OS-V: 0520 Sandwich Shell
Test No: R0031/3 OptiStruct examines the z deflection at C, Normal XX stress at C, Normal YY stress at C and Shear stress at E for linear static analysis.
Figure 1. FE Model with Boundary Conditions and Loadcases
Benchmark Model
Quad4 elements are used to create Ply laminates and with SMCORE for the simply supported one quarter model. A uniform normal pressure of 200psi is applied on the plate.
The material properties are:
- Face Sheets
- Ex
- 10.0 × 106 psi
- xy
- 0.3
- Ey
- 4.0 × 106 psi
- Gxy
- 1.875 × 106 psi
- Core
- Ex
- 0.0
- Gxz
- 3.0 × 104 psi
- Gyz
- 1.2 × 104 psi
Linear Static Analysis Results
| Target | OptiStruct Results | Normalized with the Target Value | |
|---|---|---|---|
| Laminated Plate (PCOMPP): | |||
| Z deflection at C (inches) | -0.123 | -0.123 | 1 |
| xx at C | 34449 | 34126.09 | 1.00946226 |
| yy at C | 13390 | 13375.11 | 0.99812263 |
| Τxy at E | -5067.5 | -5080.6 | 0.99742156 |
| SMCORE (PCOMPG): | |||
| Z deflection at C (inches) | -0.123 | -0.078 | 1.57692308 |
| xx at C | 34449 | 32578.56 | 1.05741322 |
| yy at C | 13390 | 14508.05 | 0.9201788 |
| Τxy at E | -5067.5 | -5327.68 | 0.95116448 |
Model Files
Refer to Access the Model Files to download the required model file(s).
The model files used in this problem include:
- compssq4.fem
- compssq4smcore.fem
Reference
NAFEMS R0031 - Composite Benchmarks, Hardy 2001