Hierarchical Optimization of Landing Performance for Lander with Adaptive Landing Gear

Chinese Journal of Mechanical Engineering

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[1] 0000 0000 9999 1211, grid.64939.31, School of Mechanical Engineering and Automation, Beijing University of Aeronautics and Astronautics, 100083, Beijing, China;0000 0000 9999 1211, grid.64939.31, School of Mechanical Engineering and Automation, Beijing University of Aeronautics and Astronautics, 100083, Beijing, China;0000 0000 9999 1211, grid.64939.31, State Key Laboratory of Virtual Reality and Systems, Beijing University of Aeronautics and Astronautics, 100083, Beijing, China;0000 0000 9999 1211, grid.64939.31, School of Mechanical Engineering and Automation, Beijing University of Aeronautics and Astronautics, 100083, Beijing, China;0000 0001 0662 3178, grid.12527.33, Department of Mechanical Engineering, Tsinghua University, 100084, Beijing, China;0000 0000 9999 1211, grid.64939.31, School of Mechanical Engineering and Automation, Beijing University of Aeronautics and Astronautics, 100083, Beijing, China;0000 0004 0508 5971, grid.495325.c, Beijing System Design Institute of Electro-Mechanic Engineering, China Aerospace Science and Industry Corporation Limited, 100854, Beijing, China;

关键词: Landing gear;    Soft landing;    Sensitivity analysis;    Response surfaces;    Hierarchical optimization;   

DOI  :  10.1186/s10033-019-0331-0

来源: publisher

【 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 conditioning factors as design variables to find out the worst landing conditions, while the leader took buffer 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 sensitive conditioning factors, buffer parameters and landing performance indexes. Finally, the response surface model was used for hierarchical optimization iteration to improve the computational efficiency. After selecting the optimum buffer 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%.

【 授权许可】

CC BY