着陆器软着陆机构的动力学分析

王春洁; 郭 永

着陆器软着陆机构的动力学分析

王春洁,
郭永

北京航空航天大学机械工程及自动化学院, 北京 100191

详细信息

作者简介:
王春洁(1955-),女,辽宁锦州人,教授,wangcj@buaa.edu.cn.

中图分类号: V 414
计量
- 文章访问数: 2907
- HTML全文浏览量: 70
- PDF下载量: 1337
- 被引次数: 0
出版历程
- 收稿日期: 2008-07-20
- 网络出版日期: 2009-02-28

Dynamic analysis of lunar lander

School of Mechanical Engineering and Automation, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 以某型号着陆器软着陆机构为研究对象,采用MSC.Patran/Nastran 对软着陆机构进行模态分析,得到结构模态的主要影响因素,主要包括机构尺寸和装配连接方式.主要分析了软着陆机构中主支柱、辅助支柱活塞杆和活塞筒壁厚、以及活塞筒端盖厚度对模态频率的影响,并对主支柱、辅助支柱活塞杆和活塞筒装配连接方式进行研究,接着提出一种基于Bush单元的装配连接方式,有效地解决了传统方法中用MPC(Multiple Point Constraint)刚性连接来模拟装配连接的不足,使仿真结果更加准确.最后对收拢状态下的模型进行了频率响应分析,结果发现在给定的频率范围内结构不会发生共振,进一步说明结构设计的合理性.
- 着陆器软着陆机构 /
- MPC刚性连接 /
- Bush单元连接 /
- 频响分析
Abstract: By the modal analysis of lunar lander based on MSC.Patran/Nastran, the main factors affecting the mode frequency were retrieved, including the dimensions of the machine and the method of the assembled part. The influence brought about by modifying the thickness of the piston barrel and piston rod on the mode frequency was illustrated. Meanwhile, the connection method of the assembled part was also studied. Subsequently a new approach based on Bush was proposed to solve the problems encountered by using MPC(multiple point constraint), which makes the simulated results more accurate. Finally, frequency analysis on the stow model of the lunar lander was implemented, whose result shows the structure can not resonated in the specified range of excitation, which further validates the reliability of the lunar lander.
- lunar lander /
- MPC rigid connection /
- Bush element connection /
- frequency analysis

HTML全文

参考文献(1)

[1] 邓宗全,王闯,刘荣强,等. 空间桁架式着陆器的动力学分析[J]. 振动与冲击,2007,26(10):169-170 Deng Zongquan, Wang Chuang, Liu Rongqiang,et al. Dynamic analysis of spatial trussed luna lander[J].Journal of Vibration and Shock, 2007,26(10):169-170(in Chinese) [2] 张永昌.MSC.Nastran有限元分析理论基础与应用[M]. 北京: 科学出版社,2004 Zhang Yongchang.Application and fundamental theory of finite element[M].Beijing: Science Press,2004(in Chinese) [3] 隋允康, 杜家政,彭细荣. MSC.NASTRAN有限元分析与优化设计实用教程[M]. 北京: 科学出版社,2004 Sui Yunkang, Du Jiazheng,Peng Xirong.Finite element analysis and optimization based on MSC.NASTRAN[M]. Beijing: Science Press,2004(in Chinese) [4] 邓宗全,王闯,高海波,等.国内外月球着陆器研究现状[J].导弹与航天运载技术, 2006(4):33-34 Deng Zongquan, Wang Chuang, Gao Haibo, et al.The research situation of lunar lander[J]. Missles and Space Vehicles, 2006(4):33-34(in Chinese) [5] Herr Roberrt W, Lconard H Waync. Dynamic model investigation of touchdown stability of lunar landing vehicles .NASA TN D-4215, 1967 [6] Ulysses Blancha. Full-scale dynamic investigation of a prototype lunar module . TN D-5029 1-41, 1919 [7] 赵猛,张以都,马良文,等．基于MSC的装结构模态分析技术研究[J].机械科学与技术,2003,26(3):103-104 Zhao Meng, Zhang Yidu, Ma Liangwen, et al. Research on modal analysis of assembly structures based on MSC Nastran[J].Mechanical Science and Technology, 2003,26(3):103-104(in Chinese) [8] 杨剑,张璞,陈火红．新编MD Nastran有限元实例教程[M]．北京:机械工业出版社,2007 Yang Jian,Zhang Pu,Chen Huohong. New edition of finite element analysis based on MD Nastran[M]. Beijing: China Machine Press,2007(in Chinese) [9] 杨洪波．空间遥感器动力学环境计算机仿真[J].光学精密工程,1998,6(6):39-42 Yang Hongbo.Dynamic environment simulation of space remote sensor [J].Optics and Precision Engineering,1998,6(6):39-42(in Chinese)

施引文献

资源附件(0)

访问统计