Example 1 Patran

COMPOSITE STRUCTURESEXAMPLE #3

LINEAR ANALYSIS OF A SYMMETRIC ANGLE-PLY LAMINATE

UNDER LATERAL PRESSURE

Problem Description

p = 0.1 MPa One-ply thickness = 0.5 mm Stacking sequence = [45/-45]S E11 = 380 GPa, E22 = E33 = 8.2 GPa, 12 =13 = 0.28, 23 = 0.47,

G12 = G13 = 4.5 GPa, G23 = 4.5 GPa

500 mm

SS

SS

SS

SS

x

yz

Step 1. Create Geometry & Mesh with CQUAD4 Elements

126 mesh

Step 2. 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

e. OK

f. Click on Select Application Region

g. Select Geometry for Geometry Filter

h. Pick the Curve and Edge icon

i. Select all free edges(Using Shift Key)

j. Add

k. OK

l. Apply

Step 3. Create Lateral Pressure

a. Loads/BCs : Create / Pressure / Element Uniform

b. Select on New Set Name and enter pressure

c. Target Element Type : 2D

d. Select Input Data

e. Enter 0.1 (MPa) for Top Surf Pressure

f. OK

g. Click on Select Application Region

h. Select Geometry for Geometry Filter

i. Pick the Surface or Face icon

j. Select on the surface

k. Add

l. OK

m. Apply

Step 3. Create Lateral Pressure (Contd)

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

Step 4. 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 5. 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 6. Define Laminate PCOMP

a. Materials : Create / Composite / Laminate

b. Select prepreg in Existing Materials two times

c. Stacking Sequence Convention : Symmetric

d. Fill in Stacking Sequence Definition Thickness : 0.5 mm Orientation : [45/-45]S

e. Select on New Material Nameand enter laminate

f. Apply

Step 7. Check [A], [B], and [D] Matrices

Step 8. 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 Region and pick to include all geometry as shown in the figure

h. Add

i. Apply

Step 9. 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 10. 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 10. Create NASTRAN Input File (Contd)

a. Select Solution Type

b. Choose LINEAR STATIC for Solution Type

c. OK

Step 10. 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

Step 11. 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 9. Results - Deformation

a. Results : Create / Deformation

b. Select Displacements, Translational under Select Deformation Result

c. Apply

Step 9. Results Deformation (Contd)

.

Deflection Fringe

Step 10. Results Stress

a. Results : Create / Fringe

b. Select Stress Tensorunder Select Fringe Result

c. Position : Layer 1Quantity : X Component

d. Apply

Step 10. Results Stress (Contd)




d. Apply





d. Apply





d. Apply

Step 11. Results Failure Index


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

c. Position : Layer 1

d. Apply

Step 11. Results Failure Index (Contd)




d. Apply





d. Apply





d. Apply

Example 1 Patran

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