# 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.

## 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**- E
_{x} - 10.0 × 10
^{6}psi -
$\upsilon $
_{xy} - 0.3
- E
_{y} - 4.0 × 10
^{6}psi - G
_{xy} - 1.875 × 10
^{6}psi

**Core**- E
_{x} - 0.0
- G
_{xz} - 3.0 × 10
^{4}psi - G
_{yz} - 1.2 × 10
^{4}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 |

$\sigma $
_{xx} at C |
34449 | 34126.09 | 1.00946226 |

$\sigma $
_{yy} at C |
13390 | 13375.11 | 0.99812263 |

Τ_{xy} at E |
-5067.5 | -5080.6 | 0.99742156 |

SMCORE (PCOMPG): | |||

Z deflection at C (inches) | -0.123 | -0.078 | 1.57692308 |

$\sigma $
_{xx} at C |
34449 | 32578.56 | 1.05741322 |

$\sigma $
_{yy }at C |
13390 | 14508.05 | 0.9201788 |

Τ_{xy} at E |
-5067.5 | -5327.68 | 0.95116448 |

## Reference

NAFEMS R0031 - Composite Benchmarks, Hardy 2001