Tutori l 11b: Composite , Modelling ply failure Stephanie Miot
First matrix crack Fibre failure initiation
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1.
Introduction
In this tu tutorial, yo you wi will mo mo ify a structural model of a stiffened pan l to define the mate ma teri rial al pr prop oper erti ties es in inc clu ludi di g th the e pl ply y fa fail ilur ure e par aram amet eter ers s. You wil illl t en perform a stat st atic ic an anal alys ysis is of a ben bendi ding test and visua visualize lize the simulatio simulation n o the damage propagation with Abaqus/Viewer.
When you complete this tu orial, you will be able to: -
Define the material ro rope perti rties es of a com compo posi site te ply ply inc inclu ludi ding ng t e coefficients of th the e Has Hashi hin’ n’s s fa fail ilu u e criteria
-
Define a damage pr pagation model
-
Use Us e the vi visu sual aliz izati atio o module to create ply stack plots and c ntour plots on different plies
Preliminaries The stiffened panel is com osed of: -
-
a skin •
Dimensions: 600 mm x 1000 m, 6 mm thick
•
Lay-up: (-452, 452, 02, 902, 02, 902)S
•
Material: UD arbon / epoxy T300/M18
2 stiffeners •
Dimensions: 00 mm x 140 mm, 1600 mm long, 4 mm thick
•
Lay-up: (02, - 52, 902, 452)S
•
Material: UD arbon / epoxy T800/M18
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Figure 1: Stiffened panel
2.
Setting up the model
Open the model Tutorial1 b.cae. This file contains the asse bly as presented in Figure 1. The unit are: mm and MPa. In this tutorial, you will defi e: -
the properties for ach material and include the Hashin’s failure criteria and the progressive damage models
-
the lay-up of the co ponents
-
the mesh
-
the static analysis
-
the boundary conditions and the loading.
Finally, you will run a static analysis and use the visualization m dule to postprocess the results of the simulation.
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3.
Material and section properties
1. Define the mechanical behaviour of the UD plies with the foll wing material properties:
T300/M18
T80 /M18
Elasticity coefficients E1
170 GPa
19 GPa
E2
9 GPa
15 GPa
ν12
0.34
0.34
G12
4.8 GPa
5.6 GPa
G13
4.8 GPa
5.6 GPa
G23
4.5 GPa
4.9 GPa
Hashin’s failure criteria coefficients XT
2050 MPa
2240 MPa
XC
1200 MPa
1230 MPa
YT
62 MPa
71 MPa
YC
190 MPa
21 MPa
SL
81 MPa
90 MPa
ST
81 MPa
90 MPa
Fracture toughnesses Long. tensile fracture energy: Gftc
95 kJ/m²
105 kJ/m²
Long. compressive fracture energy: Gfcc
103 kJ/m²
108 kJ/m²
Trans. tensile fracture energy: Gmtc
0.2 kJ/m²
0.2 kJ/m²
Trans. compressive fracture energy: Gmcc
0.2 kJ/m²
0.2 kJ/m²
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a. Go into the Property Module and click the Create Material icon
b. In the Edit Material dialog box, name the material T300/M18 .
c. From the material edi or’s menu bar, select Mechanical
→
Elasticity
→
Elastic. Select Type: Lamina and enter the material data as de ined above.
d. Select Mechanical → Damage and enter the
amage for Fiber-Reinforced Composi tes
→
Hashin
aterial data as defined above.
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e. Click Suboptions and select Damage Evolution. In the Sub ption Editor dialog box, enter the parameters as defined above.
f. Click Suboptions and elect Damage Stabilization. Specify the value of the viscosity coefficient f r each failure mode: 1e-4.
g. Follow the instructions
to f to create the material T800/M18.
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2. Define the lay-up of each component. The skin is made of 24 plies. The stacking sequence is defi ed as: (-452, 452, 02, 902, 02, 902)S. The stiffener is made of 16 plies. The stac ing sequence is defined as: (0 2, -452, 902, 452)S. a. Click the Create Comp site Layup icon definition: Skin lay-up .
.
Name
the
new
lay-up
et the Initial ply count at 6 and selec the Element
Type: Continuum She l. Click Continue...
b. In the Edit Composite Layup dialog box, define the Layup orie tation. Select Definition: Coordinat
system. Click the Select CSYS icon
Datum csys-1. Click O
to go back to the composite lay-up editor.
to select
c. Accept the default selection for the Normal direction: Ax s 3 and the Stacking Direction: El ment direction 3.
d. In the Plies tab, toggle on Make calculated sections symm tric. Rename the plies then double-click the Region button and select the entire part. e. Double-click the Materi l button and select the material: T300/M18. f. Double-click the Elem nt Relative Thickness button and s t the relative thickness of each ply at 0.25. Note: The sum of the relative thicknesses does not need to be equal to 1. The result will be automatic lly normalised by Abaqus. g. In the column Rotation Angle, define the orientation for each pl . h. Finally, set the number of Integration Points at 1.
i.
Use the options availa le in the Display tab to check the ori ntation of the lay-up. Then click OK t create the new lay-up.
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j.
Follow the instructions
to i to define the lay-up of the stiffener.
Note: The stiffener is m de of two regions: -
seat, 16-ply region, 02, -452, 902, 452)S
-
web, 32-ply region, (02, -452, 902, 452, 452, 902, -452, 02)S
See Tutorial 10 for mor detailed instructions if needed.
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4.
Mesh
1. Create the FE mesh fo the skin. a. Go into the Mesh Mod le and select the Part: Skin in the menu bar.
b. Click the Assign Ele ent Type icon
. Select the entir
part. In the
Element Type dialog ox, select Family: Continuum Shell and accept the other default selections.
c. Click the Seed Part ico
. Set the approximate global si e at 30 mm.
d. Click the Assign Mesh Controls icon
. Select Techniqu : Sweep and
Algorithm: Medial axis.
e. Click the Mesh Part icon
and click Yes.
f. Check that the stacking direction is correct. Click the Assign Stack Direction icon
and select the top face of the skin to define
he reference
orientation.
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2. Create the FE mesh fo the stiffener. a. Select the Part: Stiffener in the menu bar or right click Stiffener in the model tree and select Make C rrent.
b. Assign the element typ : Continuum Shell and set the appro imate global size of the elements at 20 mm.
c. Mesh the part and assi n the stacking direction.
d. In the menu bar, select Object: Assembly to visualise the mesh of the different instances.
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5.
Static analysi
1. Create a new analysis tep and define the parameters of the analysis. a. Go into the Step Module. Click the Create Step icon
b. Select the type of procedure: Static, General and click Continu ...
c. In the Edit Step dialog box, toggle on Nlgeom. In the Incre entation tab, define the Maximum
umber of increments: 100 000 and the Increment
size: Initial: 0.01, Mini um: 1e-9, Maximum: 0.1. Click OK.
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2. Create new output req ests. The preselected default output does not include the damage variables an
the default selection of the layered
includes only the top an
bottom points. To visualize the stresses and the
damage evolution in each ly in the Visualization module, you will
ection points
rite additional
field output to the output d tabase file. a. Click the Create Field
utput icon
b. In the Edit Field Output Request dialog box, select Domain: S t: Skin-1.All. Then select Frequency: Evenly spaced time intervals and set Interval: 10. c. In the Output Variabl s list, expand the Stresses list and toggle on the variable S, then expan the Failure/Fracture list and toggle o the variables DAMAGEFT,
DAMA EFC,
DAMAGEMT,
HSNFCCRT,
HSNM CRT,
and
DAMAGEMC,
HSNMCCRT.
Finally,
HSNFTCRT, expand
the
State/Field/User/Time list and toggle on the variable STATUS. d. Specify the output at layered section points: 1, 2, 3, 4, 5, 6 and lick OK. e. Click the Field Output
anager icon
. Select the second field output
requests F-Output-2 cr ated in Step-1 and click Copy... f. Rename the new field utput request: F-Output-3 and click O . In the Field Output Requests Man ger, F-Output-3 is selected. Click Edit.. g. Modify the selection o the Domain: Set: Stiffener-1.All. Th n modify the specification of the layered section points: 1, 2, 3, 4. Click OK. h. Follow the instructions
to g to create a new field output reque t: F-Output-4
for the second stiffener: Domain: Set: Stiffener-2.All.
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6.
Boundary conditions
1. Preliminary work: cre te a reference point and define a coupling constraint between the point and the ace of the skin where the loading is applied. This is to simplify the post-processing. The displacement and the total reaction force can then be extracted at a single point. a. Go into the Interaction Module. Click the Create Reference Point icon
b. Specify the coordinates X, Y, Z: 0., 900., 3.
c. Click the Create Const aint icon
. Accept the default na e and select
Coupling. Click Continue...
d. Select the constraint control points: RP-1, the constraint region type: Surface and the surface: BC-2. e. In the Edit Constraint dialog box, accept the default sele tions for the Coupling type: Kinematic and the Constrained degrees of freedom: All. Click OK.
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2. Create new boundary onditions a. Go into the Load Module. Click the Create Boundary Condition icon
b. Select
Step:
Initial,
Category:
Mechanical
nd
Type:
Displacement/Rotatio . Click Continue...
c. Select the region from the list of eligible Sets: BC-1. Toggle on U1, U2 and U3. Click OK.
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d. Create a new Boun ary Condition. Select Step: Step- , Category: Mechanical and Type: Displacement/Rotation. Click Continu ...
e. Select the reference
oint RP-1 then specify the applied
isplacements:
U2 = 14 mm and U3 = -70 mm. Click OK.
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7.
Analysis and ost-processing
1. Run the job. a. Go into the Job Modul . Click the Create Job icon.
b. Name the new job: Pan el01. Click Continue...
c. In the Edit Job dialog box, open the tab: Parallelization. T ggle On Use multiple processors a d set the number of processors at 4. A cept the other default selections and click OK. Then submit the job: Panel01. d. Click Monitor... to monitor the job while it is running.
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2. Analyse the results of he simulation.
a. When the job submission has been completed, in the Job M nager dialog box, click Results or open Panel01.odb in the Visualization Module.
b. Click the Create Display Group icon
or click Tools
→
Dis lay Group
→
Create...
c. In the Create Display Group dialog box, select Part insta ces: SKIN-1. Click the Replace icon
then click Dismiss.
d. Click the Plot Contour on Deformed Shape icon
e. Click the Field Output
f. In the Field Output
ialog icon
or click Result → Field Output.
ialog box, in the Primary Variable t b, select the
Output Variable: HSN TCRT. Click Apply then click Section Points.. g. In the Section Points ialog box, click Selection method: Plies and select the ply Skin - ply 0 - 1. Click Apply. You can then visualise he fibre failure prediction in the 0° ply. 1 2
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h. In the Field Output di log box, select the Output Variable: DAMAGEFT to visualise the fibre failure propagation. Click Apply. In the S ction Points dialog box, click Selection method: Plies and select the ply S in - ply 0 - 1. Click Apply.
i.
In the Field Output di log box, select the Output Variable: D MAGEMT to visualise the matrix failure propagation. In the Section Poin s dialog box, select the ply Skin - ply 90-1. Then select Skin - ply -45. Yo can observe the propagation of the
atrix damage in the different plies. 2
1 1 2
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j.
Click the Replace All icon
.
k. Click the Common Options icon
and select Visible E ges: Feature
edges. Click OK.
l.
In the Field Output di log box, select the Output Variable: D MAGEFT. In the Section Points dialog box, select the ply SRO - ply 0. Click Apply. Select various variable and section points to plot the numeri al predictions for the damage initiatio and propagation in different plies.
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m. Click Tools
→
XY Dat
→
Create. In the Create XY Data dial g box, select
ODB field output. Clic Continue...
n. In the XY Data from
DB Field Output dialog box, in the
ariables tab,
select Position: Unique Nodal. In the variables list, expand RF: Reaction force and toggle on M gnitude, then expand U: Spatial disp acement and toggle on Magnitude. In the Elements/Nodes tab, select
ethod: Node
sets: ASSEMBLY_C NSTRAINT-2_REFERENCE_POINT.
lick Save. A
warning message is displayed. Click OK. Then click Dismiss.
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o. Click Tools
→
XY Dat
→
Create. In the Create XY Data dial g box, select
Operate on XY data. Click Continue...
p. In the Operate on X
Data dialog box, in the Operators column, click
combine(X,X). Double click U:Magnitude PI: ASSEMBLY..., add “,” then double click RF:Magnitude PI: ASSEMBLY.... Click Plot Expression. q. In the model tree, expa d XYData and rename _temp_1: Load isp.
r. Double-click the chart. In the Chart Options dialog box, toggle off Fill then click Dismiss. Double- lick the X axis. In the Axis Options dialog box, in the Title tab, click the Font icon. Set the size at 24 and click OK. In the Axes tab, click the Font icon and set the size at 18.
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s. Follow instruction r to
t. Click Options
→
odify the font sizes for the Y axis.
XY Options
→ Curve... In
the Curve Optio s dialog box,
increase the thickness f the curve then click Dismiss.
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