临近空间载人舱着陆动力学及影响因素分析
|
摘要
为满足临近空间载人舱着陆缓冲装置可重复使用以及多着陆工况下能提供较好缓冲性能的要求,提出一种以双腔油气缓冲器为主支柱,单腔油气缓冲器为辅助支柱的新型着陆缓冲系统。针对舱体着陆过程,建立了考虑地面弹塑性变形的联合仿真动力学模型;通过与单腿着陆冲击试验的对比分析验证了所建动力学模型的有效性。在此基础上,研究了水平着陆速度,着陆俯仰角以及地面摩擦系数三种初始着陆条件对临近空间载人舱着陆性能的影响。研究结果表明:降低水平着陆速度可有效减小舱体水平着陆过载及提高着陆稳定性能;水平或小俯仰角着陆可使主、辅支柱的受载分配更加合理;减小足垫与地面间摩擦力可降低舱体竖直过载并提高着陆稳定性能。
In order to meet the requirements that the landing system of a near space manned capsule's reusable and providing good buffering performance under various landing conditions,a novel landing system is proposed with a doublechamber oleo-pneumatic shock absorber installed in the primary strut and two single-chamber oleo-pneumatic shock absorber installed in secondary struts respectively. A co-simulation dynamic model considering the ground elastic deformation is established for the landing impact procedure of the capsule,and the validity of the dynamic model is verified by the one-leg landing impact test. Based on the simulation model,the effects of the initial horizontal landing velocity,landing angle and ground friction coefficient on the landing performance of the near space manned capsule are studied. The results show that the decrease of the horizontal landing speed can effectively reduce the capsule horizontal landing overload and improve the landing stability; the load distribution between the primary and auxiliary struts can be more reasonable under the conditions with small landing angles; the decrease of the friction force between the footpad and ground can reduce the capsule vertical overload and improve the landing stability.
In order to meet the requirements that the landing system of a near space manned capsule's reusable and providing good buffering performance under various landing conditions,a novel landing system is proposed with a doublechamber oleo-pneumatic shock absorber installed in the primary strut and two single-chamber oleo-pneumatic shock absorber installed in secondary struts respectively. A co-simulation dynamic model considering the ground elastic deformation is established for the landing impact procedure of the capsule,and the validity of the dynamic model is verified by the one-leg landing impact test. Based on the simulation model,the effects of the initial horizontal landing velocity,landing angle and ground friction coefficient on the landing performance of the near space manned capsule are studied. The results show that the decrease of the horizontal landing speed can effectively reduce the capsule horizontal landing overload and improve the landing stability; the load distribution between the primary and auxiliary struts can be more reasonable under the conditions with small landing angles; the decrease of the friction force between the footpad and ground can reduce the capsule vertical overload and improve the landing stability.
引文
[1]薛永江,李体方.临近空间飞行器发展及关键技术分析[J].飞航导弹,2011(2):32-36.[Xue Yong-jiang,Li Tifang.Development and crucial technology analysis of near-space vehicle[J].Aerodynamic Missile Journal.2011(2):32-36.]
[2]中国空间技术研究院.北京空间机电研究所中标国内首个临近空间载人观光舱降落伞系统项目[J].航天返回与遥感,2016(2):81-81.[China Academy of Space Technology.Beijing space electromechanical research institute won the bid for parachute system of first near space manned capsule in China,Spacecraft Recovery Remote Sensing[J].2016(2):81-81.]
[3]杨建中,曾福明,满剑锋,等.嫦娥三号着陆器着陆缓冲系统设计与验证[J].中国科学:技术科学,2014(5):440-449.[Yang Jian-zhong,Zeng Fu-ming,Man Jian-feng,et al.Design and verification of the landing impact attenuation system for Chang'E-3 lander[J].Scientia Sinica,2014,44(5):440-449.]
[4]Lin Q,Kang Z,Ren J,et al.Impact analysis of lunar lander soft landing performance caused by the body gravity centerline shift[J].Journal of Aerospace Engineering,2014,28(4):04014104.
[5]吴宏宇,王春洁,丁宗茂,等.两种着陆模式下的着陆器缓冲机构构型优化[J].宇航学报,2017,38(10):1032-1040.[Wu Hong-yu,Wang Chun-jie,Ding Zong-mao,et al.Configuration optimization of landing gear under two kinds of landing modes[J].Journal of Astronautics,2017,38(10):1032-1040.]
[6]Wei X,Lin Q,Nie H,et al.Investigation on soft-landing dynamics of four-legged lunar lander[J].Acta Astronautica,2014,101(1):55-66.
[7]董威利,刘莉,周思达,等.月球探测器软着陆动力学及影响因素分析[J].宇航学报,2014,35(4):388-396.[Dong Wei-li,Liu Li,Zhou Si-da,et al.Analysis on soft-landing dynamics and influence factors of lunar lander[J].Journal of Astronautics,2014,35(4):388-396.]
[8]吴建云,王春洁,宋顺广.月球着陆器典型故障模式分析[J].宇航学报,2014,35(6):633-638.[Wu Jian-yun,Wang Chun-jie,Song Shun-guang.Analysis of typical failure modes for lunar lander[J].Journal of Astronautics,2014,35(6):633-638.]
[9]韩鸿硕,王一然,蒋宇平,等.国外深空探测器着陆缓冲系统的特点和应用[J].航天器工程,2012,21(6):7-24.[Han Hong-shuo,Wang Yi-ran,Jiang Yu-ping,et al.Characteristics and application of deep-space explorer landing impact attenuation system[J].Spacecraft Engineering,2012,21(6):7-24.]
[10]Sperling F B.The surveyor shock absorber[R].AIAA N50-17368,1964.
[11]汪岸柳,聂宏,陈金宝.月球着陆器软着陆状态跳跃半主动控制[J].航空学报,2009,30(11):2218-2223.[Wang Anliu,Nie Hong,Chen Jin-bao.State-jump semi-active control of lunar lander soft landing[J].Acta Aeronautica Et Astronautica Sinica,2009,30(11):2218-2223.]
[12]牛伯瑶.月球探测器着陆系统磁流变缓冲器的结构设计与优化[D].重庆:重庆大学,2016.[Niu Bo-yao.The structure design and optimization of magnetorheological buffer of lunar landing system[D].Chongqing:Chongqing University,2016.]
[13]牟让科,齐丕骞,吴启荣,等.一种自适应双腔缓冲器动力特性研究[J].应用力学学报,2001,18(s1):96-100.[Mu Rang-ke.Investigation for the dynamic behavior of a dual chamber energy-absorber with adaptive control[J].Chinese Journal of Applied Mechanics,2001,18(s1):96-100.]
[14]宋晓晨.某无人机起落架缓冲器防卡滞设计技术研究[D].南京:南京航空航天大学,2013.[Song Xiao-chen.Research on binding prevention design technique of an unmanned aircraft landing gear shock absorber[D].Nanjing:Nanjing university of aeronautics and astronautics,2013.]
[15]杨桂通.土动力学[M].北京:中国建材出版社,2000.
[16]陈金宝,聂宏,万峻麟.深空探测着陆器数字化设计及着陆性能影响因素[J].航空学报,2014,35(2):541-554.[Chen Jin-bao,Nie Hong,Wan Jun-lin.Digital design and landing performance influence factors of deep space lander[J].Acta Aeronautica Et Astronautica Sinica,2014,35(2):541-554.]
[17]Wong J Y.Theory of ground vehicles[M].3rd ed.New York:John Wiley&Sons Inc.,2001.
[18]Ding J Z,Wang C J.Fast modeling for lunar lander dynamic analysis[R].AIAA 2016-1191,2016.
[19]岳帅,聂宏,张明,等.一种用于垂直降落重复使用运载器的缓冲器性能分析[J].宇航学报,2016,37(6):646-656.[Yue Shuai,Nie Hong,Zhang Ming,et al.Analysis on performance of a damper used for vertical landing reusable launch vehicle[J].Journal of Astronautics,2016,37(6):646-656.]
[2]中国空间技术研究院.北京空间机电研究所中标国内首个临近空间载人观光舱降落伞系统项目[J].航天返回与遥感,2016(2):81-81.[China Academy of Space Technology.Beijing space electromechanical research institute won the bid for parachute system of first near space manned capsule in China,Spacecraft Recovery Remote Sensing[J].2016(2):81-81.]
[3]杨建中,曾福明,满剑锋,等.嫦娥三号着陆器着陆缓冲系统设计与验证[J].中国科学:技术科学,2014(5):440-449.[Yang Jian-zhong,Zeng Fu-ming,Man Jian-feng,et al.Design and verification of the landing impact attenuation system for Chang'E-3 lander[J].Scientia Sinica,2014,44(5):440-449.]
[4]Lin Q,Kang Z,Ren J,et al.Impact analysis of lunar lander soft landing performance caused by the body gravity centerline shift[J].Journal of Aerospace Engineering,2014,28(4):04014104.
[5]吴宏宇,王春洁,丁宗茂,等.两种着陆模式下的着陆器缓冲机构构型优化[J].宇航学报,2017,38(10):1032-1040.[Wu Hong-yu,Wang Chun-jie,Ding Zong-mao,et al.Configuration optimization of landing gear under two kinds of landing modes[J].Journal of Astronautics,2017,38(10):1032-1040.]
[6]Wei X,Lin Q,Nie H,et al.Investigation on soft-landing dynamics of four-legged lunar lander[J].Acta Astronautica,2014,101(1):55-66.
[7]董威利,刘莉,周思达,等.月球探测器软着陆动力学及影响因素分析[J].宇航学报,2014,35(4):388-396.[Dong Wei-li,Liu Li,Zhou Si-da,et al.Analysis on soft-landing dynamics and influence factors of lunar lander[J].Journal of Astronautics,2014,35(4):388-396.]
[8]吴建云,王春洁,宋顺广.月球着陆器典型故障模式分析[J].宇航学报,2014,35(6):633-638.[Wu Jian-yun,Wang Chun-jie,Song Shun-guang.Analysis of typical failure modes for lunar lander[J].Journal of Astronautics,2014,35(6):633-638.]
[9]韩鸿硕,王一然,蒋宇平,等.国外深空探测器着陆缓冲系统的特点和应用[J].航天器工程,2012,21(6):7-24.[Han Hong-shuo,Wang Yi-ran,Jiang Yu-ping,et al.Characteristics and application of deep-space explorer landing impact attenuation system[J].Spacecraft Engineering,2012,21(6):7-24.]
[10]Sperling F B.The surveyor shock absorber[R].AIAA N50-17368,1964.
[11]汪岸柳,聂宏,陈金宝.月球着陆器软着陆状态跳跃半主动控制[J].航空学报,2009,30(11):2218-2223.[Wang Anliu,Nie Hong,Chen Jin-bao.State-jump semi-active control of lunar lander soft landing[J].Acta Aeronautica Et Astronautica Sinica,2009,30(11):2218-2223.]
[12]牛伯瑶.月球探测器着陆系统磁流变缓冲器的结构设计与优化[D].重庆:重庆大学,2016.[Niu Bo-yao.The structure design and optimization of magnetorheological buffer of lunar landing system[D].Chongqing:Chongqing University,2016.]
[13]牟让科,齐丕骞,吴启荣,等.一种自适应双腔缓冲器动力特性研究[J].应用力学学报,2001,18(s1):96-100.[Mu Rang-ke.Investigation for the dynamic behavior of a dual chamber energy-absorber with adaptive control[J].Chinese Journal of Applied Mechanics,2001,18(s1):96-100.]
[14]宋晓晨.某无人机起落架缓冲器防卡滞设计技术研究[D].南京:南京航空航天大学,2013.[Song Xiao-chen.Research on binding prevention design technique of an unmanned aircraft landing gear shock absorber[D].Nanjing:Nanjing university of aeronautics and astronautics,2013.]
[15]杨桂通.土动力学[M].北京:中国建材出版社,2000.
[16]陈金宝,聂宏,万峻麟.深空探测着陆器数字化设计及着陆性能影响因素[J].航空学报,2014,35(2):541-554.[Chen Jin-bao,Nie Hong,Wan Jun-lin.Digital design and landing performance influence factors of deep space lander[J].Acta Aeronautica Et Astronautica Sinica,2014,35(2):541-554.]
[17]Wong J Y.Theory of ground vehicles[M].3rd ed.New York:John Wiley&Sons Inc.,2001.
[18]Ding J Z,Wang C J.Fast modeling for lunar lander dynamic analysis[R].AIAA 2016-1191,2016.
[19]岳帅,聂宏,张明,等.一种用于垂直降落重复使用运载器的缓冲器性能分析[J].宇航学报,2016,37(6):646-656.[Yue Shuai,Nie Hong,Zhang Ming,et al.Analysis on performance of a damper used for vertical landing reusable launch vehicle[J].Journal of Astronautics,2016,37(6):646-656.]