核热推进载人火星探测方案设计
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摘要
针对载人火星探测任务,结合我国现有技术基础,提出我国载人火星探测方案,重点研究载人火星探测任务推进系统的设计。首先,综合考虑载人深空探测任务的约束,采用Pork-Chop图设计了适用于不同任务场景的转移轨迹;然后,参考我国空间站技术,基于核热推进系统设计了我国载人火星探测任务的飞船;最后,对核热推进系统的发动机台数和推力进行了优化,得到了适用于不同任务场景的最优推进系统组合方案。本文所研究内容为我国未来载人火星探测任务提供了有益参考。
A manned Mars exploration concept based on the nuclear thermal propulsion is proposed for China's future Mars exploration. Firstly,the transfer trajectories suitable for different types of missions are designed using Pork-Chop.Secondly,according to the mission requirements,the spacecraft is designed by referring to the space station technical standards. Thirdly,the number and thrust of the nuclear thermal engines in the propulsion system are optimized to ensure that they can complete the mission with low costs and high reliability. The optimal solutions of the propulsion system are obtained for long-term and short-term Mars missions. Finally,the processes of the different manned Mars exploration missions are described in detail. The content of this article provides a useful reference for China's future manned Mars exploration missions.
A manned Mars exploration concept based on the nuclear thermal propulsion is proposed for China's future Mars exploration. Firstly,the transfer trajectories suitable for different types of missions are designed using Pork-Chop.Secondly,according to the mission requirements,the spacecraft is designed by referring to the space station technical standards. Thirdly,the number and thrust of the nuclear thermal engines in the propulsion system are optimized to ensure that they can complete the mission with low costs and high reliability. The optimal solutions of the propulsion system are obtained for long-term and short-term Mars missions. Finally,the processes of the different manned Mars exploration missions are described in detail. The content of this article provides a useful reference for China's future manned Mars exploration missions.
引文
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[12]叶培建,黄江川,孙泽洲,等.中国月球探测器发展历程和经验初探[J].中国科学:技术科学,2014,44(6):543-558.[Ye Pei-jian,Huang Jiang-chuan,Sun Ze-zhou,et al. The process and experience in the development of Chinese lunar probe[J]. Sci. Sin. Tech.,2014,44(16):543–558.]
[13] Ping J S,Su X L,Huang Q,et al. The Chang’E-1 orbiter plays a distinctive role in China’s first successful selenodetic lunar mission[J]. Science China Physics, Mechanics and Astronomy,2011,54(12):2130-2144.
[14] Wu W R,Liu Y,Liu L,et al. Pre-LOI trajectory maneuvers of the Chang’E-2 liberation point mission[J]. Science China Information Sciences,2012,55(6):1249-1258.
[15] Li C,Liu J,Ren X,et al. The Chang’E 3 mission overview[J]. Space Science Reviews,2015,190(1-4):85-101.
[16] Jiang X,Yang B,Li S. Overview of China’s 2020 Mars mission design and navigation[J]. Astrodynamics,2018,2(1):1-11.
[17]周建平.我国空间站工程总体构想[J].载人航天,2013,19(2):1-10.[Zhou Jian-ping. Chinese space station project overall vision[J]. Manned Spaceflight,2013,19(2):1-10.]
[18]解家春,霍红磊,苏著亭,等.核热推进技术发展综述[J].深空探测学报,2017,4(5):417-429.[Xie Jia-chun,Huo Hong-lei,Su Zhu-ting,et al. Review of nuclear thermal propulsion technology development[J]. Journal of Deep Space Exploration,2017,4(5):417-429.]
[19] Landau D F,Longuski J M. Trajectories for human missions to Mars,Part I:impulsivetransfers[J]. Journal of Spacecraft and Rockets,2006,43(5):1035-1042.
[20]杨彬,李爽.火星探测转移轨道初始设计与分析[J].中国空间科学技术,2017,37(4):18-27.[Yang Bin,Li Shuang.Transfer orbit initial design and analysis for Mars exploration mission[J]. Chinese Space Science and Technology,2017,37(4):18-27.]
[21]杨雷,张柏楠,郭斌,等.新一代多用途载人飞船概念研究[J].航空学报,2015,36(3):703-713.[Yang Lei,Zhang Bai-nan,Guo Bin,et al. Concept definition of new-generation multi-purpose manned spacecraft[J]. Acta Aeronautica et Astronautica Sinica,2015,36(3):703-713.]
[22] Joyner C R,Levack D J,Crowley J. Determining Mars mission NTP thrust size and architecture impact for mission options[C].The 51st AIAA/SAE/ASEE Joint Propulsion Conference,Orlando,USA,July 27-29,2015.
[2]李爽,江秀强.火星EDL导航,制导与控制方案综述与启示[J].宇航学报,2016,37(5):499-511.[Li Shuang,Jiang Xiu-qiang. Summary and enlightenment of GNC schemes for Mars entry,descent and landing[J]. Journal of Astronautics,2016,37(5):499-511.]
[3] Mase R A. Introduction:2001 Mars odyssey mission[J]. Journal of Spacecraft and Rockets,2005,42(3):385-385.
[4] Kornfeld R P,Prakash R,Devereaux A S,et al. Verification and validation of the Mars science laboratory/curiosity rover entry,descent,and landing system[J]. Journal of Spacecraft and Rockets,2014,51(4):1251-1269.
[5] Adamo D R,Giorgini J D,Abell P A,et al. Asteroid destinations accessible for human exploration:a preliminary survey in mid-2009[J]. Journal of Spacecraft and Rockets,2010,47(6):994-1002.
[6] Christian J A,Wells G, Lafleur J M, et al. Extension of traditional entry,descent,and landing technologies for human Mars exploration[J]. Journal of Spacecraft and Rockets,2008,45(1):130-141.
[7] Drake B G,Hoffman S J,Beaty D W. Human exploration of Mars,design reference architecture 5. 0[C]. IEEE 2010 IEEE Aerospace Conference,Big Sky,USA,Mar 6-13,2010.
[8] Messina P,Vennemann D. The European space exploration programme:current status of ESA’s plans for Moon and Mars exploration[J]. Acta Astronautica,2005,57(2-8):156-160.
[9] Borowski S,Mc Curdy D,Packard T.“7-Launch”NTR space transportation option for NASA’s Mars design reference architecture(DRA)5. 0[C]. The 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit,Denver,USA,August 2-5,2009.
[10]廖宏图.核热推进技术综述[J].火箭推进,2011,37(4):1-11.[Liao Hong-tu. Overview of nuclear thermal propulsion technologies[J]. Journal of Rocket Propulsion,2011,37(4):1-11.]
[11] Gabrielli R A,Herdrich G. Review of nuclear thermal propulsion systems[J]. Progress in Aerospace Sciences,2015,79:92-113.
[12]叶培建,黄江川,孙泽洲,等.中国月球探测器发展历程和经验初探[J].中国科学:技术科学,2014,44(6):543-558.[Ye Pei-jian,Huang Jiang-chuan,Sun Ze-zhou,et al. The process and experience in the development of Chinese lunar probe[J]. Sci. Sin. Tech.,2014,44(16):543–558.]
[13] Ping J S,Su X L,Huang Q,et al. The Chang’E-1 orbiter plays a distinctive role in China’s first successful selenodetic lunar mission[J]. Science China Physics, Mechanics and Astronomy,2011,54(12):2130-2144.
[14] Wu W R,Liu Y,Liu L,et al. Pre-LOI trajectory maneuvers of the Chang’E-2 liberation point mission[J]. Science China Information Sciences,2012,55(6):1249-1258.
[15] Li C,Liu J,Ren X,et al. The Chang’E 3 mission overview[J]. Space Science Reviews,2015,190(1-4):85-101.
[16] Jiang X,Yang B,Li S. Overview of China’s 2020 Mars mission design and navigation[J]. Astrodynamics,2018,2(1):1-11.
[17]周建平.我国空间站工程总体构想[J].载人航天,2013,19(2):1-10.[Zhou Jian-ping. Chinese space station project overall vision[J]. Manned Spaceflight,2013,19(2):1-10.]
[18]解家春,霍红磊,苏著亭,等.核热推进技术发展综述[J].深空探测学报,2017,4(5):417-429.[Xie Jia-chun,Huo Hong-lei,Su Zhu-ting,et al. Review of nuclear thermal propulsion technology development[J]. Journal of Deep Space Exploration,2017,4(5):417-429.]
[19] Landau D F,Longuski J M. Trajectories for human missions to Mars,Part I:impulsivetransfers[J]. Journal of Spacecraft and Rockets,2006,43(5):1035-1042.
[20]杨彬,李爽.火星探测转移轨道初始设计与分析[J].中国空间科学技术,2017,37(4):18-27.[Yang Bin,Li Shuang.Transfer orbit initial design and analysis for Mars exploration mission[J]. Chinese Space Science and Technology,2017,37(4):18-27.]
[21]杨雷,张柏楠,郭斌,等.新一代多用途载人飞船概念研究[J].航空学报,2015,36(3):703-713.[Yang Lei,Zhang Bai-nan,Guo Bin,et al. Concept definition of new-generation multi-purpose manned spacecraft[J]. Acta Aeronautica et Astronautica Sinica,2015,36(3):703-713.]
[22] Joyner C R,Levack D J,Crowley J. Determining Mars mission NTP thrust size and architecture impact for mission options[C].The 51st AIAA/SAE/ASEE Joint Propulsion Conference,Orlando,USA,July 27-29,2015.