实现机翼前缘形状连续变化柔性机构的拓扑优化  

Topology Optimization of the Compliant Mechanism for Shape Change of Airfoil Leading Edge

作　　者：黄杰[1] 葛文杰[1] 杨方[1] 

机构地区：[1]西北工业大学机电学院,陕西西安710072

出　　处：《航空学报》2007年第4期988-992,共5页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(50675175)

摘　　要：为了实现自适应机翼表面的连续准确变化和结构轻量化,将分布式柔性机构引入到机翼形状变化结构设计中。基于SIMP密度-刚度插值模型,以实际位移与目标位移之间的偏差最小为目标,建立了实现机翼前缘形状连续变化柔性机构的拓扑优化模型,采用Matlab编程对柔性机构进行了优化设计,并对不同参数变化的影响进行了讨论,最后使用Ansys9.0对其中一个优化结果进行了机构的仿真分析。研究结果表明:该机构可实现机翼前端0～8.14°的变化;不同的体积分数、驱动位置、权重因子将对优化结果产生不同程度的影响,从而证明了用分布式柔性机构实现机翼前缘连续形变的可行性和设计方法的有效性。Distributed compliant mechanisms were introduced into the research on compliant airfoil to achieve the shape change of the leading edge and to decrease the weight. A compliant mechanism topology optimization model was presented, which was based on the solid isotropic material with peualization （SIMP） modal, to try to minimize the deviation between the deformed and target shapes. At last a Matlab program was developed to achieve the topology optimizations of the compliant mechanisms, one of which was reconstructed and analyzed in Ansys9.0 too. The influence caused by the volume fraction, the place of actuator and the weight factors were studied in detail. The results show that the mechanism can make the leading edge change about 0-8.14°, which proves the possibility of the method in this paper.

关 键 词：自适应机翼 柔性机构 拓扑优化 多目标优化 优化准则法 

分 类 号：TH163[机械工程—机械制造及自动化]