Abstract
A simple method was presented by means of FE software to fix on the location of stiffness-center axis of a high-ratio-aspect composite wing model. The most difference was 7.5%, comparing the results of FE method with that of theoretical method. It was applied to an example of engineering. The optimal design was carried out with the location of stiffness-center axis of a composite wing as objective function and static strength and stability as constraints. The design variables were the lay-up thickness of panel and spar web, and the cross-section area of stringer and spar edge. Through the iterative calculation by multi-island genetic algorithm and sequential quadratic programming, the optimized location of stiffness-center axis of composite wing model was obtained finally. Compared with that optimized before, the location of stiffness-center axis is closer to leading edge of the wing.
| Original language | English |
|---|---|
| Pages (from-to) | 52-55 |
| Number of pages | 4 |
| Journal | Zhongguo Jixie Gongcheng/China Mechanical Engineering |
| Volume | 24 |
| Issue number | 1 |
| DOIs | |
| State | Published - 10 Jan 2013 |
Keywords
- Finite element(FE) method
- Multi-island genetic algorithm
- Optimization design
- Sequential quadratic programming
- Stiffness center axis
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