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�������պ����ѧѧ�� 2010, Vol. 36 Issue (11) :1348-1352    DOI:
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1. �������պ����ѧ������ʵ������ϵͳ�����ص�ʵ����, ���� 100191;
2. �й��ռ似���о�Ժ���岿, ���� 100094
Dynamic analysis for lunar lander based on rigid-flexible coupled model
Lu Yuntong1, Song Shunguang1, Wang Chunjie1, Zeng Fuming2*
1. State Key Laboratory of Virtual Reality Technology and Systems, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. Beijing Institute of Spacecraft System Engineering, Beijing 100094, China

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Abstract�� Based on the rigid-flexible coupled multibody dynamics theory, an analysis method involved three-dimensional solid modelling, finite element analysis and multi-body system dynamics analysis was proposed. With such a method, the landing dynamics model for a lunar lander was established and used to analyze the landing performance for a typical touchdown case in both Earth-s gravity and Lunar-s gravity (1/6 Earth-s gravity) environments. The results include the max strut stroke in both the primary struts and secondary structs, the lunar lander mass center-s max acceleration. The analysis results were contrasted with those from the shock testing, showing that the rigid-flexible coupled dynamics model has been correctly built and the analysis method is valid and efficient. The model and method developed can then be used for future evaluating the landing performance of the lunar lander. The landing performance of the dynamics model was analyzed in energy prospect, making up shortage of shock testing’s failure of doing energy prospect.
Keywords�� lunar lander   rigid-flexible coupled model   dynamic analysis   shock testing     
Received 2009-10-27;
Fund:

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Corresponding Authors: ����ͨ     Email: yuntonglu@126.com
About author: ����ͨ(1985-),��,�ӱ��ȷ���,˶ʿ��,yuntonglu@126.com.
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����ͨ, ��˳��, ������, ������.���ڸ������ģ�͵�������½������ѧ����[J]  �������պ����ѧѧ��, 2010,V36(11): 1348-1352
Lu Yuntong, Song Shunguang, Wang Chunjie, Zeng Fuming.Dynamic analysis for lunar lander based on rigid-flexible coupled model[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2010,V36(11): 1348-1352
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