基于柔性机构的机翼前缘变形多目标优化  

Exploring Further Multi-Objective Optimization for Shape Change of Aircraft Leading Edge Using Compliant Mechanisms

作　　者：葛文杰[1] 朱鹏刚[1] 刘世丽[1] 张永红[1] 

机构地区：[1]西北工业大学机电学院,陕西西安710072

出　　处：《西北工业大学学报》2010年第2期211-217,共7页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(50675175)资助

摘　　要：全柔性机构用于自适应机翼具有实现其形状的连续平滑变形和轻量化等优点。文章根据机翼前缘在不同飞行状态下气动外形要求,以离散体结构拓扑优化为出发点,以目标形状与实际形状的边界曲线之差最小为优化目标,并考虑机构变形要求和刚性要求等问题,建立了多目标优化函数;采用遗传算法(GA)和双向渐进结构优化法(BESO)相结合,应用于Matlab与Ansys,通过二次优化,获得了稳定的最优解,不仅实现编程模块化,而且提高了优化效率。最后,对结果进行Ansys仿真分析和模型实验验证。结果表明:仿真结果和模型实验结果一致,该方法是可行的。Aim.The introduction of the full paper reviews past research,including particularly Refs.2,4,7,8 and 9;Refs.7,8 and 9 present the results of NWPU researchers′ past exploration;the last paragraph of the introduction points out how this paper differs from Refs.7,8 and 9.Section 1 explains the method of this paper;its core consists of：（1） it,starting from topological optimization of discrete structure with the optimization target of the least difference of the boundary curve between target shape and actual shape,establishes multi-objective optimization functions considering the problems of mechanisms deformation and rigidity request;（2） it adopts GA and BESO algorithm to MATLAB and ANSYS and gets the stable optimal solution through quadratic optimization,which can not only realize programming modularization but also improve the optimization efficiency.Section 2 applies our method to the numerical example taken from Ref.11 authored by Kerr-Jia Lu and Sridhar Kota.The application of our method to this numerical example gives the results presented in Tables 1 and 2 and Figs.6,7 and 8;in addition,the last paragraph of section 2 presents model experiment tests performed by us.All the above-mentioned results,including the model experiment tests,show preliminarily that our method is feasible.

关 键 词：变形柔性机翼 拓扑优化 遗传算法 全柔性机构 BESO 

分 类 号：V224[航空宇航科学与技术—飞行器设计]