Optimization and experiments of deployment performance for folding wing mechanism of an aircraft

Xue-feng HAN; Xiao-dong LIU; Wu-yuan MA; Qing MA; Dong-ming YUAN

doi:10.3788/OPE.20162409.2262

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Optimization and experiments of deployment performance for folding wing mechanism of an aircraft

Micro/Nano Technology and Fine Mechanics | 更新时间：2020-07-07

- Optimization and experiments of deployment performance for folding wing mechanism of an aircraft
- Optics and Precision Engineering Vol. 24, Issue 9, Pages: 2262-2270(2016)
- 作者机构：
  
  中国科学院长春光学精明机械与物理研究所, 吉林长春 130033
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20162409.2262
  CLC： V224
- Received：17 January 2016，
  
  Accepted：10 February 2016，
  
  Published：2016-09
- 稿件说明：
移动端阅览
Xue-feng HAN, Xiao-dong LIU, Wu-yuan MA, et al. Optimization and experiments of deployment performance for folding wing mechanism of an aircraft[J]. Optics and precision engineering, 2016, 24(9): 2262-2270.
DOI：

Xue-feng HAN, Xiao-dong LIU, Wu-yuan MA, et al. Optimization and experiments of deployment performance for folding wing mechanism of an aircraft[J]. Optics and precision engineering, 2016, 24(9): 2262-2270. DOI： 10.3788/OPE.20162409.2262.

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仿真分析。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0.128 s，测点位置应力分别为82 MPa和92 MPa；动力学仿真得到折叠翼机构展开时间为0.122 s，相应测点位置应力分别为85 MPa和96 MPa，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。

Abstract

To optimize the deploying performance of folding 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 mechanism also basically satisfies the design requirements like the stability

reliability

fast speed

small stress and the impact force.

关键词

Keywords

references

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