火星采样返回任务轨道方案初步设计
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摘要
火星采样返回是近年国际上深空探测规划的重点任务.本文考虑开展火星探测任务的实际工程约束,以2028年发射机会为例,对火星采样返回任务全飞行过程各阶段的轨道方案进行了研究,在不同方案比较分析的基础上,推荐未来开展火星采样返回任务的可能轨道方案.对任务轨道进行了初步分析和设计,给出了主要阶段的分析结果,讨论重点包括发射转移、近火制动、火星轨道交会对接和火地转移等飞行阶段轨道方案的初步设计.分析表明:火星采样返回任务每两年有一次发射机会,其中2028年发射窗口集中在11月;考虑到重型火箭研发风险,可以采用现役火箭分别发射着陆上升组合体和轨返组合体的两次发射方案;从火星返回地球,约两年有一次返回机会,火星出发窗口和地球出发窗口相差约两年时间.
Mars sample return missions are the focus of international deep space exploration planning in recent years. In this paper,the orbit design of the different flight phases of a Mars sample return mission is studied with consideration of practical engineering constraints, using 2028 launch opportunity as an example; based on comparative analysis of different schemes, feasible orbit designs are recommended for future Mars sample return missions. Preliminary analysis and design of the mission orbit are carried out and the analysis results of the main flight phases are provided in the paper, and the discussion focuses on launch opportunity, Earth to Mars transfer, Mars orbit insertion, rendezvous and docking in Mars orbit, and Mars to Earth transfer. It is shown in the paper that the launch opportunities for Mars sample return missions emerge every two years, and the launch windows in 2028 opportunity concentrate in the November; considering the high risk of the research and development of heavy lift rockets, the scheme that the descent and ascent module, the orbiter and reentry module are launched separately using two available rockets is recommended; the Mars to Earth return opportunities emerge about every two years, and the return windows open about two years after the Earth departure.
Mars sample return missions are the focus of international deep space exploration planning in recent years. In this paper,the orbit design of the different flight phases of a Mars sample return mission is studied with consideration of practical engineering constraints, using 2028 launch opportunity as an example; based on comparative analysis of different schemes, feasible orbit designs are recommended for future Mars sample return missions. Preliminary analysis and design of the mission orbit are carried out and the analysis results of the main flight phases are provided in the paper, and the discussion focuses on launch opportunity, Earth to Mars transfer, Mars orbit insertion, rendezvous and docking in Mars orbit, and Mars to Earth transfer. It is shown in the paper that the launch opportunities for Mars sample return missions emerge every two years, and the launch windows in 2028 opportunity concentrate in the November; considering the high risk of the research and development of heavy lift rockets, the scheme that the descent and ascent module, the orbiter and reentry module are launched separately using two available rockets is recommended; the Mars to Earth return opportunities emerge about every two years, and the return windows open about two years after the Earth departure.
引文
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14 Baranov A A.An algorithm for calculating parameters of multi-orbit maneuvers in remote guidance.Cosmic Res,1990,28:61-67
15 Gong S P,Baoyin H X,Li J F.Rapid targeting method for multi-impulse near circular orbit rendezvous(in Chinese).Space Control Tech Appl,2010,36:1-6[龚胜平,宝音贺西,李俊峰.多冲量近圆轨道交会的快速打靶法.空间控制技术与应用,2010,36:1-6]
16 Zhang J.Strategy and planning of space rendezvous phasing maneuvers(in Chinese).Dissertation for Master Degree.Changsha:National University of Defense Technology,2008[张进.空间交会远程导引变轨任务规划.硕士学位论文.长沙:国防科技大学,2008]
17 Wang Z S,Meng Z,Gao S,et al.Preliminary design of the phasing strategy of a lunar orbit rendezvous mission.In:AAS/AIAA Astrodynamics Specialist Conference.Hilton Head,2013
18 Wang Z S,Meng Z F,Gao S.Study of orbit maneuver strategy for lunar orbit rendezvous mission(in Chinese).Spacecr Eng,2014,23:103-110[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.航天器工程,2014,23:103-110]
19 Wang Z S,Meng Z F,Gao S,et al.Phasing strategy of lunar orbit rendezvous and docking operation:Design and flight test.In:Global Space Exploration Conference(GLEX).Beijing,2017
20 Wang Z S,Meng Z F,Gao S.Optimization of maneuver strategy of Moon to Earth transfer insertion(in Chinese).In:China Space Flight Mechanics Meeting.Yantai,2017[汪中生,孟占峰,高珊.月地转移入射变轨策略优化设计.见:中国飞行力学学术年会,烟台,2017]
21 Wang Z S,Meng Z F,Tian B Y,et al.Optimization of maneuver strategy of Moon or Mars to Earth transfer insertion(in Chinese).In:The 3rd Symposium on Astrodynamics,China Academy of Space Technology.Beijing,2017[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.见:五院航天动力学论坛第三届学术研讨会,北京,2017]
22 Wang Z S,Meng Z F,Gao S.Optimization of TEI strategy in a lunar sample return mission.In:4th IAA Conference on Dynamics and Control of Space Systems(DYCOSS2018).Changsha,2018
2 Wercinski P F.Mars sample return-A direct and minimum-risk design.J Spacecraft Rockets,1996,33:381-385
3 Gamber R T,Adams G L.Mars sample return mission options.AIAA 91-3017,July 1991
4 O’Neil W J,Cazaux C.The Mars sample return project.Acta Astronaut,2000,47:453-465
5 Cazaux C,Naderi F,Whetsel C,et al.The NASA/CNES Mars sample return-A status report.Acta Astronaut,2004,54:601-617
6 Wolf A A,Acikmese B,Cheng Y,et al.Toward improved landing precision on Mars.In:IEEE Aerospace Conference.Big Sky,2011
7 Dillman R,Laub B,Kellas S,et al.Development and Test Plan for the MSR EEV.In:The 2nd International Planetary Probe Workshop.Moffett Field,2004.269-274
8 Brown C.Spacecraft Mission Design.Reston:AIAA Press,1992
9 Wang Z S,Guo H L,Qu G J.Launch opportunity analysis for Mars missions(in Chinese).In:China Space Flight Mechanics Meeting.Guiyang,September 2007[汪中生,郭海林,曲广吉.火星飞行原理和发射时机分析.见:中国飞行力学学术年会,贵阳,2007年9月]
10 Curtis H D.Orbital Mechanics for Engineering Students.Burlington:Elsevier Butterworth-Heinemann,2005
11 Zhang X H,Liu Z S.Study of the transfer trajectory with unpowered gravity assist for Mars missions(in Chinese).J Astronaut,2008,29:1739-1746[张旭辉,刘竹生.火星探测无动力借力飞行轨道研究.宇航学报,2008,29:1739-1746]
12 Derz U,Seboldt W.Mars sample return mission architectures utilizing low thrust propulsion.Acta Astronaut,2012,77:83-96
13 Liu D C,Zhou W Y.Mars aerobraking orbit design.In:Spaceflight and Mechanics Summit.Beijing,2011[刘德成,周文艳.火星气动减速轨道设计.见:航天与力学高峰论坛.北京,2011]
14 Baranov A A.An algorithm for calculating parameters of multi-orbit maneuvers in remote guidance.Cosmic Res,1990,28:61-67
15 Gong S P,Baoyin H X,Li J F.Rapid targeting method for multi-impulse near circular orbit rendezvous(in Chinese).Space Control Tech Appl,2010,36:1-6[龚胜平,宝音贺西,李俊峰.多冲量近圆轨道交会的快速打靶法.空间控制技术与应用,2010,36:1-6]
16 Zhang J.Strategy and planning of space rendezvous phasing maneuvers(in Chinese).Dissertation for Master Degree.Changsha:National University of Defense Technology,2008[张进.空间交会远程导引变轨任务规划.硕士学位论文.长沙:国防科技大学,2008]
17 Wang Z S,Meng Z,Gao S,et al.Preliminary design of the phasing strategy of a lunar orbit rendezvous mission.In:AAS/AIAA Astrodynamics Specialist Conference.Hilton Head,2013
18 Wang Z S,Meng Z F,Gao S.Study of orbit maneuver strategy for lunar orbit rendezvous mission(in Chinese).Spacecr Eng,2014,23:103-110[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.航天器工程,2014,23:103-110]
19 Wang Z S,Meng Z F,Gao S,et al.Phasing strategy of lunar orbit rendezvous and docking operation:Design and flight test.In:Global Space Exploration Conference(GLEX).Beijing,2017
20 Wang Z S,Meng Z F,Gao S.Optimization of maneuver strategy of Moon to Earth transfer insertion(in Chinese).In:China Space Flight Mechanics Meeting.Yantai,2017[汪中生,孟占峰,高珊.月地转移入射变轨策略优化设计.见:中国飞行力学学术年会,烟台,2017]
21 Wang Z S,Meng Z F,Tian B Y,et al.Optimization of maneuver strategy of Moon or Mars to Earth transfer insertion(in Chinese).In:The 3rd Symposium on Astrodynamics,China Academy of Space Technology.Beijing,2017[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.见:五院航天动力学论坛第三届学术研讨会,北京,2017]
22 Wang Z S,Meng Z F,Gao S.Optimization of TEI strategy in a lunar sample return mission.In:4th IAA Conference on Dynamics and Control of Space Systems(DYCOSS2018).Changsha,2018