月球着陆器模型参数修正

吴建云; 王春洁; 汪翰

月球着陆器模型参数修正

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:
吴建云(1988-),男,浙江温州人,硕士生,wjy@me.buaa.edu.cn.

中图分类号: V11
计量
- 文章访问数: 1516
- HTML全文浏览量: 179
- PDF下载量: 556
- 被引次数: 0
出版历程
- 收稿日期: 2012-12-19
- 网络出版日期: 2013-10-30

Model parameters updating of lunar lander

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

摘要

摘要: 建立了着陆器的参数化模型,把着陆碰撞过程简化为弹簧阻尼模型,将其中的刚度、阻尼、非线性指数和最大穿透深度作为修正参数;定义了判断着陆器是否翻倒的着陆稳定性平面.基于地面稳定性试验结果,利用ADAMS和Isight软件联合仿真,采用优化拉丁方试验设计缩小修正参数范围.基于模型修正理论,采用自适应模拟退火算法进行模型参数修正,修正效果明显,修正后的仿真模型更符合实际试验样机.
- 月球着陆器 /
- 模型修正 /
- 着陆稳定性 /
- 试验设计 /
- 优化
Abstract: The parametric model of the lander was established, and the landing collision process was simplified as a spring-damper model. Parameters including stiffness, damping, force exponent and the maximum penetration depth were set to be updated. Landing stability plane was defined to determine whether the lander was overturned. Based on the ground stability experimental results, ADAMS and Isight were used to make co-simulation, and optimized super Latin square method was adopted to narrow the range of the updated parameters. Based on the model updating theory, adaptive simulated annealing method was adopted to the model parameters updating. It is proven that the effect of collection is obvious and the updated simulation model conforms better to the actual experimental prototype.
- lunar lander /
- model update /
- landing stability /
- design of experiments /
- optimization

HTML全文

参考文献(1)

[1] 罗松柏,赵永嘉.月球软着陆动力学分析与仿真[J].北京航空航天大学学报,2012,38(2):185-190 Luo Songbai,Zhao Yongjia.Dynamic analysis and simulation of soft-landing for lunar lander[J].Journal of Beijing University of Aeronautics and Astronautics,2012,38(2):185-190(in Chinese) [2] 赵俊锋,刘莉,周思达,等.月球探测器软着陆冲击力学环境研究[J].振动与冲击,2012,31(3):37-42 Zhao Junfeng,Liu Li,Zhou Sida,et al.Dynamic environment research for soft landing for lunar lander[J].Journal of Vibration and Shock,2012,31(3):37-42(in Chinese) [3] Hilderman R A.Landing dynamics of the lunar excursion module[J].Spacecraft,2005,8(3):1484-1489 [4] Doiron H H.Apollo lunar module landing dynamics[R].AIAA-2000-1678,2010 [5] Durling B J,Walton W C Jr.A procedure for computing the motion of a lunar-landing vehicle during the landing impact[R].NASA-TN-D-4216,1967 [6] NASA.Lunar surface models[R].NASA-SP-8023,1969 [7] 王博,吕正勋,何伟.结构动力模型修正方法研究与进展[J].水利与建筑工程学报,2009,7(1):16-19 Wang Bo,Lü Zhengxun,He Wei.Research and progress on updating method for dynamic model of structure[J].Journal of Water Resources and Architectural Engineering,2009,7(1):16-19(in Chinese) [8] 朱宏平,徐斌.结构动力模型修正方法的比较研究及评估[J].力学进展,2002,32(4):512-524 Zhu Hongping,Xu Bin.Comparison and evaluation of structural dynamic model updating methods[J].Advances in Mechanics,2002,32(4):512-524(in Chinese) [9] 曾福明,杨建中,满剑锋,等.月球着陆器着陆缓冲机构设计方法研究[J].航天器工程,2011,20(2):46-51 Zeng Fuming,Yang Jianzhong,Man Jianfeng,et al.Study of design method of landing gear for lunar lander[J].Spacecraft Engineering,2011,20(2):46-51(in Chinese) [10] MSC Corporation.ADAMS/Solver online help version[EB/OL].USA:Santa Ana,2010[2012-12-01].http://simcompanion.mscsoftware.com/infocenter/index?page=home [11] Blancbard Ulysse J.Evaluation of a full-scale lunar-gravity simution by comparison of landing-impact tests of a full-scale and 1/6-scale model[R].NASA-TN-D-4474,1968 [12] 刘晓路,陈英武,荆显荣,等.优化拉丁方试验设计方法及其应用[J].国防科技大学学报,2011,33(5):73-77 Liu Xiaolu,Chen Yingwu,Jing Xianrong,et al.Optimized Latin hypercube sampling method and its application[J].Journal of National University of Defence Technology,2011,33(5):73-77(in Chinese) [13] 朱汪,杨建中.月球着陆器软着陆机构着陆稳定性仿真分析[J].宇航学报,2009,30(5):1792-1795 Zhu Wang,Yang Jianzhong.Touchdown stability siulation of landing gear system for lunar lander[J].Journal of Astronaurtics,2009,30(5):1792-1795(in Chinese)

施引文献

资源附件(0)

访问统计