月球探测器软着陆动力学及影响因素分析
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摘要
为准确预估探测器着陆冲击过程的动力学响应,采用非线性有限元方法建立了探测器软着陆动力学模型,全面考虑了各种非线性因素的影响。为保证仿真精度,提高计算效率,提出了一种缓冲腿的简化模型并采用隐式算法求解系统动力学方程。通过与试验数据的对比证明了简化模型及计算方法的有效性。在此基础上,分析了具有不同阻尼和不同刚度的着陆器中心体对有效载荷冲击响应的影响,并针对刚度的影响给出了理论解释。研究结果表明阻尼可以很好地缓冲有效载荷的加速度响应,而中心体刚度大小与有效载荷的加速度响应峰值呈负相关。研究结果对探测器的动力学分析与设计提供了一定的理论依据和技术支持。
The soft landing impact performance of lunar lander has a bearing on the success of moon mission. In order to accurately predict the dynamics response of a lunar lander during the landing process,the flexible model of the lunar lander is built by using nonlinear finite element method. This method comprehensively considers various nonlinear factors. For the sake of improving computational efficiency and guaranteeing simulation accuracy,a simplified model for cushion legs is presented,and an implicit algorithm is adopted to solve system kinematics equations. The effectiveness of the proposed simplified model and the simulation method are validated by comparison with test data. On this basis,the influence of center bodies with different damping and stiffness on the impact response of a payload is investigated,and then the theoretical explanation for the influence caused by stiffness is given. Results indicate that the acceleration response of the payload can be easily reduced by damping,and there is a negative correlation between the stiffness of the center body and the acceleration response peak value of the payload. This research provides theory basis and technical support for dynamics analysis and design of lunar lander.
The soft landing impact performance of lunar lander has a bearing on the success of moon mission. In order to accurately predict the dynamics response of a lunar lander during the landing process,the flexible model of the lunar lander is built by using nonlinear finite element method. This method comprehensively considers various nonlinear factors. For the sake of improving computational efficiency and guaranteeing simulation accuracy,a simplified model for cushion legs is presented,and an implicit algorithm is adopted to solve system kinematics equations. The effectiveness of the proposed simplified model and the simulation method are validated by comparison with test data. On this basis,the influence of center bodies with different damping and stiffness on the impact response of a payload is investigated,and then the theoretical explanation for the influence caused by stiffness is given. Results indicate that the acceleration response of the payload can be easily reduced by damping,and there is a negative correlation between the stiffness of the center body and the acceleration response peak value of the payload. This research provides theory basis and technical support for dynamics analysis and design of lunar lander.
引文
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[15]万峻麟,聂宏,李立春,等.基于瞬态动力学方法的月球探测器软着陆腿着陆冲击性能分析[J].兵工学报,2010,31(5):567-573.[Wan Jun-lin,Nie Hong,Li Li-chun,et al.Analysis of the landing impact performance for lunar landing leg with transient dynamic method[J].Acta Armamentarii,2010,31(5):567-573.]
[16]万峻麟,聂宏,陈金宝,等.月球着陆器有效载荷着陆冲击响应分析[J].宇航学报,2010,31(11):2456-2464.[Wan Jun-lin,Nie Hong,Chen Jin-bao,et al.Impact response analysis of payloads of lunar lander for lunar landing[J].Journal of Astronautics,2010,31(11):2456-2464.]
[17]Doengi F,Burnage S T,Cottard H,et al.Lander shockalleviation techniques[J].European Space Agency Bulletin,1998(93):51-60.
[18]William F R.Apollo experience report-lunar module landing gear subsystem[R].Houston:Manned Spacecraft Center,NASA TN D-6850,1972.
[19]梁东平,柴洪友,曾福明.月球着陆器着陆腿非线性有限元建模与仿真[J].北京航空航天大学学报,2013,39(1):1-5.[Liang Dong-ping,Chai Hong-you,Zeng Fu-ming.Nonlinear finite element modeling and simulation for landing leg of lunar lander[J].Journal of Beijing University of Aeronautics and Astronautics,2013,39(1):1-5.]
[20]梁东平,柴洪友.着陆冲击仿真月壤本构模型及有限元建模[J].航天器工程,2012,21(1):18-24.[Liang Dong-ping,Chai Hong-you.Lunar soil constitutive model and finite element modeling for landing impact simulation[J].Spacecraft Engineering,2012,21(1):18-24.]
[21]Chopra A K.Dynamics of structures:theory and applications to earthquake engineering[M].Upper Saddle River,New Jersey:Prentice-Hall,2005.
[2]Otto O R,Laurenson R M,Melliere R A,et al.Analyses and limited evaluation of payload and legged landing system structures for the survivable soft landing of instrument payloads[R].Washington:NASA CR-111919,1971.
[3]Lavender R E.Equations for two-dimensional analysis of touchdown dynamics of spacecraft with hinged legs including elastic,damping,and crushing effects[R].Huntsville:George C.Marshall Space Flight Center,N 66 23668,1963.
[4]Doiron H H,Zupp G A.A mathematical procedure for predicting the touchdown dynamics of a soft-landing vehicle[R].Houston:Manned Spacecraft Center,NASA TN D-7045,1971.
[5]Laurenson R,Melliere R,Mcgehee J.Analysis of legged landers for the survivable soft landing of instrument payload[J].Journal of Spacecraft and Rockets,1972,10(3):208-214.
[6]Nohmi M,Miyahara A.Modeling for lunar lander by mechanical dynamics software[C].AIAA Modeling and Simulation Techmologies Conference and Exhibit,San Francisco,California,2005.
[7]朱汪,杨建中.月球探测器软着陆机构着陆腿模型与仿真分析[J].宇航学报,2008,29(6):1723-1728.[Zhu Wang,Yang Jian-zhong.Modeling and simulation of landing leg for the lunar landing gear system[J].Journal of Astronautics,2008,29(6):1723-1728.]
[8]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):1792-1796.[Zhu Wang,Yang Jian-zhong.Touchdown stability simulation of laning gear system for lunar lander[J].Journal of Astronautics,2009,30(5):1792-1796.]
[9]蒋万松,黄伟,沈祖炜,等.月球探测器软着陆动力学仿真[J].宇航学报,2011,32(3):462-469.[Jiang Wan-song,Huang Wei,Shen Zu-wei,et al.Soft landing dynamics simulation for lunar explorer[J].Journal of Astronautics,2011,32(3):462-469.]
[10]陈金宝,聂宏,赵金才,等.月球探测器软着陆缓冲机构着陆性能分析[J].宇航学报,2008,29(6):1729-1732.[Chen Jin-bao,Nie Hong,Zhao Jin-cai,et al.Research of the factors of buffering performance in lunar lander[J].Journal of Astronautics,2008,29(6):1729-1732.]
[11]曾福明,杨建中,朱汪,等.月球着陆器着陆缓冲性能研究[J].航天器工程,2010(5):43-49.[Zeng Fu-ming,Yang Jian-zhong,Zhu Wang,et al.Research on landing impact attenuation performance of lunar lander[J].Spacecraft Engineering,2010(5):43-49.]
[12]赵俊锋.月球探测器软着陆动力学分析及力学环境研究[D].北京:北京理工大学,2011.[Zhao Jun-feng.A study on soft-landing dynamics and environment of lunar lander[D].Beijing:Beijing Institute of Technology,2011.]
[13]林轻,聂宏,陈金宝,等.月球着陆器软着陆冲击仿真[J].中国空间科学技术,2011(5):70-75.[Lin Qing,Nie Hong,Chen Jin-bao,et al.Soft landing impact simulation of lunar lander[J].Chinese Space Science and Technology,2011(5):70-75.]
[14]万峻麟,聂宏,李立春,等.月球着陆器着陆性能及多因素影响分析[J].南京航空航天大学学报,2010,42(3):288-293.[Wan Jun-lin,Nie Hong,Li Li-chun,et al.Analysis of landing performance and multi-factor effects with lunar lander[J].Journal of Nanjing University of Aeronautics and Astronautics,2010,42(3):288-293.]
[15]万峻麟,聂宏,李立春,等.基于瞬态动力学方法的月球探测器软着陆腿着陆冲击性能分析[J].兵工学报,2010,31(5):567-573.[Wan Jun-lin,Nie Hong,Li Li-chun,et al.Analysis of the landing impact performance for lunar landing leg with transient dynamic method[J].Acta Armamentarii,2010,31(5):567-573.]
[16]万峻麟,聂宏,陈金宝,等.月球着陆器有效载荷着陆冲击响应分析[J].宇航学报,2010,31(11):2456-2464.[Wan Jun-lin,Nie Hong,Chen Jin-bao,et al.Impact response analysis of payloads of lunar lander for lunar landing[J].Journal of Astronautics,2010,31(11):2456-2464.]
[17]Doengi F,Burnage S T,Cottard H,et al.Lander shockalleviation techniques[J].European Space Agency Bulletin,1998(93):51-60.
[18]William F R.Apollo experience report-lunar module landing gear subsystem[R].Houston:Manned Spacecraft Center,NASA TN D-6850,1972.
[19]梁东平,柴洪友,曾福明.月球着陆器着陆腿非线性有限元建模与仿真[J].北京航空航天大学学报,2013,39(1):1-5.[Liang Dong-ping,Chai Hong-you,Zeng Fu-ming.Nonlinear finite element modeling and simulation for landing leg of lunar lander[J].Journal of Beijing University of Aeronautics and Astronautics,2013,39(1):1-5.]
[20]梁东平,柴洪友.着陆冲击仿真月壤本构模型及有限元建模[J].航天器工程,2012,21(1):18-24.[Liang Dong-ping,Chai Hong-you.Lunar soil constitutive model and finite element modeling for landing impact simulation[J].Spacecraft Engineering,2012,21(1):18-24.]
[21]Chopra A K.Dynamics of structures:theory and applications to earthquake engineering[M].Upper Saddle River,New Jersey:Prentice-Hall,2005.