探测器月地转移入射变轨策略优化设计
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摘要
在探测器月球采样返回任务中,从环绕月球的轨道返回地球的转移入射考虑采用一次变轨或两次变轨的方案。其中,月地转移入射一次变轨方案要求采用大推力变轨发动机,难以实现高精度轨道控制。为此,文章提出将月地转移入射一次变轨机动改为分两次执行,两次间隔大约1天的优化策略。首先讨论了月地转移入射一次变轨的基本设计方法,然后给出了月地转移入射两次变轨方案的优化设计算法流程,并采用数值算例进行了说明。此外,还对月地转移入射三脉冲变轨方案和低能月地转移轨道展开了讨论,并在多方案比较分析的基础上,推荐了月球采样返回任务采用的月地转移入射变轨策略。
In a typical lunar sample return mission,one-impulse or two-impulse strategy can be adopted for the trans-earth insertion maneuver.It is found in this study that the use of an engine with large magnitude thrust is necessary for one-impulse strategy,which however may lead to poor orbital control performance.It is proposed in the study that the one-impulse strategy be replaced by a two-impulse strategy,with about one-day time difference between the execution times of the two maneuvers.The paper first addresses the basic design procedure of one-impulse strategy,then an optimization procedure is introduced for the design of two-impulse strategy,with numerical examples for the purpose of illustration.Also discussed in the paper are the design procedures of three-impulse trans-earth insertion strategy and low-energy moon-to-earth transfer trajectory.Based on the comparison study of these strategies,the appropriate trans-earth insertion strategies are recommended for the lunar sample return missions.
In a typical lunar sample return mission,one-impulse or two-impulse strategy can be adopted for the trans-earth insertion maneuver.It is found in this study that the use of an engine with large magnitude thrust is necessary for one-impulse strategy,which however may lead to poor orbital control performance.It is proposed in the study that the one-impulse strategy be replaced by a two-impulse strategy,with about one-day time difference between the execution times of the two maneuvers.The paper first addresses the basic design procedure of one-impulse strategy,then an optimization procedure is introduced for the design of two-impulse strategy,with numerical examples for the purpose of illustration.Also discussed in the paper are the design procedures of three-impulse trans-earth insertion strategy and low-energy moon-to-earth transfer trajectory.Based on the comparison study of these strategies,the appropriate trans-earth insertion strategies are recommended for the lunar sample return missions.
引文
[1]Gunther P.Asymptotically optimum two-impulse transfer from lunar orbit[J].AIAA Journal,1966,4(2):346-352
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[12]Wang Zhongsheng.Preliminary design of the phasing strategy of a lunar orbit rendezvous mission[C]//AAS/AIAA Astrodynamics Specialist Conference.Washington D.C.:AIAA,2013
[13]Wang Z,Meng Z,Gao S.Phasing strategy of lunar orbit rendezvous and docking operation:design and flight test[C]//Global Space Exploration Conference(GLEX).Paris:IAF,2017
[2]Gerbracht R J,Penzo P A.Optimum three-impulse transfer between an elliptic orbit and a non-coplanar escape asymptote[C]//AAS/AIAA Astrodyanmics Specialist Conference.Washington D.C.:AIAA,1968
[3]Ocampo C,Saudemont R.Initial trajectory model for a multi-maneuver moon-to-earth abort sequence[J].Journal of Guidance,Control,and Dynamics,2010,33(4):1184-1194
[4]Ivashkin V.On themoon-to-earth trajectories with gravitational escape from the moon attraction[C]//18th International Symposium on Space Flight Dynamics.Munich:DLR and ESA,2004
[5]刘玥.月地低能返回轨道设计与控制方法研究[D].哈尔滨:哈尔滨工业大学,2014Liu Yue.Research on the low energy moon return trajectory design and control strategy[D].Harbin:Harbin Institute of Technology,2014(in Chinese)
[6]汪中生,孟占峰,高珊.月地转移入射变轨策略优化设计[C]//中国飞行力学学术年会.北京:中国宇航学会,2017Wang Zhongsheng,Meng Zhanfeng,Gao Shan.Optimization of maneuver strategy of moon to earth transfer insertion[C].//China Space Flight Mechanics Meeting.Beijing:CSA,2017(in Chinese)
[7]汪中生,孟占峰,田百义,等.月球和火星任务返回地球转移入射变轨策略优化设计[C]//中国空间技术研究院航天动力学论坛第三届学术研讨会.北京:中国空间技术研究院,2017Wang Zhongsheng,Meng Zhanfeng,Tian Baiyi,et al.Optimization of maneuver strategy of Moon or Mars to Earth transfer insertion[C]//The 3rd Symposium on Astrodynamics in China Academy of Space Technology.Beijing:China Academy of Space Technology,2017(in Chinese)
[8]Wang Z S,Meng Z F,Gao S.Optimization of TEIstrategy in a lunar sample return mission[C]//4th IAAConference on Dynamics and Control of Space Systems(DYCOSS2018).Changsha:IAA,2018
[9]Wang Z,Meng Z.Orbit design considerations for precision lunar landing for a sample return mission[C]//AAS/AIAA Space Flight Mechanics Meeting.Washington D.C.:AIAA,2014
[10]汪中生,孟占峰,高珊.月面定点着陆变轨策略研究[J].航天器工程,2017,26(2):29-37Wang Zhongsheng,Meng Zhanfeng,Gao Shan.Study of orbital maneuver strategies for precision lunar landing[J].Spacecraft Engineering,2017,26(2):29-37(in Chinese)
[11]汪中生,孟占峰,高珊.月球轨道交会任务的远程导引变轨策略研究[J].航天器工程,2014,23(5):103-110Wang Zhongsheng,Meng Zhanfeng,Gao Shan.Study of orbit maneuver strategy for lunar orbit rendezvous mission[J].Spacecraft Engineering,2014,23(5):103-110(in Chinese)
[12]Wang Zhongsheng.Preliminary design of the phasing strategy of a lunar orbit rendezvous mission[C]//AAS/AIAA Astrodynamics Specialist Conference.Washington D.C.:AIAA,2013
[13]Wang Z,Meng Z,Gao S.Phasing strategy of lunar orbit rendezvous and docking operation:design and flight test[C]//Global Space Exploration Conference(GLEX).Paris:IAF,2017