月球着陆器结构设计技术及仿真分析
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摘要
月球是地球的卫星,有着得天独厚的地理优势、丰富的资源和极高的利用价值。近年来,国际上再次出现月球探测的新高潮。以月球为主的深空探测也是我国航天事业近期重点发展的方向之一。2009年3月1日,“嫦娥一号”卫星成功撞击月球,标志着我国探月一期工程的顺利完成,我国的探月活动进入了二期工程:月球软着陆探测和自动巡视勘察。
着陆器主结构和软着陆机构的设计是月球软着陆探测的基础,而结构力学分析是着陆器主结构和软着陆机构设计的重要手段和工具。本文基于月球软着陆器的探测任务和飞行程序,根据着陆器主结构和软着陆机构设计的一般原则、要求和过程,进行了着陆器主结构和软着陆机构的设计和分析。
本文首先根据设计要求给出了月球着陆器主结构和软着陆机构的设计方案,在此基础上,在有限元软件MSC.Patran对着陆器整体结构进行合理的简化,并建立相应的有限元模型。然后,利用有限元软件对着陆器整体进行结构静力分析、模态分析和频率响应分析,其中静力分析考虑的是着陆过程中的最大过载时刻,模态分析和频率响应分析考虑的是发射过程(着陆器被放置在运载火箭整流罩内部)。分析结果表明,所设计着陆器满足着陆器在工作过程中的强度和刚度要求。最后,介绍了月球表面主要的环境特征以及相应的模拟方法,研究了其在月球着陆器着陆冲击试验中的应用以及具体的试验方案。本文研究结果对月球着陆器设计具有一定的借鉴意义。
Lunar, the natural satellite of the earth, has been a focus of the space discovey again recently because of its abundant resource and high value in use. Lunar exploration is also one of the most important projects in china. March 1, 2009,“Chang’e 1”satellite impacted on the moon under control, which marks the first phase of China’s lunar exploration project completed successfully, and the exploration activities is going to the second phase: the soft lunar landing and auto surface survey.
The design of the lunar lander and the soft landing system is the basic of the lunar exploration, while the structure dynamic analysis is an importment approach for the designes. Based on the mission and flight procedure of the lunar lander, the constructions of the lunar vehicle and the soft landing system have been designed and analyzed in accordance with the general principles, requirements and process of design on lunar lander.
At first, the detailed designs of the structures of the lunar vehicle and soft landing system have been given in accordance with the design requirement. Founded on the structure designed, the entire model of the lunar lander has been simplified reasonably, and the corresponding finite element model has been built in the software MSC.Patran. Then static analysis, modal analysis and frequency response analysis have been calculated in the software, in which the static analysis has been taken into the landing process, while the modal analysis and the frequency response analysis have been taken into the launch process (The landing gear has been placed in the fairing interior of the rocket.). The results of the calculations show that the designed structures of the lunar vehicle and soft landing system meet the strength and stiffness requirements at the course of work. Finally, the major environment features of the lunar surface and the corresponding simulation methods have been decribed. Then the applications of these methods in the landing impact tests of the lunar lander and the specific pilot programs have been given. The result of the study has actual guidance on structure design of lunar lander.
着陆器主结构和软着陆机构的设计是月球软着陆探测的基础,而结构力学分析是着陆器主结构和软着陆机构设计的重要手段和工具。本文基于月球软着陆器的探测任务和飞行程序,根据着陆器主结构和软着陆机构设计的一般原则、要求和过程,进行了着陆器主结构和软着陆机构的设计和分析。
本文首先根据设计要求给出了月球着陆器主结构和软着陆机构的设计方案,在此基础上,在有限元软件MSC.Patran对着陆器整体结构进行合理的简化,并建立相应的有限元模型。然后,利用有限元软件对着陆器整体进行结构静力分析、模态分析和频率响应分析,其中静力分析考虑的是着陆过程中的最大过载时刻,模态分析和频率响应分析考虑的是发射过程(着陆器被放置在运载火箭整流罩内部)。分析结果表明,所设计着陆器满足着陆器在工作过程中的强度和刚度要求。最后,介绍了月球表面主要的环境特征以及相应的模拟方法,研究了其在月球着陆器着陆冲击试验中的应用以及具体的试验方案。本文研究结果对月球着陆器设计具有一定的借鉴意义。
Lunar, the natural satellite of the earth, has been a focus of the space discovey again recently because of its abundant resource and high value in use. Lunar exploration is also one of the most important projects in china. March 1, 2009,“Chang’e 1”satellite impacted on the moon under control, which marks the first phase of China’s lunar exploration project completed successfully, and the exploration activities is going to the second phase: the soft lunar landing and auto surface survey.
The design of the lunar lander and the soft landing system is the basic of the lunar exploration, while the structure dynamic analysis is an importment approach for the designes. Based on the mission and flight procedure of the lunar lander, the constructions of the lunar vehicle and the soft landing system have been designed and analyzed in accordance with the general principles, requirements and process of design on lunar lander.
At first, the detailed designs of the structures of the lunar vehicle and soft landing system have been given in accordance with the design requirement. Founded on the structure designed, the entire model of the lunar lander has been simplified reasonably, and the corresponding finite element model has been built in the software MSC.Patran. Then static analysis, modal analysis and frequency response analysis have been calculated in the software, in which the static analysis has been taken into the landing process, while the modal analysis and the frequency response analysis have been taken into the launch process (The landing gear has been placed in the fairing interior of the rocket.). The results of the calculations show that the designed structures of the lunar vehicle and soft landing system meet the strength and stiffness requirements at the course of work. Finally, the major environment features of the lunar surface and the corresponding simulation methods have been decribed. Then the applications of these methods in the landing impact tests of the lunar lander and the specific pilot programs have been given. The result of the study has actual guidance on structure design of lunar lander.
引文
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[42]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: 32～52.
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[2] Foing B H.The moon as a platform for astronomy and space science [J].Adv.Space Res,1996,18(11): 17～23.
[3] Bruns J O, Mendell W W. Future astronomical observatories on the moon [R].NASA-CP-2489,1989.
[4] Shkuratov Y G, Kaydash, Nickolaj V. Iron and titanium abundance and maturity degree distribution on the lunar nearside[J]. Icarus, 1999, 137(2): 222～234.
[5]李大耀.论月球资源和航天月球探测[J].航天返回与遥感,2004,25(1) : 60～63.
[6]邹永廖,欧阳自远,徐琳,等.月球表面的环境特征[J].第四纪研究,2002,22(2) : 533～538.
[7]陈金宝.月球探测器软着陆缓冲机构设计及关键技术研究[D].南京:南京航空航天大学,2007.
[8]殷礼明.中国深空探测器技术的发展与展望[J].中国航天,2003,(2): 39～43.
[9]陈忠贵,张云彤,潘屹.世界各国月球探测发展概况及我国实施步骤探讨[J].航天器工程,2003,12(2) : 74～81.
[10]褚桂柏.月球探测器技术[M].北京:中国科学技术出版社,2007: 2～13.
[11]邓连印,崔乃刚.月球探测发展历程及启示[J].哈尔滨工业大学学报, 2008, 10(3) : 14～19.
[12]叶培建,邓湘金,彭兢.国外深空探测态势特点及启示[J].航天器环境工程,2008,25(6): 501～511.
[13]何绍.探月之路[J].探月特刊,2007,(11):82～86.
[14] Toshih Ikomisu, Tatsuakha Shmto. Optical guidance for Autonomous landing of spacecraft[J].IEEE Transaction on Aerospace and Electronic systes, 1999, 459～473.
[15] Binder A B.Lunar prospector overview[J] .Science ,1998,(281) : 1475～1476.
[16]天兵.全球掀起探月新高潮[J].国际太空,2002,(3): 8～11.
[17]王闯,邓宗全,高海波,等.国内外月球着陆器研究状况[J].导弹与航天运载技术,2006,(4) :31～36.
[18] William F R. Apollo experience report-Lunar module landing gear subsystem[R]. NASA TN D-6850.
[19] Gromov V. Physical and mechanical properties of lunar and planetary soils[J]. Earth,Moonand Planets,1998,(80) : 51~72.
[20] David W C. Lunar soil grain size distribution [J].The Moon, 1973, (6): 250～263.
[21]邓永春,欧阳自远,王世杰,等.月壤的物理和机械性能[J].矿物岩石,2004,24(4) : 14～19.
[22] Fan Shichao, Feng Yaoqi. The experimental facility for lunar rover development[J].Spacecraft environment engineering,2007,24(2): 85～87.
[23]樊世超,贾阳,向树红,等.月面地形地貌环境模拟初步研究[J].航天器环境工程,2007,24(1): 15～20.
[24] Victor L V, Emilio A B. Impact dynamics research facility for full-scale aircraft crash testing[R].NASA TN D-8179, 1976.
[25] Karen E J, Edwin L F.A survey of research performed at NASA Langley research center’s impact dynamic research facility[R].AIAA 2003-1896, 2003.
[26]王少纯,邓宗权,胡明,等.一种模拟月球着陆器低重力场着陆试验方法[J].上海交通大学学报,2005,39(6) : 989-992.
[27]Peng Jing, Liu Zhongyao, Zhang He. Conceptual Design of A Lunar Lander[J]. Spacecraft engineering,2008,17(1) : 18～23.
[28]陈昌亚,邓晓亚,姜普庆.卫星结构优化设计的建模问题[J].机械科学与技术,2005,24(1) : 66～69.
[29]王薇.“TXZ”微小卫星结构优化设计与分析[D].南京:南京航空航天大学,2008.
[30]杨建中,曾福明.月球探测器软着陆机构综述[C].宇航学会深空探测专业技术年会,2004.
[31]曾福明,杨建中.月球及行星探测器软着陆缓冲器技术综述[C].宇航学会深空探测专业技术年会,2004.
[32]刘志全,黄传平.月球探测器软着陆机构发展综述[J].中国空间科学技术,2006,(1): 33～39.
[33]Taylor I. Investigation of the application of airbag to provide softlanding[R].AIAA 2001-2045, 2001.
[34]Sperling F B. The surveyor shock absorber[R]. AIAA N50-17368, 1964.
[35]Miltom B. Surueyor lander mission capability[R]. NASA N64-28969, 1964.
[36]陈金宝,聂宏,汪岸柳,等.月球软着陆系统关键技术研究与发展综述[J].中国机械工程,2006,(2): 426～428.
[37]陈金宝,聂宏,柏合民.月球探测器软着陆缓冲装置研究[C].中国宇航学会年会论文,2006.
[38]赵汝嘉.机械结构有限元分析[M].西安:西安交通大学出版社,1990: 1～4.
[39]C.T.F.鲁斯.结构力学的有限元法(吴德心,谢仁物,严京敏,等).北京:人民交通出版社,1991: 8～12.
[40]朱闯峰.飞机起落架静强度虚拟实验技术研究[D].南京:南京航空航天大学,2008.
[41]王春洁,郭永.着陆器软着陆机构的动力学分析[J].北京航空航天大学学报,2009,35(2): 183～187.
[42]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: 32～52.
[43]Herr R W, Lconard H W. Dynamic model investigation of touchdown stability of lunar landing vehicles[R]. NASA TN D-4215, 1967.
[44]中国航空研究院编.复合材料结构稳定性分析指南[M].北京:航空工业出版社,2002.
[45]沃西源,夏英伟,涂彬.蜂窝夹层结构复合材料特性及破坏模式分析[J].航天返回及遥感,2005,26(4): 45～49.
[46]中国航空研究院编.复合材料结构设计手册[M].北京:航空工业出版社,2001.
[47]刘焕焕.多腿式月球探测软着陆器着陆动力学建模与仿真研究[D].南昌:南昌大学,2008.
[48]Jan T B. Extended modal analysis based on state-space model reveals new information [R]. AIAA-97-0942, 1997.
[49]Mayuresh J P. Decoupled second-order equations and modal analysis of a general nonconservative system [R]. AIAA-2000-1654, 2000.
[50]Aranda J, Crespo J. Modal analysis applied to spacecraft attitude control [R]. AAIA-2007-6444, 2007.
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