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
Model Files
Before you begin, copy the file(s) used in this problem
to your working directory.
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 200 psi 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 |
Reference
NAFEMS R0031 - Composite Benchmarks, Hardy 2001