摘要
为缩短研制周期,减少设计中的反复,提高设计质量,舱段的结构设计需要进行优化。探索一种解决复杂舱段结构设计的渐进优化设计方法。首先进行拓扑优化,根据拓扑优化结果设计方案;再进行静、动力学特性分析;而后对设计结构要素进行参数优化;最后进行试验验证。通过一个复杂舱段的结构设计与优化,验证方法的有效性。
An optimization of system design is needed to shorten the development time, reduce the reiteration, and improve the design level. A gradual optimization approach is proposed to design complex structure cabins. Firstly, a topology optimization is done, and a structure draft is made based on the result of topology optimization. Secondly, the static and dynamic structural analysis is performed in MD Nastran. Thirdly, a parameter optimization about the original structure is conducted. Lastly, the test is prerequisite. The method is validated by a complex cabin structure design and optimization..
出处
《导弹与航天运载技术》
北大核心
2013年第1期6-10,共5页
Missiles and Space Vehicles
关键词
拓扑优化
有限元分析
参数优化
Topology Optimization
FEM Analysis
Parameter Optimization
