第24卷
第9期
2016年9月文章编号
1004-924X(2016)092262-09
光学精密工程
Optics and Precision Engineering
Vol.24No.9
Sept.2016
飞行器折叠翼机构展开性能的优化及实验
韩雪峰，，刘晓东，马伍元，马青，袁东明
（中国科学院长春光学精明机械与物理研究所，吉林长春130033）
摘要：为了优化飞行器折叠翼机构的展开性能，对飞行器的折叠翼机构进行分析，并提出了优化其展开性能的方法。建立了折叠翼机构展开的理论模型和动力学仿真模型，对折叠翼机构展开过程进行了动力学分析，并进行了实例计算。分析了影响折叠翼机构展开性能的因素，用正交试验的方法对折叠翼机构进行了优化设计，得到了最优折叠翼机构方案，并对最优方案进行了伤真分析。最后，按照最优方案折叠翼机构进行了改进，实验测试了折叠翼机构的展开性能。实验测得折叠翼机构展开时间为0.128s，测点位置应力分别为82MPa和92MPa；动力学仿真得到折叠翼机构展开时间为 0.122s，相应测点位置应力分别为85MPa和96MPa,两项测试误差在5%以内。得到的结果表明折叠翼机构满足机翼
展开稳定、快速，应力和冲击力小的要求，为飞行器性能的调高奠定了基础。关键词：飞行器；折叠翼；展开性能；动力学模型；正交试验；结构优化
中图分类号：V224
文献标识码：A
doi;10.3788/OPE.20162409.2262
Optimizationandexperimentsofdeploymentperformance
forfoldingwingmechanismofanaircraft
HAN Xue-feng', LIU Xiao-dong, MA Wu-yuan, MA Qing, YUAN Dong-ming
(ChangchunInstituteofOptics，FineMechanicsandPhysics， ChineseAcademyof Sciences,Changchun130033,China)*Correspondingauthor，E-mail:hanruefeng5210@163.com
Abstract:To optimize thedeploying performance offolding wing mechanism for an aircraft,this paper analyzes the folding wing mechanism and proposes a method to optimize the deploying performance of the mechanism. A theoretical model and a dynamic simulation model for the deployment of folding wing mechanism were established, the deploying processing of folding wing mechanism was analyzed and the folding time of the mechanism was given by using the theoretical model. Then, the effect factor on the deploying performance of the mechanism was analyzed, and the orthogonal trial method was used to optimize those structure parameters to obtain a optimized designed scheme, Finally, the mechanism was simulated and optimized by the optimal scheme and the deploying performance of the mechanism was measured by experiments. Experimental results show that the folding time of the mechanism is 0. 128 s and the structure stresses at the measuring points are 92 MPa and 80 MPa respectively. Moreover the dynamic model test results of the mechanism show that the folding time of the mechanism is 0. 12 s and the structure stresses at the measuring points are 85 MPa and 96 MPa, respectively. The difference of the experimental and simulation results is within 5%. It indicates that the optimal folding wing mechanism promotes the flight performance of the aircraft while the
收稿日期：2016-01-17；修订日期：2016-02-10
基金项目：中国科学院国防科技创新基金资助项目（No.YYYJ-1122)