北京航空航天大学学报 ›› 2014, Vol. 40 ›› Issue (5): 707-711.doi: 10.13700/j.bh.1001-5965.2013.0364

• 论文 • 上一篇    下一篇

基于响应面法的月球着陆器软着陆性能优化

王家俊, 王春洁, 宋顺广   

  1. 北京航空航天大学 机械工程及自动化学院, 北京 100191
  • 收稿日期:2013-06-25 出版日期:2014-05-20 发布日期:2014-06-04
  • 作者简介:王家俊(1990- ),男,河北定州人,硕士生,wangjiajun@me.buaa.edu.cn.

Performance optimization of lunar lander based on response surface methodology

Wang Jiajun, Wang Chunjie, Song Shunguang   

  1. School of Mechanical Engineering and Automation, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2013-06-25 Online:2014-05-20 Published:2014-06-04

摘要: 为了提高月球着陆器软着陆性能,建立了月球着陆器的多体动力学参数化模型.对某典型恶劣工况进行了优化拉丁超立方实验设计,辨识关键实验因子.利用参数化模型和实验设计获取样本点构造了响应面模型,并检验了响应面的拟合精度.以多个动力学性能作为优化目标,用响应面计算结果构造目标函数和约束条件,对响应面参数做多目标优化.将优化所得参数代入动力学模型中进行仿真,优化效果明显,验证了基于响应面法的软着陆性能优化方法的可行性,为今后的仿真实验提供参考.

Abstract: The parametric model of the lunar lander based on multi-body dynamics was established for improving landing performances of the lunar lander. With the model, an optimal Latin hypercube experimental design for a typical failure case was carried out to find out the key factors. The sample points were acquired by using parametric model and the design of experiments to construct the response surface model, and the response surface fitting accuracy was tested. The calculated response surface results were taken as the objective functions and constraint conditions, and response surface parameters were optimized to improve the comprehensive landing performances. The optimized model was then obtained by substituting the result of the multi-objective optimization into the parametric model. Compared with the previous model, the optimized model has more excellent performance on the typical case. So that the feasibility of optimization method was verified, which can be used for the future simulation experiments.

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