Abaqus Tutorial 11b PlyFailure (1)

Strategic

Southill Barn, Southill Business Park, Cornbury Park, Charlbury, Oxfordshire, OX7 3EW

T. 01608 811777 F. 01608811770 [email protected] W. www.ssanalysis.co.uk

Tutorial Modelling

First matrix crack

Strategic Simulation & Analysis Ltd



Tutorial 11b: Composites

Modelling ply failure

Stephanie Miot

Fibre failure



: Composites ,

Fibre failure initiation




1. Introduction

In this tutorial, you will modify a structural model of

material properties including

static analysis of a bending

propagation with Abaqus/Viewer

When you complete this tutorial, y

- Define the material properties of a composite ply

of the Hashin’s failure criteria

- Define a damage propagation model

- Use the visualization module to create

different plies

Preliminaries

The stiffened panel is composed of:

- a skin

• Dimensions: 16

• Lay-up: (-452,

• Material: UD carbon / epoxy

- 2 stiffeners

• Dimensions: 20

• Lay-up: (02, -45

• Material: UD carbon / epoxy




modify a structural model of a stiffened panel

material properties including the ply failure parameters. You will then

bending test and visualize the simulation of the damage

Abaqus/Viewer.

When you complete this tutorial, you will be able to:

Define the material properties of a composite ply including the

ashin’s failure criteria

Define a damage propagation model

Use the visualization module to create ply stack plots and contour plots

The stiffened panel is composed of:

Dimensions: 1600 mm x 1000 m, 6 mm thick

, 452, 02, 902, 02, 902)S

Material: UD carbon / epoxy T300/M18

Dimensions: 200 mm x 140 mm, 1600 mm long, 4 mm thick

452, 902, 452)S

Material: UD carbon / epoxy T800/M18


T. 01608 811777 F. 01608811770 [email protected] W. www.ssanalysis.co.uk 2

a stiffened panel to define the

You will then perform a

simulation of the damage

including the coefficients

and contour plots on

m long, 4 mm thick




2. Setting up the model

Open the model Tutorial11b

This file contains the assembly as presented in Figure 1.

MPa.

In this tutorial, you will define

- the properties for each

and the progressive damage models

- the lay-up of the components

- the mesh

- the static analysis

- the boundary conditions and the loading.

Finally, you will run a static analysis and use the visualization module to post

process the results of the simulation.




Figure 1: Stiffened panel

Setting up the model

Tutorial11b .cae.

the assembly as presented in Figure 1. The units are: mm and

define:

for each material and include the Hashin’s failure criteria

nd the progressive damage models

components

boundary conditions and the loading.

run a static analysis and use the visualization module to post

process the results of the simulation.



The units are: mm and

Hashin’s failure criteria

run a static analysis and use the visualization module to post-




3. Material and section

1. Define the mechanical

properties:

E1

E2

ν12

G12

G13

G23

Hashin’s failure criteria coefficients

XT

XC

YT

YC

SL

ST

Long. tensile fracture energy: Gftc

Long. compressive fracture energy: Gfcc

Trans. tensile fracture energy: Gmtc

Trans. compressive fracture energy: Gmcc




and section properties

behaviour of the UD plies with the following

T300/M18 T800/M18

Elasticity coefficients

170 GPa 192

9 GPa 15

0.34 0.3

4.8 GPa 5.6

4.8 GPa 5.6

4.5 GPa 4.9

Hashin’s failure criteria coefficients

2050 MPa 2240 MPa

1200 MPa 1230 MPa

62 MPa 71

190 MPa 210 MPa

81 MPa 90

81 MPa 90

Fracture toughnesses

95 kJ/m² 105 kJ/m

103 kJ/m² 108

0.2 kJ/m² 0.2 kJ/m²

0.2 kJ/m² 0.2 kJ/m²



following material

T800/M18

92 GPa

GPa

0.34

5.6 GPa

5.6 GPa

4.9 GPa

0 MPa

0 MPa

MPa

0 MPa

MPa

MPa

5 kJ/m²

108 kJ/m²

0.2 kJ/m²

0.2 kJ/m²




a. Go into the Property Module

b. In the Edit Material dialog box, name the material

c. From the material editor’s menu bar, select

Elastic. Select Type: Lamina

d. Select Mechanical → Damage for Fiber

Damage and enter the material




Property Module and click the Create Material icon

dialog box, name the material T300/M18.

From the material editor’s menu bar, select Mechanical →

Type: Lamina and enter the material data as defined above.

Damage for Fiber -Reinforced Composites

nter the material data as defined above.



icon

Elasticity →

and enter the material data as defined above.

Reinforced Composites → Hashin




e. Click Suboptions and select

dialog box, enter the parameters as defined above.

f. Click Suboptions and select

viscosity coefficient for each failure mode: 1e

g. Follow the instructions a




and select Damage Evolution . In the Suboption Editor

he parameters as defined above.

and select Damage Stabilization . Specify the value of the

for each failure mode: 1e-4.

a to f to create the material T800/M18.



Suboption Editor

Specify the value of the




2. Define the lay-up of each component

stacking sequence is defined as:

made of 16 plies. The stacking sequence is defined as:

a. Click the Create Composite Layup

definition: Skin lay-up. Set the

Type: Continuum Shell

b. In the Edit Composite Layup

Definition: Coordinate system

Datum csys-1 . Click OK

c. Accept the default selection for the

Stacking Direction: Element direction 3

d. In the Plies tab, toggle on

the plies then double-click the

e. Double-click the Material

f. Double-click the Element Relative Thickness

thickness of each ply at 0.

Note: The sum of the relative thicknesses does not need to be equal to 1. The

result will be automatically normalised by Abaqus.

g. In the column Rotation Angle

h. Finally, set the number of

i. Use the options available in the

lay-up. Then click OK to create the new




each component . The skin is made of 24 plies. The

stacking sequence is defined as: (-452, 452, 02, 902, 02, 902)S. The stiffener is

made of 16 plies. The stacking sequence is defined as: (02, -452, 90

Composite Layup icon . Name the new lay

. Set the Initial ply count at 6 and select the

Continuum Shell . Click Continue...

Edit Composite Layup dialog box, define the Layup orientation. Select

Definition: Coordinate system . Click the Select CSYS icon to select

OK to go back to the composite lay-up editor.

Accept the default selection for the Normal direction: Axis 3

Stacking Direction: Element direction 3 .

tab, toggle on Make calculated sections symmetric

click the Region button and select the entire part

Material button and select the material: T300/M18

Element Relative Thickness button and set the relative

at 0.25.


result will be automatically normalised by Abaqus.

Rotation Angle , define the orientation for each ply.

of Integration Points at 1.

the options available in the Display tab to check the orientation of the

to create the new lay-up.



The skin is made of 24 plies. The

The stiffener is

902, 452)S.

. Name the new lay-up

and select the Element

dialog box, define the Layup orientation. Select

icon to select

up editor.

Normal direction: Axis 3 and the

Make calculated sections symmetric . Rename

button and select the entire part.

T300/M18.

button and set the relative


ne the orientation for each ply.

tab to check the orientation of the




j. Follow the instructions a

Note: The stiffener is made of

- seat, 16-ply region, (0

- web, 32-ply region, (0

See Tutorial 10 for more detailed instructions if needed.




a to i to define the lay-up of the stiffener.

Note: The stiffener is made of two regions:

(02, -452, 902, 452)S

(02, -452, 902, 452, 452, 902, -452, 02)S

See Tutorial 10 for more detailed instructions if needed.






4. Mesh

1. Create the FE mesh for the

a. Go into the Mesh Module

b. Click the Assign Element Type

Element Type dialog box, select

other default selections.

c. Click the Seed Part icon . Set the

d. Click the Assign Mesh Controls

Algorithm : Medial axis.

e. Click the Mesh Part icon

f. Check that the stacking direction is correct. Click the

icon and select the top face of the skin to define the reference

orientation.




1. Create the FE mesh for the skin .

Module and select the Part: Skin in the menu bar.

Assign Element Type icon . Select the entire part. In the

dialog box, select Family: Continuum Shell and accept the

other default selections.

icon . Set the approximate global size

Assign Mesh Controls icon . Select Technique

: Medial axis.

icon and click Yes.

Check that the stacking direction is correct. Click the Assign Stack Direction

and select the top face of the skin to define the reference



in the menu bar.

. Select the entire part. In the

and accept the

approximate global size at 30 mm.

Technique : Sweep and

Assign Stack Direction

and select the top face of the skin to define the reference




2. Create the FE mesh for the

a. Select the Part: Stiffener

tree and select Make Current

b. Assign the element type:

size of the elements at 2

c. Mesh the part and assign the stacking direction.

d. In the menu bar, select

different instances.




. Create the FE mesh for the stiffener .

Part: Stiffener in the menu bar or right click Stiffener

Make Current .

ype: Continuum Shell and set the approximate global

of the elements at 20 mm.

Mesh the part and assign the stacking direction.

In the menu bar, select Object: Assembly to visualise the mesh



Stiffener in the model

approximate global

to visualise the mesh of the




5. Static analysis

1. Create a new analysis step

a. Go into the Step Module

b. Select the type of procedure:

c. In the Edit Step dialog box, toggle on

define the Maximum number of increments:

size: Initial: 0.01, Minimum:




Static analysis

new analysis step and define the parameters of the analysis

Module . Click the Create Step icon

Select the type of procedure: Static, General and click Continue...

dialog box, toggle on Nlgeom . In the Incrementation

aximum number of increments: 100 000 and the

Minimum: 1e-9, Maximum: 0.1. Click OK.



and define the parameters of the analysis.

Continue...

Incrementation tab,

100 000 and the Increment




2. Create new output requests.

the damage variables and the default selection of the layered section points

includes only the top and bottom points

damage evolution in each ply

field output to the output database file

a. Click the Create Field Output

b. In the Edit Field Output Request

Then select Frequency: Evenly spaced time intervals

c. In the Output Variables

variable S, then expand

DAMAGEFT , DAMAGEF

HSNFCCRT, HSNMTCRT

State/Field/User/Time

d. Specify the output at layered section points: 1, 2, 3, 4, 5, 6

e. Click the Field Output Manager

requests F-Output-2 created in

f. Rename the new field output request:

Output Requests Manager

g. Modify the selection of the

specification of the layered section points: 1, 2, 3, 4. Click

h. Follow the instructions e

for the second stiffener:




Create new output requests. The preselected default output does not include

and the default selection of the layered section points

includes only the top and bottom points. To visualize the stresses and the

damage evolution in each ply in the Visualization module, you will write additional

field output to the output database file.

Create Field Output icon

Edit Field Output Request dialog box, select Domain: Set:

Frequency: Evenly spaced time intervals and set

Output Variables list, expand the Stresses list and toggle on the

, then expand the Failure/Fracture list and toggle on the variables

DAMAGEFC, DAMAGEMT , DAMAGEMC ,

HSNMTCRT, and HSNMCCRT. Finally,

list and toggle on the variable STATUS.

the output at layered section points: 1, 2, 3, 4, 5, 6 and c

Field Output Manager icon . Select the second field output

created in Step-1 and click Copy...

Rename the new field output request: F-Output-3 and click OK

Output Requests Manager , F-Output-3 is selected. Click Edit...

Modify the selection of the Domain: Set: Stiffener-1.All . Then modify the

specification of the layered section points: 1, 2, 3, 4. Click OK.

e to g to create a new field output request:

for the second stiffener: Domain: Set: Stiffener-2.All .



does not include

and the default selection of the layered section points

stresses and the

write additional

Domain: Set: Skin-1.All .

and set Interval: 10 .

list and toggle on the

list and toggle on the variables

, HSNFTCRT,

expand the

click OK.

. Select the second field output

OK. In the Field

Edit...

. Then modify the

to create a new field output request: F-Output-4




6. Boundary conditions

1. Preliminary work: create a reference point and define a coupling constraint

between the point and the face 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

b. Specify the coordinates

c. Click the Create Constraint

Coupling . Click Continue...

d. Select the constraint control points: RP

Surface and the surface: BC

e. In the Edit Constraint

Coupling type: Kinematic

Click OK.




conditions

create a reference point and define a coupling constraint


processing. The displacement and the total reaction force can

en be extracted at a single point.

Interaction Module . Click the Create Reference Point

Specify the coordinates X, Y, Z: 0., 900., 3.

Create Constraint icon . Accept the default name and select

Continue...

constraint control points: RP -1, the constraint region type:

surface: BC -2.

Edit Constraint dialog box, accept the default selections for the

Coupling type: Kinematic and the Constrained degrees of freedom: A



create a reference point and define a coupling constraint


processing. The displacement and the total reaction force can

Create Reference Point icon

. Accept the default name and select

constraint region type:

dialog box, accept the default selections for the

Constrained degrees of freedom: A ll .




2. Create new boundary conditions

a. Go into the Load Module

b. Select Step: Initial

Displacement/Rotation

c. Select the region from the list of eligible

U3. Click OK.




Create new boundary conditions

Module . Click the Create Boundary Condition

Step: Initial , Category: Mechanical and

Displacement/Rotation . Click Continue...

Select the region from the list of eligible Sets: BC-1 . Toggle on



Create Boundary Condition icon

and Type:

. Toggle on U1, U2 and




d. Create a new Boundary Condition. Select

Mechanical and Type: Displacement/Rotation

e. Select the reference point

U2 = 14 mm and U3 = -




Create a new Boundary Condition. Select Step: Step- 1

Type: Displacement/Rotation . Click Continue...

Select the reference point RP-1 then specify the applied displacements:

-70 mm. Click OK.



1, Category:

Continue...

then specify the applied displacements:




7. Analysis and post

1. Run the job.

a. Go into the Job Module

b. Name the new job: Panel01

c. In the Edit Job dialog box, open the tab:

multiple processors and set the number of processors at

default selections and click

d. Click Monitor... to monitor the job while it is running.




nalysis and post -processing

Module . Click the Create Job icon.

Panel01. Click Continue...

dialog box, open the tab: Parallelization . Toggle On

and set the number of processors at 4. Accept the other

default selections and click OK. Then submit the job: Panel01.

to monitor the job while it is running.



. Toggle On Use

. Accept the other




2. Analyse the results of the simulation.

a. When the job submission has been completed, in the

box, click Results or open

b. Click the Create Display

Create...

c. In the Create Display Group

Click the Replace icon

d. Click the Plot Contours on Deformed Shape icon

e. Click the Field Output Dialog

f. In the Field Output dialog box,

Output Variable: HSNFTCRT

g. In the Section Points dialog box, click

the ply Skin - ply 0 - 1 . Click

You can then visualise the fibre failure prediction




the results of the simulation.

When the job submission has been completed, in the Job Manager

open Panel01.odb in the Visualization Module

Create Display Group icon or click Tools → Displa

Create Display Group dialog box, select Part instances:

icon then click Dismiss .

Plot Contours on Deformed Shape icon

Output Dialog icon or click Result → Field Output

dialog box, in the Primary Variable tab, select the

HSNFTCRT. Click Apply then click Section Points..

dialog box, click Selection method: Plies

. Click Apply .

You can then visualise the fibre failure prediction in the 0° ply.



Job Manager dialog

Visualization Module .

Displa y Group →

Part instances: SKIN-1.

Field Output .

tab, select the

Section Points..

Plies and select

1

2




h. In the Field Output dialog box, select the

visualise the fibre failure

dialog box, click Selection method: Plies

Click Apply .

i. In the Field Output dialog box, select the

visualise the matrix failure

select the ply Skin - ply

the propagation of the matrix damage in the different plies




dialog box, select the Output Variable: DAMAGEFT

fibre failure propagation. Click Apply . In the Section Points

Selection method: Plies and select the ply Skin

dialog box, select the Output Variable: DAMAGE

failure propagation. In the Section Points

ply 90-1. Then select Skin - ply -45 . You can observe

propagation of the matrix damage in the different plies.

1

2



Output Variable: DAMAGEFT to

Section Points

Skin - ply 0 - 1 .

Output Variable: DAMAGE MT to

Section Points dialog box,

. You can observe

1

2




j. Click the Replace All icon

k. Click the Common Options

edges . Click OK.

l. In the Field Output dialog box, select the

the Section Points dialog box, select the ply

Select various variables and

for the damage initiation and propagation in different plies.




icon .

Common Options icon and select Visible Edges:

dialog box, select the Output Variable: DAMAGE

dialog box, select the ply SRO - ply 0 . Click

Select various variables and section points to plot the numerical predictions

for the damage initiation and propagation in different plies.



Visible Edges: Feature

Output Variable: DAMAGE FT. In

Click Apply .

to plot the numerical predictions




m. Click Tools → XY Data

ODB field output . Click

n. In the XY Data from ODB Field Output

select Position: Unique Nodal

force and toggle on Magnitude

toggle on Magnitude . In the

sets: ASSEMBLY_CONSTRAINT

warning message is displayed. Click




XY Data → Create . In the Create XY Data dialog box, select

. Click Continue...

XY Data from ODB Field Output dialog box, in the Variables

Position: Unique Nodal . In the variables list, expand RF: Reaction

Magnitude , then expand U: Spatial displacement

. In the Elements/Nodes tab, select Method: Node

ASSEMBLY_CONSTRAINT -2_REFERENCE_POINT. Click

warning message is displayed. Click OK. Then click Dismiss .



dialog box, select

Variables tab,

RF: Reaction

Spatial displacement and

Method: Node

. Click Save. A




o. Click Tools → XY Data

Operate on XY data . Click

p. In the Operate on XY

combine(X,X) . Double click

double click RF:Magnitude

q. In the model tree, expand

r. Double-click the chart. In the

click Dismiss . Double-click the

Title tab, click the Font

click the Font icon and set the size at 18.




XY Data → Create . In the Create XY Data dialog box, select

. Click Continue...

Operate on XY Data dialog box, in the Operators

. Double click U:Magnitude PI: ASSEMBLY... , add “

Magnitude PI: ASSEMBLY... . Click Plot Expression

In the model tree, expand XYData and rename _temp_1: LoadDisp

click the chart. In the Chart Options dialog box, toggle off

click the X axis. In the Axis Options dialog box, in the

icon. Set the size at 24 and click OK. In the

on and set the size at 18.



dialog box, select

column, click

, add “,” then

Plot Expression .

_temp_1: LoadDisp .

dialog box, toggle off Fill then

dialog box, in the

. In the Axes tab,




s. Follow instruction r to modify the font sizes for the Y axis.

t. Click Options → XY Options

increase the thickness of the curve then click




to modify the font sizes for the Y axis.

XY Options → Curve... In the Curve Options

increase the thickness of the curve then click Dismiss .



Curve Options dialog box,

Abaqus Tutorial 11b PlyFailure (1)

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Transcript of Abaqus Tutorial 11b PlyFailure (1)