example 02(linstatic angle-ply)
DESCRIPTION
analisis de los esfuerzos internos en una lamina compuesta, aplicando el metodo de elementos finitos con el programa patran v2010TRANSCRIPT
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COMPOSITE STRUCTURESEXAMPLE #2
LINEAR ANALYSIS OF A ANGLE-PLYLAMINATE SUBJECTED TO TENSION
Problem Description
P = 10 kN One-ply thickness = 1.0 mm Stacking sequence = [45/-45]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
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Step 1. Modify Material Data for Laminate 1 .
a. Materials : Modify / Composite / Laminate
b. Select laminate in Laminated Comp. To Modify
c. Modify Orientation in Stacking Sequence Definition Orientation : [45/-45] Use Overwrite Option in Text Entry Mode
d. Apply
Step 1. Modify the Material (Cont.)
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Step 2. 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 2. Create NASTRAN Input File (Contd)
a. Select Solution Type
b. Choose LINEAR STATIC for Solution Type
c. OK
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Step 3. 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 4. 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
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Step 5. Results - Deformation
a. Results : Create / Deformation
b. Select Displacements, Translational under Select Deformation Result
c. Apply
Step 6. Results - Stress
a. Results : Create / Fringe
b. Select Stress Tensorunder Select Fringe Result
c. Position : Layer 2Quantity : X Component
d. Apply
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Step 7. Results Failure Index
a. Results : Create / Fringe
b. Select Failure Indices, Ply Indices under Select Fringe Result
c. Position : Layer 1
d. Apply
Step 5. Results Failure Index (Contd)
a. Results : Create / Fringe
b. Select Failure Indices, Ply Indices under Select Fringe Result
c. Position : Layer 2
d. Apply
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Exercise
P = 10 kN 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
free
free
x
yz
P