Hierarchical Optimization of Landing Performance for Lander with Adaptive Landing Gear

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英文篇名：Hierarchical Optimization of Landing Performance for Lander with Adaptive Landing Gear 作者：Zongmao ; Ding ; Hongyu ; Wu ; Chunjie ; Wang ; Jianzhong ; Ding 英文作者：Zongmao Ding;Hongyu Wu;Chunjie Wang;Jianzhong Ding;School of Mechanical Engineering and Automation, Beijing University of Aeronautics and Astronautics;Beijing System Design Institute of Electro?Mechanic Engineering, China Aerospace Science and Industry Corporation Limited;Department of Mechanical Engineering, Tsinghua University;State Key Laboratory of Virtual Reality and Systems, Beijing University of Aeronautics and Astronautics; 英文关键词：Landing gear;;Soft landing;;Sensitivity analysis;;Response surfaces;;Hierarchical optimization 中文刊名：YJXB 英文刊名：中国机械工程学报(英文版) 机构：School of Mechanical Engineering and Automation, Beijing University of Aeronautics and Astronautics;Beijing System Design Institute of Electro-Mechanic Engineering, China Aerospace Science and Industry Corporation Limited;Department of Mechanical Engineering, Tsinghua University;State Key Laboratory of Virtual Reality and Systems, Beijing University of Aeronautics and Astronautics; 出版日期：2019-04-15 出版单位：Chinese Journal of Mechanical Engineering 年：2019 期：v.32 基金：Supported by National Natural Science Foundation of China(Grant No.51635002) 语种：英文; 页：YJXB201902002 页数：12 CN：02 ISSN：11-2737/TH 分类号：24-35

摘要

A parameterized dynamics analysis model of legged lander with adaptive landing gear was established. Based on the analysis model, the landing performances under various landing conditions were analyzed by the optimized Latin hypercube experimental design method. In order to improve the landing performances, a hierarchical optimization method was proposed considering the uncertainty of landing conditions. The optimization problem was divided into a higher level(hereafter the "leader") and several lower levels(hereafter the "follower"). The followers took condition?ing factors as design variables to find out the worst landing conditions, while the leader took bu er parameters as design variables to better the landing performance under worst conditions. First of all, sensitivity analysis of landing conditioning factors was carried out according to the results of experimental design. After the sensitive factors were screened out, the response surface models were established to reflect the complicated relationships between sensi?tive conditioning factors, bu er parameters and landing performance indexes. Finally, the response surface model was used for hierarchical optimization iteration to improve the computational e ciency. After selecting the optimum bu er parameters from the solution set, the dynamic model with the optimum parameters was simulated again under the same landing conditions as the simulation before. After optimization, nozzle performance against damage is improved by 5.24%, the acceleration overload is reduced by 5.74%, and the primary strut improves its performance by 21.10%.
        A parameterized dynamics analysis model of legged lander with adaptive landing gear was established. Based on the analysis model, the landing performances under various landing conditions were analyzed by the optimized Latin hypercube experimental design method. In order to improve the landing performances, a hierarchical optimization method was proposed considering the uncertainty of landing conditions. The optimization problem was divided into a higher level(hereafter the "leader") and several lower levels(hereafter the "follower"). The followers took condition?ing factors as design variables to find out the worst landing conditions, while the leader took bu er parameters as design variables to better the landing performance under worst conditions. First of all, sensitivity analysis of landing conditioning factors was carried out according to the results of experimental design. After the sensitive factors were screened out, the response surface models were established to reflect the complicated relationships between sensi?tive conditioning factors, bu er parameters and landing performance indexes. Finally, the response surface model was used for hierarchical optimization iteration to improve the computational e ciency. After selecting the optimum bu er parameters from the solution set, the dynamic model with the optimum parameters was simulated again under the same landing conditions as the simulation before. After optimization, nozzle performance against damage is improved by 5.24%, the acceleration overload is reduced by 5.74%, and the primary strut improves its performance by 21.10%.

引文

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