COMPOSITE STRUCTURESEXAMPLE #4
THERMAL STRESS ANALYSIS OF COMPOSITE LAMINATE
Problem Description
Initial Temp = 130 C, Final Temp = 25 C
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 = 4.5 GPa
11 = -0.5e-6, 22 = 25e-6
x
yz
500 mm
One point fixed
Step 1. Create Geometry & Mesh with CQUAD4 Elements
1010 mesh
Step 2. Create Constraints
a. Loads/BCs : Create / Displacement / Nodal
b. Select on New Set Name and enter displ_1
c. Select Input Data
d. Enter , for Translations and Rotations
e. OK
f. Click on Select Application Region
g. Select FEM for Geometry Filter
h. Select on the centre node
i. Add
j. OK
k. Apply
Step 3. Create Temperature Conditions
a. Loads/BCs : Create / Initial Temperature / Nodal
b. Select on New Set Name and enter ini_temp
c. Select Input Data
d. Enter 130 (C) for Initial Temperaturee. OK
f. Click on Select Application Region
g. Select Geometry for Geometry Filter
h. Pick the Surface or Face icon
i. Select on the surface
j. Add
k. OK
l. Apply
Step 3. Create Temperature Conditions (Contd)
a. Loads/BCs : Create / Temperature / Nodal
b. Select on New Set Name and enter temp
c. Select Input Data
d. Enter 25 (C) for Temperaturee. OK
f. Click on Select Application Region
g. Select Geometry for Geometry Filter
h. Pick the Surface or Face icon
i. Select on the surface
j. Add
k. OK
l. Apply
Step 3. Create Temperature Conditions (Cont.)
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 : 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 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 thermal_analysis.op2
d. OK
e. Apply
Step 12. Results - Deformation
a. Results : Create / Deformation
b. Select Displacements, Translational under Select Deformation Result
c. Apply
Step 13. Results - Stress
a. Results : Create / Fringe
b. Select Stress Tensorunder Select Fringe Result
c. Position : Layer 1Quantity : X Component
d. Apply
.
Step 13. Results Stress (contd)
a. Results : Create / Fringe
b. Select Stress Tensorunder Select Fringe Result
c. Position : Layer 2Quantity : Y Component
d. Apply
Step 14. Results Failure Index
a. Results : Create / Fringe
b. Select Failure Indices, Ply Indices under Select Fringe Result
c. Position : Layer 1
d. Apply
Step 14. Results Failure Index (Contd)
a. Results : Create / Fringe
b. Select Failure Indices, Ply Indices under Select Fringe Result
c. Position : Layer 2
d. Apply
Exercise 1
Initial Temp = 130 C, Final Temp = 25 C One-ply Thickness = 1.0 mm Stacking Sequence = [02]T E11 = 380 GPa, E22 = E33 = 8.2 GPa, 12 = 13 = 0.28, 23 = 0.47,
G12 = G13 = 4.5 GPa, G23 = 4.5 GPa
11= -0.5e-6, 22= 25e-6
x
yz
500 mm
One point fixed
Exercise 2
x
yz
500 mm
clamped
clamped
Initial Temp = 130 C, Final Temp = 25 C One-ply Thickness = 1.0 mm Stacking Sequence = [02]T E11 = 380 GPa, E22 = E33 = 8.2 GPa, 12 = 13 = 0.28, 23 = 0.47,
G12 = G13 = 4.2 GPa, G23 = 4.2 GPa
11= -0.5e-6, 22= 25e-6