COMPOSITE STRUCTURESEXAMPLE #1

LINEAR ANALYSIS OF A CROSS-PLYLAMINATE SUBJECTED TO TENSION

Problem Description

P = 10 kN One-ply thickness = 1.0 mm Stacking sequence = [0/90]T E11 = 380 GPa, E22 = E33 = 8.2 GPa, 12 = 13 = 0.28, 23 = 0.47,

G12 = G13 = 4.5 GPa, G23 = 3.5 GPa

500 mm

free

free

x

yz

P

Step 1. Create a Database

Step 2. Create Geometry - Surface

a. Geometry : Create / Surface / XYZ

b. Select on Vector Coordinates List and enter < 500 250 0 >

c. Apply

Step 3. Create Mesh Seeds

a. Elements : Create / Mesh Seed / Uniform

b. Select Number of Elements and enter 6for the Number

c. Select the right edge and click Apply

d. Select Number of Elements and enter 12 for the Number

e. Select the bottom edge and click Apply

Step 4. Create Mesh

a. Elements : Create / Mesh / Surface

b. Select Elem Shape : Quad Mesher : IsoMesh Topology : Quad4

c. Click on Surface List and select Surface 1

d. Apply

Step 5. Create Constraints

a. Loads/BCs : Create / Displacement / Nodal

b. Select on New Set Name and enter disp_1

c. Select Input Data

d. Enter for Translations and for Rotations

e. OK

f. Click on Select Application Region

g. Select Geometry for Geometry Filter

h. Pick the Curve and Edge icon

i. Select on the left edge

j. Add

k. OK

l. Apply

Step 6. Create Load Condition

a. Loads/BCs : Create / Distributed Load/ Element Uniform

b. Select on New Set Name and enter dist_load

c. Target Element Type : 2D

d. Select Input Data

e. Enter for Edge Distr Load * 5000 N /125 mm = 40 N/mm

f. OK

g. Click on Select Application Region

h. Select Geometry for Geometry Filter

i. Select on the right edge

j. Add

k. OK

l. Apply

Step 6. Create Load Condition (Contd)

a. Select on Iso3 viewfrom the tool bar. Your model should look like the following.

Step 7. Define Material Properties MAT8

a. Materials : Create / 2d Orthotropic / manual Input

b. Select on Material Name and enter prepreg

c. Select Input Properties

d. Enter : Fill in properties

e. OK

f. Apply

Step 8. Define Failure Criteria

a. Click on prepreg in Existing Materials

b. Select Const. Model : Failure Failure Limits : Stress Comp Fail : Tsai-Wu

c. Enter : Fill in properties

d. OK

e. Apply

Step 9. Define Laminate PCOMP

a. Materials : Create / Composite / Laminate

b. Select prepreg in Existing Materials two times

c. Stacking Sequence Convention : Total

d. Fill in Stacking Sequence Definition Thickness : 1.0 mm Orientation : [0/90]

e. Select on New Material Nameand enter laminate

f. Apply

Step 10. Check [A], [B], and [D] Matrices

A B

B D

Step 11. Define Element Properties - PCOMP

a. Properties : Create / 2D / Shell

b. Select on Property Set Name and enter p_comp

c. Options : Laminate / Standard Formulation

d. Select Input Properties

e. Enter : Fill in properties

f. OK

g. Select on Application Regionand pick to include all geometry in window

h. Add

i. Apply

Step 12. Check Loads and Constraints

a. Load Cases : Modify

b. Select Default in Existing Load Cases

c. Make sure that all Loads and BCs are selected

d. Cancel

Step 13. Create NASTRAN Input File

a. Analysis : Analyze / Entire Model / Analysis Deck

b. Select Translation Parameters

c. Data Output : OP2

d. Bulk Data Format Sorted Bulk Data : No Card Format : small

e. OK

Step 13. Create NASTRAN Input File (Contd)

a. Select Solution Type

b. Choose LINEAR STATIC for Solution Type

c. OK

Step 13. Create NASTRAN Input File (Contd)

a. Select Output Requests in Subcases

b. Form Type : Advanced

c. Select STRESS(SORT1, ) in Output Requests

d. OptionsComposite Plate Opt : Ply & Elem. Stresses

e. OK

f. Apply Cancelg. Apply

h. Run NASTRAN

Step 14. Read in OP2 File

a. Analysis : Access Results / Read Output2 / Result Entities

b. Click on Select Results File

c. Select composite.op2

d. OK

e. Apply

Step 15. Results - Deformation

a. Results : Create / Deformation

b. Select Displacements, Translational under Select Deformation Result

c. Apply

Step 16. Results Stress in fiber direction

a. Results : Create / Fringe

b. Select Stress Tensorunder Select Fringe Result

c. Position : Layer 1Quantity : X Component

d. Apply

Step 17. Results Failure Index

a. Results : Create / Fringe

b. Select Failure Indices, Ply Indices under Select Fringe Result

c. Position : Layer 1

d. Apply

Failure criteria was determined when defining the material properties.

Step 17. Results Failure Index (Contd)

a. Results : Create / Fringe

b. Select Failure Indices, Ply Indices under Select Fringe Result

c. Position : Layer 2

d. Apply