the stack building, while still being able to modify the LM_Ply sequence at t he single LM_Ply level if required. Make current definition a total definition.

Make the current definition symmetrical by copying LM_Plies.

Make the current definition symmetrical about the bottom LM_Ply.

Split the current definition in half.

Split the current definition in half as if the current definition is symmetrical about a mid-LM_Ply. mid-LM_Ply.

Cut data from selected spreadsheet cells.

Copy data from selected spreadsheet cells

Paste data cut or copied from selected spreadsheet cells


Paste mirrored data cut or copied from selected select ed spreadsheet cells

Undo the last command for the LM_Layup definition spreadsheet.

Figure 3-7

Icons on LM_Layup Create Spreadsheet Spreadsheet


Offset Definition Form

Important:

Ignore Offsets is required for analysis preferences like ABAQUS and Patran Advanced FEA which do not allow any offset definition for composite shells. This is not the same as having an offset = 0.0. An offset with a specified value will cause an error as it is interpreted as a set value.


Select Element Type Form


Tolerance Definition Form


Modify LM_Layup Add Form

As only a single layup is allowed in a single Layup file, the form for layup modification is identical to that for layup creation.


Show LM_Layup Exploded View Form

This capability allows the user us er to verify the definition and application direction of the plies defined in a layup.


Show LM_Layup Cross Section Form

This capability allows the user to define cross-section plots of the plies defined in a layup.


Show LM_Layup Element Form

This capability allows the user to verify the resulting layup on individual elements. Visualization capabilities are similar to t o those provided by the Show Laminate function.


Show LM_Layup Element Info Form


Transform LM_Layup Mirror Form

This capability allows the user to model a repeated unit of a symmetrical model, and mirror as appropriate to generate the full model. For example, only one half of a composite chassis may m ay be modeled prior to mirroring the mesh and layup about the center plane.


Delete LM_Layup Select Form

This form allows the user to delete the single layup defined in the current Layup file.

Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 87 Creating Solid Elements and an Analysis Model

Creating Solid Elements and an Analysis Model The MSC.Laminate Modeler defines a ply layup on a 2D shell mesh. The majority of analyses can be conducted using shell elements as through-thickness effects are relatively insignificant. H owever, if the laminate is thick, and especially if the surface is curved, it may be necessary to use solid elements to model structural behavior adequately. For these situations, the MSC.Laminate Modeler includes the capability to extrude shell elements through a distance equal to the laminate thickness. Furthermore, laminate materials and element properties can be created automatically to allow accurate analysis. If the analysis code does not support laminated solid elements, the laminate materials are converted to equivalent anisotropic materials for subsequent analysis.

88 MSC Laminate Modeler User’s Guide Creating Solid Elements and an Analysis Model

Create Solid Elements LM_Layup Form

This capability allows the user to generate solid elements and the associated materials and element properties needed for detailed analysis of thick laminates.

Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 89 Creating Laminate Materials

Creating Laminate Materials The MSC.Laminate Modeler generates laminate materials and element properties when creating or modifying a layup, or when creating solid elements. Addit ional capabilities are provided for advanced users who need greater control over the creation of the analysis model. For example, when using MSC.Nastran, the user can align the laminate materials using several different methods such as using coordinate systems or specified vectors. The procedure followed for generating an analysis model is as follows. The MSC.Laminate Modeler stores warp angle, weft angle and thickness thi ckness data for every element making up a ply. ply. When a layup is created, the total material definition on every element can be defined. By default, angle data is specified with respect to the first edge of every element. The next step is to transform this angle data to the angle definition system required by the selected element type. For example, the projection of a vector onto each element may be used as the basis for defining laminate material orientations. This allows the program to calculate a corresponding laminate material on each element. However, it is generally unwieldy to define a laminate material per element for large models which may contain over a hundred thousand elements. Hence, a sorting mechanism is invoked to identify a minimum number of materials within the user-defined tolerance. The analysis model can become complicated due to the continuous variation of fiber direction over curved surfaces. Verification Verification tools allow the user to t o show the layer thickness and orientations orientat ions on any element in the model. This capability capabilit y can be used even if conventional techniques have been used to define the composites model, or legacy analysis files have been imported into Patran.

90 MSC Laminate Modeler User’s Guide Creating Laminate Materials

Create Laminate LM_Layup Form


Laminate Options Form

Preview Form


Show Laminate Form


Delete Laminate Select Form


Delete Property Set Select Form

Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 95 Creating Sorted Results

Creating Sorted Results Most analysis codes which generate results for laminated composite materials define the layer results as the stacking sequence number with respect to the element orientation system. If there are ply drop-offs or elements are reversed, the stacking sequence number bears no direct relationship to the physical plies. To overcome this problem, two results sorting procedures are supported. If the analysis model has been generated using laminate modeler, the results can be sorted quite simply using data stored in the Layup file. Otherwise, results can be sorted so rted on the basis of underlying material IDs, if t he ID is only used once on every element over a selected area.

96 MSC Laminate Modeler User’s Guide Creating Sorted Results

Create LM_Results LM_Ply Sort Form

Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 97 Creating Sorted Results

Create LM_Results Material ID Sort Form

98 MSC Laminate Modeler User’s Guide Creating Failure Results

Creating Failure Results Failure indices according to various criteria can be calculated from layered results. Note that these are based on calculated results and do not affect the analysis model itself. Therefore, they rely on the assumption of linearity and are only valid for first ply failure.

Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 99 Creating Failure Results

Create LM_Results Failure Calc Form

100 100 MSC Laminate Modeler User’s Guide Creating Failure Results

Material Allowables Form

101 Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 101 Creating Design and Manufacturing Data

Creating Design and Manufacturing Data It is important to integrate the design, analysis and manufacture of laminated composites. In particular, it is important that the model analyzed is equivalent to the manufactured part. Therefore, a ply book containing design and manufacturing data can be produced at any time.

102 102 MSC Laminate Modeler User’s Guide Creating Design and Manufacturing Data

Create Ply Book Layup Form

103 Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 103 Importing Plies and Models

Importing Plies and Models Usually, a new Layup file is created once a mesh has been fi nalized in the Patran database. If the user subsequently changes the mesh, the elements in the database and those in the t he Layup file no longer correspond. This can lead to errors because the elements selected in the viewport may not have the same IDs as those used for internal operations. For this reason, a warning is issued if the database mesh does not correspond to the Layup file mesh when opening a new Layup file. In addition, it may be desirable to import plies from another Layup file, which may have a different element definition. For example, a draping simulation tool embedded in a CAD package could generate a Layup file which has no knowledge of the analysis mesh. The Import Ply capability has been developed to allow users to remesh as required and also import of data from other draping systems. In order to do this, it is necessary to generate a mapping between the current mesh and the imported mesh. This mapping is calculated by element matching or piercing. The MSC.Laminate Modeler first tires to find a direct match between c urrent and imported elements by identifying elements with the same nodal coordinates. Where such a mat ch is identified, the layup on the imported element can be transferred directly to the current element as necessary. The matching process is relatively fast. Where a current element has no direct match, mapping is determined through piercing. Here, a normal vector is calculated at the centroid of each current element and any intersections with imported elements are calculated. If there are multiple intersections, that closest to the centroid is chosen. The distance between the centroid and intersection point is calculated, as is t he angle between the current normal and the normal of the intersected imported element. If both the calculated distance and angle are less than the distance and angular tolerances respectively, the layup on the intersected element is mapped onto the current element. This piercing process is relatively slow due to the multiple calculations required. In addition to ply import, it is also possible to import a complete composites model definition stored in a Layup file. This will copy the mesh and materials from the Layup file into a Patran database so that further operations like ply creation can be conducted as normal. This feature means that composite models can be transferred and stored by means of the Layup file alone.

104 104 MSC Laminate Modeler User’s Guide Importing Plies and Models

Import Plies File Form

105 Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 105 Importing Plies and Models

Import Model File Form

106 106 MSC Laminate Modeler User’s Guide Importing and Exporting Laminate Materials

Importing and Exporting Laminate Materials The MSC.Laminate Modeler generates laminate materials based on a ply layup. However, under certain circumstances, it is desirable to export or import laminate materials to or from specialized tools used for laminate analysis. The MSC.Laminate Modeler includes and interface to the LAP laminate analysis program developed by Anaglyph Ltd. (www.anaglyph.co.uk). During preliminary design, the user can define a baseline laminate material within LAP and save t his data in a text file. This information can be imported into Patran and referenced by element properties in the normal way. This basic laminate can be optimized for loading and manufacturing criteria using the tools within the MSC.Laminate MS C.Laminate Modeler. Following analysis, the user can export laminate material and load information to LAP in order to examine and report stresses.

107 Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 107 Importing and Exporting Laminate Materials

Import Laminate LAP Form

108 108 MSC Laminate Modeler User’s Guide Importing and Exporting Laminate Materials

Export Laminate LAP Form

109 Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 109 Setting Options

Setting Options Options for the display of graphical information in a viewport, and the export of manufacturing data, must be set before creating plies and layups.

110 110 MSC Laminate Modeler User’s Guide Setting Options

Set Export Options Form


Flat Pattern Example

Figure 3-8

Example Flat Pattern

The 2D flat pattern shape can be generated in different formats. The DXF format is typically used to drive nesting and cutting machines. Note that the flat pattern shape does not indicate the edges of the fabric where the maximum strain value has been exceeded.


Set Display Options Form


Additional Forms Controlling Ply and Layup Graphics


Flat Pattern Display on Screen

Figure 3-9

Flat Pattern Displayed Displayed on Screen

The flat pattern shape is displayed on the screen perpendicular to the application direction arrow. arrow. The variation that occurred between the draped fabric on the model and the undeformed fabric shape can be seen.


Figure 3-10

Flat Pattern Displayed Displayed for Surface with Split Definition

116 116 MSC Laminate Modeler User’s Guide Session File Support

Session File Support MSC.Laminate Modeler can be run from a session sessi on file if required. The session file should contain calls to the public PCL functions defined in the next section. These functions correspond to user interface forms in the usual way. If required, the contents of a session file can be modified manually before being replayed to change the layup. Replaying a session file also allows the user to remesh surfaces if area selection s election is done by reference to geometrical entities, such as . However, care must be taken with the sel ection of the start point and the reference direction to make sure that they correspond to the remeshed model. Note that running a session file will be slightly different from undertaking an interactive run because the forms will not appear or be filled with the corresponding data.

Important:

Session File edits.

It is also advisable to change the full path names for the files to just the file names. For example: “/usr/people/demo/test/testrun. Layup” becomes “testrun.Layup”.

117 Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 117 Public PCL Functions

Public PCL Functions These functions correspond to user interface forms in the usual way. They can be used by running a session file, or calling tthem hem directly from other PCL functions. In either case, it i s important that the PCL library is available to the session, and the executable is in the path

p3cm.new

( )

Input:

STRING

Name of the new Layup file.

Status return value. The value will be 0 if the routine is successful.

Output:

INTEGER

Begins a MSC.Laminate Modeler session using a new Layup file with the name .

p3cm.open

( )

Input:

STRING

Name of the existing Layup file.


Output:

INTEGER

Begins a MSC.Laminate Modeler session by opening an existing Layup file with the name .

p3cm.save_as

( )

Input:

STRING

Name of the target Layup file.


Output:

INTEGER

Saves a copy of the current Layup file with the name .

118 118 MSC Laminate Modeler User’s Guide Public PCL Functions

p3cm.create_material_add

( , , , , , , , )

Input:

STRING

Application type.

STRING

Material name.

STRING

Analysis ma material na name.

REAL

Initial thickness of the ply material.

REAL

Maximum permissible strain of the ply material.

REAL

Initial angle between warp and weft fibres.


Output:

INTEGER

Creates a new material


p3cm.create_ply_add

( , , , , , , , , , , , , , , , )

Input:

STRING

Application type.

STRING

Ply material name.

STRING

Ply name.

REAL ARRAY

Coordinates of starting point.

REAL ARRAY

Vector defining application direction.

REAL ARRAY

Vector defining the reference direction.

REAL

Reference angle.

REAL

Initial angle between warp and weft fibres.

REAL

Maximum permissible strain of the ply material.

REAL

Step length.

INTEGER

Axis type.

INTEGER

Maximum number of sweeps.

REAL ARRAY

Maximum fabric bounds.

STRING

Selected area.

STRING

Split definition.


Output:

INTEGER

Creates a new ply.


p3cm.create_layup_add

(, , , , , , < num_offs>, , < off_flags>, < off_starts>, , < off_areas>, < num_tols>, , , , , < element_type>, , )

Input:

INTEGER

Number of plies.

STRING ARRAY

Ply names.

STRING ARRAY

Application types.

INTEGER ARRAY

Instances.

STRING ARRAY

Side of application.

REAL ARRAY

Angular offset values.

INTEGER

Number of offset regions defined.

REAL ARRAY

Value of offset.

STRING ARRAY

Side of offset.

REAL ARRAY

Coordinates of starting points for offset definition.

REAL ARRAY

Vectors defining view direction for offsets.

STRING ARRAY

Selected areas for offset definition.

INTEGER

Number of tolerance regions defined.

REAL ARRAY

Angular tolerance values (degrees).

REAL ARRAY

Thickness tolerance values(degrees).

STRING ARRAY

Selected areas for tolerance definition.

LOGICAL

Generate analysis model.

STRING

Selected element type.

LOGICAL

Generate solid element file.

LOGICAL

Generate BACON command file.


Output:

INTEGER

Creates a new layup.


p3cm.delete_material_name

(, )

Input:

STRING

Application type.

STRING

Material name.


Output:

INTEGER

Deletes an unused material.

p3cm.delete_ply_name

(, < ply_name> )

Input:

STRING

Application type.

STRING

Ply name.


Output:

INTEGER

Deletes an unused ply.

p3cm.create_results_sort

( )

Input:

STRING ARRAY

A string array containing the loadcase name, subcase name, primary label, secondary label and dummy layer name of result to be sorted.


Output:

INTEGER

Creates sorted results.


p3cm.create_results_failure

(,,,, ,,, ,,,, ,,,,, )

Input:

STRING AR ARRAY

A st string ar array co containing th the lo loadcase na name, su subcase name, primary label, secondary label and dummy layer name of result to be sorted.

STRING

A list of elements for which results are to be calculated.

STRING

The name of the criterion to be used.

STRING

The basis to be used: "STRESS" or "STRAIN".

INTEGER

The number of material allowables.

STRING ARRAY

A array of material names.

REAL ARRAY

A x<8> array of material allowables.

STRING

Result name.

LOGICAL

Flag to sort ply results by LM_Ply. (Not yet implemented.)

LOGICAL

Flag to generate failure index, reserve factor, margin of safety and critical component results for every ply in the Patran database. (Not yet implemented.)

LOGICAL

Flag to generate failure index results in the Patran database. (Not yet implemented.)

LOGICAL

Flag to generate fa failure in index results in in the Pa Patran database. (Not yet implemented.)

LOGICAL

Flag to generate margin of safety results in the Patran database.

LOGIC GICAL

Fla Flag to to gen geneerate ma margin of of sa safety re resul sults in in th the Pa Patra tran database.

LOGICAL

Flag to generate critical ply results in the Patran database.


Output:

INTEGER

Creates composite failure index results. These are stored in a text file and optional results in the Patran database.


p3cm.set_graphics_options

(, , , , , , , , , , , , )

Input:

LOGICAL

Display the message file.

LOGICAL

Display the ply graphics control form.

LOGICAL

Display the layup graphics control fo form.

LOGICAL

Display the view direction arrow of a ply.

LOGICAL

Display the reference direction arrow of a ply.

LOGICAL

Display the maximum strain value of a ply.

LOGICAL

Display the border of the selected area of a ply.

LOGICAL

Display the 2D flat pattern of a ply.

LOGICAL

Display the 3D draped pattern of a ply.

LOGICAL

Display the angles of the surface plies of a layup.

LOGICAL

Display the angles of a ply.

REAL

Offset value of the 2D flat pattern of a ply.

REAL

Scale value of the angles of the surface plies of a layup.

Status return value. The va value lue wi will be 0 if the routin tine is successful.

Output:

INTEGER

Sets graphics options.


p3cm.set_export_options

(, , , , , )

Input:

LOGICAL

Export the 3D draped pattern.

LOGICAL

Export the 2D flat pattern.

LOGICAL

Export mould surface.

LOGICAL

Export files in IGES format.

LOGICAL

Export files in DXF format.

LOGICAL

Export files in postscript format.


Output:

INTEGER

Sets export options.

p3cm.delete_properties_all

()

Input:

None. Output:

INTEGER


Deletes properties named generated by the MSC.Laminate Modeler.

p3cm.delete_laminates_all

()

Input:

None. Output:

INTEGER GER

Status re return va value. Th The va value wi will be 0 if th the ro routin tine is is successful.

Deletes laminates named generated by the MSC.Laminate Modeler.

125 Chapter Chapter 3: Using MSC.Lami MSC.Laminate nate Modeler Modeler 125 Data Files

Data Files MSC.Laminate Modeler uses a variety of files to store and communicate the extensive data required for composites analysis. The file name prefix is set when entering the MSC.Laminate Modeler. The default prefix is the name of the database. For data files, additional suffices s uffices <.bak>, <.igs>, <.dxf> and <.ps> denote backup, IGES, DXF or postscript post script files respectively. 1. .Layup This is the external MSC.Laminate Modeler database.

Important:

Do not delete or modify this file manually. manually.

2. .lm_msg This message file is produced by the “layup” executable and provides a record of the ply application and manipulation processes. Any errors will always be reported in this file. This file can be displayed automatically after every user command by setting a toggle on the Set Display Options form. 3. .lm_mould This file contains mould surface data. 4. .lm_solid This file contains data describing solid elements created by extruding the shell elements through the thickness of the plies. 5. .lm_bacon This file contains BACON (SAMCEF preprocessor) commands to build the analysis model. 6. .lm_report This file contains a text summary of the layup. 7. .lm_results This file contains the results of a laminate failure analysis.

126 126 MSC Laminate Modeler User’s Guide Data Files

Chapter 4: Example:Laminated Example:Laminated Plate MSC Laminate Modeler User’s Guide

4

Example:Laminated Plate



Overview



Model Description



Modeling Procedure



Step-By-Step

128

132

129 130

128 128 MSC Laminate Modeler User’s Guide Overview

Overview This example will show the t he use of MSC.Laminate Modeler by building and modifying a si mple layup on a flat plate. The Functionality shown is extendable to general shapes.

129 Chapter Chapter 4: Example:Lam Example:Laminated inated Plate Plate 129 Model Description

Model Description • L=Length = 10 units • H=Height = 6 Units

130 130 MSC Laminate Modeler User’s Guide Modeling Procedure

Modeling Procedure Step 1: Open a new database and set parameters

Step 2: Create a new empty group

131 Chapter Chapter 4: Example:Lam Example:Laminated inated Plate Plate 131 Modeling Procedure

Step 3: Construct the Patch

Step 4: Mesh the Patch

Use the Create action.

132 132 MSC Laminate Modeler User’s Guide Step-By-Step

Step-By-Step

133 Chapter Chapter 4: Example:Lam Example:Laminated inated Plate Plate 133 Step-By-Step






Chapter 5: Theor Chapter Theory y MSC Laminate Modeler User’s Guide

5

Theory



The Geometry of Surfaces



The Fabric Draping Process



Results for Global Plies



Composite Failure Criteria

140 142

151 155

140 140 MSC Laminate Modeler User’s Guide The Geometry of Surfaces

The Geometry of Surfaces Introduction Composite materials are typically made from sheets of materials whose thickness is very much smaller than their width. Therefore, an elementary understanding of surface geometry is essential in order to use these materials effectively. effectively. For the purposes of engineering analyses, surfaces are generally divided into flat plates or curved shells. Compared with plate structures, shells generally g enerally exhibit superior strength and stiffness as a consequence of their curvature. Shells have traditionally been difficult to manufacture from conventional materials like aluminum, but are now readily built from plies of reinforcing fabrics which conform or drape relatively easily to surfaces of complex co mplex curvature. The potential for optimizing surface geometry leads to weight savings beyond those promised by the increase in mechanical performance alone. The drapability of reinforcing materials results directl y from their ability to shear, allowing the material to cling to surfaces without folding or tearing. It is important to understand the cause of material shear as this both changes the form of the material, and hence its mechanical properties, but also varies the alignment of the fibres with respect to the loads in the surface. The latter factor is especially vital in unidirectionally-reinforced materials where the strength and stiffness along the fibres may be more than ten times greater than in the transverse direction.

Effect of Gaussian Curvature The amount of shear distortion in a sheet of material is dependent on the degree of curvature of the surface and the size of the sheet. The curvature of the surface is conveniently measured by a scalar quantity called the “Gaussian curvature” which is the product of the curvature of the surface in two orthogonal principal directions. For example, the dome has posit ive Gaussian curvature because the sense of the curvature in two directions at 90 degrees is the same. Gaussian curvature can be visualized easily by drawing geodesic lines on surfaces. (Geodesic lines are those that are straight in the plane of the t he surface, such as the meridian of a sphere.) A pair of lines which are parallel at some point will wi ll tend to converge, remain parallel or diverge on surfaces of positive, zero and negative curvature respectively. In contrast, the cylinder has zero Gaussian Curvature as there is no curvature along its axis. All “developable” surfaces (i.e., those that can be rolled up from a flat sheet without the material shearing in its plane) necessarily have zero Gaussian Curvature over their entire area. Finally, a saddle which has curvature in two different directions, has a negative Gaus sian curvature.

141 Chapter Chapter 5: Theor Theory y 141 The Geometry of Surfaces

Figure 5-1

Selected Shapes with Different Gaussian Curvature Curvature

142 142 MSC Laminate Modeler User’s Guide The Fabric Draping Process

The Fabric Draping Process Note:

Material Models for Draping.

The fabric draping process can be split into two sections: 1. A Local Local drapin draping g mechani mechanism sm 2. A Global Global drapin draping g procedu procedure re

Local Draping Local draping is concerned with fitting a small section of material to a generally curved surface. If the surface has nonzero Gaussian curvature, the material element must shear in its plane to conform to the surface. This deformation is highly dependent on the microstructure of the material. As a result, local shearing behavior can be regarded as a ply material property.

Figure 5-2

Scissor Scissor Draping Mechanism Mechanism

Figure 5-3

Slide Draping Mechanism Mechanism

MSC.Laminate Modeler currently supports two local draping algorithms: scissor and slide draping. For scissor draping, an element of material which is originally square shears in a trellis-like mode about its vertices to form a rhombus. In particular, the sides of the material element remain of constant length. This type of deformation behavior is characteristic of woven fabrics which are widely used to manufacture highly-curved composite components.

143 Chapter Chapter 5: Theor Theory y 143 The Fabric Draping Process

For slide draping, two opposite sides of a square material element can slide parallel to each other while their separation remains constant. This is intended to model the application of parallel strips of material to a surface. It can also model, very simply, the relative sliding of adjacent tows making up a strip of unidirectional material. When draping a given surface using the two different local draping algorithms, the shear in the plies builds up far more rapidly for the slide draping mechanism than for the scissor draping mechanism. This observation is compatible with actual manufacturing experience that woven fabrics are more suitable for draping curved surfaces than unidirectional pre-pregs. For small deformations, the predictions of the different algorithms are practically identical. Therefore, it is suggested that the scissor draping algorithm be used in the first instance.

Global Draping Global draping is concerned with placing a real sheet of material onto a surface of general curvature. This is not a trivial task as there are infinite ways of doing this if the surface has nonzero Gaussian curvature at any point. Therefore, it is important to define procedures for the global draping simulation which are reproducible and reflect what can be manufactured in a production situat ion. As a result, global draping behavior can be regarded as a manufacturing, rather than t han material, property. MSC.Laminate Modeler currently supports three different global draping algorithms: Geodesic, Planar and Energy. For the Geodesic global draping option, principal axes are drawn away from the starting point along geodesic paths on the surface (i.e., the lines are always straight with respect to the surface). Once these principal axes are defined, there is then a unique solution for draping the remai nder of the surface. This may be considered the most “natural” method and appropriate for conventional laminating methods. However, for highly-curved surfaces, the paths of geodesic lines are highly dependent on initial conditions and so the drape simulation must be handled with care.


Figure 5-4

Geodesic Global Draping

For the Planar global draping option, the principal axes may be defined by the intersect ion of warp (and weft for scissor draping) planes which pass through the viewing direction. This method is appropriate where the body has some symmetry, or where the layup is defined on a space-centered rather than a surface-centered basis.


Figure 5-5

Planar Global Draping

Finally, the Energy global draping option is provided for draping highly-curved surfaces where the manufacturing tolerances are necessarily greater. Here, the draping proceeds outwards from the start point, while the direction of draping is controlled by minimizing the shear strain energy along each edge.

Figure 5-6

Energy Global Draping


Note:

Step Length.

Note that all draping simulations are discrete and use a specific step length. A default value is calculated on the basis of the area of the selected region. This may be modified or overridden, using the step length databox on the Additional Controls/Geometry form.

Note:

Fabric Graphics.

The sections above relate only to how the fabric algorithm works inte rnally. rnally. When the graphics are drawn to the screen, they are drawn in the same manner for all of the selected sel ected types, if applicable. The fabric drawing to the screen has no relevance to the method that the fabric generation routine executed. In particular, do not expect to see the fabric being drawn in a manner similar to the calculation method for the Energy Option.

Projected Angles MSC.Laminate Modeler supports two different methods of projecting fiber angles onto a surface. In the first Planar method, the angles are defined by the intersection of parallel planes with the surface. Using the Axis method, axes are projected onto the elements and rotated as specified. The appropriate method will depend on the manufacturing process followed.

Figure Figure 5-7

Plane Plane X-Axis X-Axis


Using the “Plane X-axis” option, a plane passing through the Z-axis and rotated through an angle α from the X-axis. The elemental material angle is the angle between the intersection intersect ion of this plane, or one parallel to it, with the element and the first edge of the element. “Plane Y-axis” uses plane through X-axis measured from Y-axis. “Plane Z-axis” uses plane through Y-axis Y-axis measured from Z-axis.

Figure 5-8

Projected X-axis

Using the “Project X-axis” option, the global X-axis is projected normally onto the element at the first node. This axis is then rotated through the reference angle α in the counter (anti-) clockwise direction from the viewing point. It is important to note that the element mate rial angle θ is generally not equal the angle α. “Project

Y-axis” uses

“ Project Z-axis ”

the Y-axis

uses the Z-axis

MSC.Laminate Modeler also allows the user to define angles with respect to the element datum (i.e., the first edge of the element). This feature feat ure can also be used to visualize the relative orientation of elements where this is not immediately obvious, such as if the pave mesher is utilized.

Practical Restrictions On Surfaces The draping simulation has been found to give realis tic results for surfaces which are manufacturable using sheet materials. This is even true for surfaces having infinite curvature in a single direction (i.e.,


sharp edges). However, the simulation is likely to fail where it is physically i mpossible to drape a real sheet of material. Geometrical features leading to poor draping include: 1. Excessive Gaussian Curvature. For example, the apex of a cone has extreme Gaussian curvature, and is therefore impossible to drape realistically. The user should use the Split Definition facility to cut the cone between its base and apex before simulating the drape.

2. Holes in Surfaces. It is recommended that holes be temporarily filled with dummy elements while a layup is being defined. If these elements are put in a separate sepa rate Patran group, they can be excluded from the analysis by only analyzing the current group.

3. Incomplete Boundary Definition. Many surfaces, such as cylinders, do not have a complete boundary; draping will continue around the body until an internal program storage limit is reached. Define artificial boundaries using the split definition facility on the Create LM_Ply, Additional Controls, Definition form.


4. “T” Sections. These can be draped along three separate paths. The user must make sure that the correct elements are selected, and that a consistent definition of top and bottom surfaces is maintained. This prevent plies crossing over unexpectedly.


151 Chapter Chapter 5: Theor Theory y 151 Results for Global Plies

Results for Global Plies MSC.Laminate Modeler results can be rearranged to produce output for a single continuous piece of fabric rather than a local element-based ply-by-ply representation of the results. This feature is essential for proper results interpretation because a single piece of fabric may be represented by different ply numbers on different elements. The common approach to results processing is to produce results by ply number over a range of elements. This can lead to completely misleading results for typical components.The results rearrangement creates a new set of results in the database which uses the exact definition of a fabric on an element/ply-number scheme, allowing meaningful postprocessing as illustrated below.

152 152 MSC Laminate Modeler User’s Guide Results for Global Plies

Example

Note:

Results shown above are centroidal. Spectrum was updated for each picture so contours were assigned per plot.

153 Chapter Chapter 5: Theor Theory y 153 Results for Global Plies

As can be seen, the analysis references to plies can be in error. This rearrangement of results does not give “better” or “more accurate results” but provides a more realistic grouping of results. The functionality can be used to rearrange any results stored and referenced by plies in the database. For example, you could create failure criteria results using P/LAM or an in-house program, read the results into Patran, and then sort these results on the basis of global plies. The initial release of this functionality extracts and creates results at element centroids. Some more simple examples can be used to help visualize the difference.

Note:

All model dimensions are greatly exaggerated.

154 154 MSC Laminate Modeler User’s Guide Results for Global Plies

Results at Multiple Sections Through a Ply This initial version of the results manipulation always tries to operate on a single result per layer. MSC.Laminate Modeler determines how many results t here are per ply by a simple formula: the number of layer results from database divided by the maximum number of plies on any element. If the value of this = 1 then MSC.Laminate Modeler uses that single value to create the new results. If the value is > 1 then a further calculation is done to extract what should be a reasonable value. For example:

155 Chapter Chapter 5: Theor Theory y 155 Composite Failure Criteria

Composite Failure Criteria Failure criteria for composite materials are significantly more complex than yield criteria for metals because composite materials can be strongly anisotropic and tend to fail in a number of different modes depending on their loading state and the mechanical properties of the material. While theories which reflect detailed mechanisms of failure are currently being developed, empirical cri teria based on test data have been used for decades. These criteria have been incorporated in the MSC.Laminate Modeler to allow rapid evaluation of the strength of a structure according to the current industry standards. The user can also define custom criteria using PCL functions for use in specialized applications.

Nomenclature Failure criteria compare the loading state at a point (stress or strain) with a set of values reflecting the strength of the material at that point (often referred to as the material allowables). Both loading and strength values should be reflected in the same material coordinate system. For unidirectional materials, this is typically in the direction of the fibres. However, for woven and knitted fabrics , this direction is not obvious, and might change as the material is formed to shape. In general, the load is represented by a full stress or strain tensor having six independent components. By convention, for lamina materials the material X axis lies in the direction of o f the warp fibres while the Z axis lies in the through-thickness direction of the sheet. Note than in Patran, shear strains are stored in tensor rather than engineering notation, and any experimental failure strengths should reflect this. STRESS

σx,σy,σz,τxy,τyz,τxz

STRAIN

εx,εy,εz, γ γxy, γ γyz, γ γxz

The strength of a composite can be expressed by an arbitrarily la rge number of values, depending on the complexity of the failure criterion. However, lamina materials, used in composites, are often assumed to be orthotropic; the through-thickness stresses or strains are ignored and it is assumed that there is negligible interaction between the different failure modes. The strength of the material can therefore be represented by seven independent variables: TX

tensile strength along the X axis

0 < TX

CX

compressive strength along the X axis

0 < CX

TY

tensile strength along the Y axis

0 < TY

CY

compressive strength along the Y axis

0 < CY

SXY

shear strength in the XY plane

0 < SXY

SYZ

shear strength in the YZ plane

0 < SY Z

SXZ

shear strength in the XZ plane

0 < SX Z

In the Tsai-Wu Tsai-Wu criterion, these values have been supplemented by an interaction term which reflects the interdependence of failure modes due to loading along both the X and Y material directions.

156 156 MSC Laminate Modeler User’s Guide Composite Failure Criteria

IXY

interaction between X and Y directions

-1< IXY <1

Note that the above values can be applied to either stress or strain. The form of the failure criterion is typically described as a mathematical function of the above variables which reaches the value of unity at failure as follows. Failure Index = FI (load, strength) = 1 The strength of a structure can be given as a Strength Ratio (SR), which is the ratio rat io by which the load must be factored to just fail. (Note that the Strength Ratio is not necessarily the reciprocal of the Failure Index.) Alternatively, the Margin of Safety (MoS), where MoS = SR - 1, is used.

Maximum Criterion This criterion is calculated by comparing the allowable load with the actual strength for each component. Mathematically, it is defined by: FI = max (σx /TX, - σx /CX, σy /TY, -σy /CY, abs(τxy)/SXY, abs( γyz)/SYZ, abs( γxz)/SXZ) In this case, SR = 1/FI

Hill Criterion The Hill criterion was one of the first attempts to develop a single formula to account for the widely different strengths in the various principal directions: FI = FXX σx2 + FYY σy2 + 2 FXY σx σy + FSS τxy2 where FXX =

FYY =

FXY =

FSS = Because this failure theory is quadratic: SR = 1 / sqrt (FI)

1/(TX TX)

if σx >= 0

1/(CX CX)

if σx <0

1/(TY TY)

if σy >= 0

1/(CY CY)

if σy <0

-1/(2 TX TX)

if σx σy >= 0

-1/(2 CX CX)

if σx σy <0

1 / (SXY SXY)


In the Laminate Modeler, the Tsai-Wu Tsai-Wu criterion for in-plane loads (representing fiber failure) has been supplemented by a maximum load theory for out-of-plane shear loads (representing matrix failure): FI = max( abs( γyz)/SYZ, abs( γxz)/SXZ) In this case, SR = 1/FI For every ply, the lower of the Margins of Safety for fibre and matrix failure is calculated calcul ated and displayed.

Tsai-Wu Criterion The Tsai-Wu failure criterion is an unashamed, empirical criterion based on the sum of the linear and quadratic invariants as follows: Fi σi + Fij σi σ j = 1

i,j = 1...6

where Fi and Fij are dependent on the material strengths. For the restrictions of lamina materials, this equation reduces to: FI = FX σx + FY σy + FXX σx2 + FYY σy2 + 2 FXY σx σy + FSS τxy2 where: FX = 1/TX - 1/CX FY = 1/TY - 1/CY FXX = 1/(TX CX) FYY = 1/(TY CY) FXY = IXY sqrt(FXX FYY) = IXY / sqrt(TX CX TY CY) FSS = 1 / (SXY SXY) Because this failure theory is quadratic, the Strength Ratio (SR) = 1/F I. However, multiplying the failure criterion by SR and rearranging gives a SR2 + b SR - 1 = 0 where a = FXX σx2 + FYY σy2 + 2 FXY σx σy + FSS τxy2 b = FX σx + FY σy Therefore SR = [-b + sqrt (b 2 + 4a)] / 2a


In the Laminate Modeler, the Tsai-Wu Tsai-Wu criterion for in-plane loads (representing fiber failure) has been supplemented by a maximum load theory for out-of-plane shear loads (representing matrix failure): FI = max( abs( γyz)/SYZ, abs( γxz)/SXZ ) In this case, SR = 1/FI For every ply, the lower of the Margins of Safety for fibre and matrix failure is calculated and displayed.

Extended Quadratic Criteria These criterion are identical to the t he Tsai-Wu Tsai-Wu criterion except for the calculation of the interaction coefficient FXY which is derived rather than obtained from experimental results.

Hoffman FXY = - 1 / (2 TX CX)

Hankinson FXY = 0.5 / (1/(TX CX) + 1/(TY CY) - 1/SXY 2)

Cowin FXY = 1 / sqrt(TX CX TY CY) - 0.5 /SXY 2

User-Defined Criterion The user can write a custom PCL function to generate failure indices and margins of safety according to specialized failure criteria. For example, sophisticated failure criteria are being developed which incorporate a mixture of equations depending on the expected mode of failure. These could be expected to outperform simple criteria where there is a complex l oading state, particularly within thick laminates. To use this facility, the user should modify the function user() within the class p3CM_create_res_fail_user. A sample function based on the criteria of maximum loading is illustrated below. The function has input values of loading state and material strength data. The output values are the margin of safety, the critical component, and a failure index. The required function should be edited into a file “p3CM_create_res_fail_user.user.pcl.” This function must then be substituted for the default dummy function in the Laminate Modeler PCL library. To do this, save a backup copy of the existing laminate_modeler.plb, and issue the following commands in the command line: !! LIBRARY ADD laminate_modeler.plb !! COMPILE p3CM_create_res_fail_user.user INTO laminate_modeler.plb The PCL source code required to implement the maximum failure criteria follows as an example: CLASS p3CM_create_res_fail_user FUNCTION user(res_array,mat_array,out_res_array)


REAL res_array() REAL mat_array() REAL out_res_array() REAL sxx,syy,szz,sxy,syz,sxz REAL fxt,fxc,fyt,fyc,fs12,fs23,fs31 REAL margin,component,fi REAL fi11t,fi11c,fi22t,fi22c,fi12,fi23,fi31 /* * Set input values. */ sxx syy szz sxy syz sxz

= = = = = =

res_array(1) res_array(2) res_array(3) res_array(4) res_array(5) res_array(6)

fxt = mat_array(1) fxc = mat_array(2) fyt = mat_array(3) fyc = mat_array(4) fs12 = mat_array(5) fs23 = mat_array(6) fs31 = mat_array(7) /* * Check that failure values are reasonable. */ IF ( (fxt<=0.) || @ (fxc<=0.) || @ (fyt<=0.) || @ (fyc<=0.) || @ (fs12<=0.) || @ (fs23<=0.) || @ (fs31<=0.) ) THEN user_message(“Ack”,4,”LAMMODEL”,”Failure strength values must be > 0.0”) RETURN END IF /* * Initialise variables. */ margin = 0.0 component = 1.0 fi = 1.0 sys_allocate_array(out_res_array,1,3) out_res_array(1) = 0.0 out_res_array(2) = 1.0 out_res_array(3) = 1.0


/* * Calculate strength ratios for each component. */ fi11t = sxx / fxt IF( fi < fi11t )THEN fi = fi11t margin = 1. / fi - 1 component = 11 ENDIF fi11c = -sxx / fxc IF( fi < fi11c )THEN fi = fi11c margin = 1. / fi - 1 component = -11 ENDIF fi22t = syy / fyt IF( fi < fi22t )THEN fi = fi22t margin = 1. / fi - 1 component = 22 ENDIF fi22c = -syy / fyc IF( fi < fi22c )THEN fi = fi22c margin = 1. / fi - 1 component = -22 ENDIF fi12 = mth_abs(sxy) / fs12 IF( fi < fi12 )THEN fi = fi12 margin = 1. / fi - 1 component = 12 ENDIF fi23 = mth_abs(syz) / fs23 IF( fi < fi23 )THEN fi = fi23 margin = 1. / fi - 1 component = 23 ENDIF fi31 = mth_abs(sxz) / fs31 IF( fi < fi31 )THEN fi = fi31 margin = 1. / fi - 1 component = 31 ENDIF /* * Set output values. */ out_res_array(1) = margin out_res_array(2) = component


out_res_array(3) = fi END FUNCTION END CLASS


Appendix A: Bibliography MSC Laminate Modeler User’s Guide

A

Bibliography

164 164 MSC Laminate Modeler User’s Guide

Bibliography 1. Bergsma, Bergsma, O.K. and Huisman, J. “Deep Drawing Drawing of Fabric Reinforced Reinforced Thermoplast Thermoplastics,” ics,” in Brebbia, C., et al., CAD in Composite Material Technology (Southampton, Computational Mechanics, 1988). 2. Berg Bergsma sma,, O.K O.K.. Deep Drawing of Fabric Reinforced Thermoplastics: Simulation and Experiment (Delft University of Technology, Department of Aerospace Engineering). 3. Call Callad adin ine, e, C. C. Theory of Shell Structures, Chapter 5. 4. Heisey, F.L., F.L., et al. “Three-Dimensi “Three-Dimensional onal Pattern Pattern Drafting,” Drafting,” Textile Research Journal, November 1990, pp. 690-696. 5. Collier, J.R., Collier, B.J., O’Toole, G. and Sargand, S.M. “Drape Prediction by Means Means of FiniteElement Analysis,” J. Text. Inst., 1991, Vol. 82, No. 1, pp. 96-107. 6. Heisey, F.L., and Haller, K.D. “Fitting Woven Fabric To Surfaces in Three Dimensions,” J. Text. Inst., 1988, No. 2, pp. 250-263. 7. Hinds, B.K., B.K., McCartney, McCartney, J., and Woods ,G. “Pattern Developmen Developmentt for Three Dimensional Dimensional Surfaces” (Queens University Belfast, Department of Mechanical and Manufacturing Engineering). 8. Kawab Kawabata ata,, S. The Standardization and Analysis of Hand Evaluation, 2nd ed., (Osaka, Japan, The Textile Machinery Society of Japan, 1980). 9. Mack, C., and Taylor, Taylor, H.M. “The “The Fitting of Woven Cloth Cloth to Surfaces,” Surfaces,” J.Text. Inst., 1956, No. 47, pp. T477-88. 10. Mallon, P.J., O’Bradaigh, O’Bradaigh, C.M., and Pipes, R.B. R.B. “Polymeric Diaphragm Forming of ComplexCurvature Thermoplastic Composite Parts,” Composites, Vol. 20, No. 1, Jan. 1989, pp.48-56. 11. Monaghan, M.R., Mallon, P.J., O’Bradaigh, O’Bradaigh, C.M., and Pipes, R.B. “The Effect of Diaphragm Stiffness on the Quality of Diaphragm Formed Thermoplastic Composite Components,” The Journal of Thermoplastic Composite Materials, Vol. 3, July 1990, pp.202-215. 12. Okine, R.K. “Analysis “Analysis of Forming Parts from from Advanced Thermoplas Thermoplastic tic Composite Composite Sheet Materials,” The Journal of Thermoplastic Composite Materials, Vol. 2, Jan. 1989, pp.50-77. 13. Potter, K.D. “The Influence Influence of Accurate Stretch Data for Reinforcements on the the Production of Complex Structural Mouldings -- Part 1. Deformation of Aligned Sheets & Fabrics,” Composites, July 1979, pp.161-167. 14. Potter, K.D. “The Influence Influence of Accurate Stretch Data for Reinforcement on the Production of Complex Structural Mouldings -- Part 2. Deformation of Random Mats,” Composites, July 1979, pp. 168-173. 15. 15. Pott Potter er,, K.D. K.D. Deformation Mechanisms of Fibre Reinforcements and Their Influence on the Fabrication of Complex Structural Parts (London, Controller HMSO, 1980). 16. Robertson, R.E., et al. “Fiber Rearrangements During the Moulding of Continuous Fiber Composites. 1: Flat Cloth to a Hemisphere,” Polymer Composites, July 1981, Vol. 2, No. 3, pp. 126-131. 17. 17. Skel Skelto ton, n, J. Shear Of Woven Fabrics (Dedham MA, USA, FRL, 1979).

165 Appendix A: Bibliography 165

18. Smiley, A.J., A.J., and Pipes, R.B. “Analysis “Analysis of the Diaphragm Forming Forming of Continuous Continuous Fiber Reinforced Thermoplastics,” The Journal of Thermoplastic Composite Materials, Vol. 1, Oct. 1988, pp. 298-321. 19. Stubbs, Stubbs, N., and Fluss, H. “A Space-truss Space-truss Model for Plain-Weav Plain-Weavee Coated Fabrics,” Fabrics,” Appl. Math. Modeling, Vol. 4, Part 1, Feb. 1980, pp. 51-58. 20. Tam, A.S., and Gutowski, T. “Ply-Slip During the Forming of Thermoplastic Composite Parts,” Journal of the ASCE Engineering Mechanics Division, Vol. 104, Part 5, Oct, 1978. 21. Testa, R.B., Stubbs, N., and Spillers, W.R. W.R. “Bilinear Model For Coated Square Fabrics,” The Journal of the ASCE Engineering Mechanics Division, Vol. 104, Part 5, Oct. 1978, pp. 10271042. 22. Van Der Weeen, F. “Algorithms For Draping Fabrics on on Doubly-Curved Surfaces,” International pp. 1415-1426. 1415-1426. Journal for Numerical Methods in Engineering, Vol. 31, 1991, pp. 23. Van West, West, B.P., B.P., et et al. al. The Draping and Consolidation of Commingled Fabrics (Delaware USA, Center for Composite Materials and Dept. of Mechanical Engineering, University of Delaware, 1990). 24. Wormersley, J.R. “The Application of Differential Geometry to the Study of of the Deformation Deformation of Cloth Under Stress,” J. Text. Inst., 1937, pp.T97-112.

166 166 MSC Laminate Modeler User’s Guide

MSC.Fatigue Quick Start Guide

Index MSC Laminate Modeler User’s Guide

Index Ind Ind ex

A

F

anisotropic behavior, 11 anisotropy, 11 automated tow placement, 13

fiber angles, 146 axis method, 146 planar method, 146 filament winding, 6, 13 filamentary composites, 11 fabrics, 11, 12 glass fibre/polyester mixture, 11 graphic fibre/epoxy resin, 11 tows, 11 finite element analysis, 20 flat plates, 140

B bottom, 57

C CAD systems, 19, 21 CADDS 5, 19 CATIA, 19 composites data, 6 compression moulding, 13 conceptual design, 15 core samples, 18 cross sections, 18 curved shells, 140

D

G Gaussian curvature, 24, 25, 140 negative, 24, 140 positive, 24, 140 zero, 140 geodesic global draping, 26, 143 geodesic lines, 140 global draping, 25, 26, 143 energy, 27, 145 geodesic, 26, 143 planar, 27, 144

degree of shear, 25 detailed development, 15 developable surfaces, 21 dome-shaped surfaces, 24 doubly-curved, 18 doubly-curved surfaces, 24 drape simulation, 20 draping global, 143 local, 142 scissor, 142 slide, 143

incomplete boundary definition, 148 initial direction, 57 initial direction vector, 58

E

L

energy global draping, 27, 145 Euclid 3, 19 excessive Gaussian curvature, 148

lamination theory, 12, 13 layer, 42, 55

H holes in surfaces, 148

I

168 MSC Laminate Modeler User’s Guide

layer materials, 49 painted, 49 projected, 49 scissor draped, 49 slide draped, 49 layup, 42, 74 layup ply table, 42 layup sequence, 42 layup table, 30 LM_layer material, 55 local draping, 25, 142

M manual layup, 6 material generation, 49 maximum strain, 50, 111 mesh, 44, 57 MSC.Mvision, 19 MSC.Patran COMPOSITE, 20 MSC.Patran FEA, 20

N nesting software, 19 non-developable, 18 non-developable surfaces, 24, 55

O outline design, 15

P planar global draping, 27, 144 ply, 42 ply laminate, 42 ply-book, 18 pressure vessels, 27 Pro/ENGINEER, 19 production methods filament winding, 6 manual layup, 6 resin transfer method (RTM), 6

R resin flow, 19 resin transfer moulding, 6, 13

RTM, 13 ruled surfaces, 21

S saddle-shaped surfaces, 24 sandwich structures, 21 scissor draping, 26, 27, 142 shell model, 46 simulation, 6 slide draping, 26, 143 springback, 19 SRIM, 13 stacking sequences, 74 step length, 146 structural reaction injection moulding, 13

T T sections, 149 thickness, 50 top, 57 top-hat section, 31

U Unigraphics, 19

V view direction, 58

W waffle plate, 21 warp, 144 warp/weft angle, 50 weft, 144 wet layup, 12

Z zero Gaussian curvature, 21

MSC Laminate Modeler Version 2008 User's Guide

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