Optimal Design of Compliant Trailing Edge for Shape Changing
Adaptive wings have long used smooth morphing technique of compliant leading and trailing edge to improve their aerodynamic characteristics. This paper introduces a systematic approach to design compliant structures to carry out required shape changes under distributed pressure loads. In order to minimize the deviation of the deformed shape from the target shape, this method uses MATLAB and ANSYS to optimize the distributed compliant mechanisms by way of the ground approach and genetic algorithm (GA) to remove the elements possessive of very low stresses. In the optimization process, many factors should be considered such as airloads, input dis- placements, and geometric nonlinearities. Direct search method is used to locally optimize the dimension and input displacement after the GA optimization. The resultant structure could make its shape change from 0 to 9.3 degrees. The experimental data of the model confirms the feasibility of this approach.
作 者： Liu Shili Ge Wenjie Li Shujun 作者单位： School of Mechatronics, Northwestern Polytechnical University, Xi'an 710072, China 刊 名： 中国航空学报（英文版） ISTIC 英文刊名： CHINESE JOURNAL OF AERONAUTICS 年，卷(期)： 2008 21(2) 分类号： V2 关键词： adaptive wing compliant mechanism genetic algorithm topology optimization distributed pressure load geometric nonlin-earity