直接再入大气的月地返回窗口搜索策略
收稿日期: 2013-09-21
修回日期: 2014-05-03
网络出版日期: 2014-05-16
基金资助
国家自然科学基金（11173005，11203003）
A Search Strategy of Back Windows for Moon-to-Earth Trajectories Directly Returning to the Earth
Received date: 2013-09-21
Revised date: 2014-05-03
Online published: 2014-05-16
Supported by
National Natural Science Foundation of China (11173005, 11203003)
结合从月球停泊轨道直接返回地球的月地转移轨道设计，提出了一种月地返回窗口的搜索策略。首先基于双二体模型，结合月地转移轨道快速设计进行当天最小再入角的计算，根据当天最小再入角的计算结果初步判断返回窗口，然后指定再入角约束，在初步返回窗口内搜索满足两端约束条件的双二体月地转移轨道。然后将该轨道作为初值，基于受摄双二体模型，采用数值积分和微分改正法进一步求解精确的月地转移轨道。最后根据精确轨道计算结果，特别是速度增量，进一步确定返回窗口。这种策略大大加快了计算返回窗口的效率，可以在大范围内快速搜索返回窗口。通过对2017年1月和2月返回窗口的搜索及对结果的分析，最终给出了满足最省燃料和3天连续返回的窗口建议。
郑爱武 , 周建平 . 直接再入大气的月地返回窗口搜索策略[J]. 航空学报, 2014 , 35(8) : 2243 -2250 . DOI: 10.7527/S1000-6893.2014.0085
Based on the design of Moon-to-Earth trajectories which directly return to the Earth from the Moon parking orbit, a search strategy for back windows is presented. First, combined with the rapid design of Moon-to-Earth transfer trajectories based on double two-body model, an initial back window is primarily estimated according to minimum reentry angle calculations at that day. If the minimum reentry angle is within the reentry corridor, then the double two-body trajectory which meets the constraints at both ends is searched with the prescribed reentry angle constraint. The results are used as initial values for subsequent precise design of Moon-to-Earth transfer trajectories based on perturbed models. The precise trajectory is obtained by using numerical integration and differential correction. The back window is further determined by the results of the precise trajectories, especially the velocity increment. This strategy greatly accelerates the computational efficiency of the back window, and the window can be quickly found in a wide range. Through the search and results analysis of back windows in January and February 2017, a feasible back window which satisfies fuel-optimal and three consecutive return possibilities is finally proposed.
[1] State Council Information Office of the People's Republic of China. China's space activities in 2011[M]. Beijing: People's Publishing House, 2011: 10. (in Chinese) 中华人民共和国国务院新闻办公室. 2011年中国的航天[M]. 北京: 人民出版社, 2011: 10.
[2] Liu L, Wang X. On the orbit dynamics of lunar satellite[J]. Progress in Astronomy, 2003, 21(4): 281-288. (in Chinese) 刘林, 王歆. 月球卫星轨道力学综述[J]. 天文学进展, 2003, 21(4): 281-288.
[3] Li L T, Zhang Z M, Yang D. Study of rapid design method for cislunar transfer trajectory[J]. Acta Aeronautica et Astronautica Sinica, 2003, 24(2): 152-156.(in Chinese) 李立涛, 张振民, 杨涤. 奔月转移轨道的快速设计方法研究[J]. 航空学报, 2003, 24(2): 152-156.
[4] Miele A. Theorem of image trajectories in the Earth-Moon space//XIth International Astronautical Congress Stockholm 1960, 1960: 385-391.
[5] Miele A, Mancuso S. Optimal trajectories for Earth-Moon-Earth flight[J]. Acta Astronautica, 2001, 49(2): 59-71.
[6] Fazelzadeh S A, Varzandian G A. Minimum-time Earth-Moon and Moon-Earth orbital maneuvers using time-domain finite element method[J]. Acta Astronautica, 2010, 66(3-4): 525-538.
[7] Bai Y Z. Analysis of the characteristics of the trajectory of lunar probe. Changsha: National University of Defense Technology, 2005. (in Chinese) 白玉铸. 月球探测器轨道特性分析. 长沙: 国防科学技术大学, 2005.
[8] Gao Y D, Xi X N, Wang W. Cislunar trajectory design using searching step by step method[J]. Journal of Astronautics, 2006, 27(6): 1157-1161. (in Chinese) 高玉东, 郗晓宁, 王威. 地月空间飞行轨道分层搜索设计[J]. 宇航学报, 2006, 27(6): 1157-1161.
[9] Gao Y D, Xi X N, Bai Y Z, et al. Fast searching design method for return transfer trajectory of lunar probe[J]. Journal of Astronautics, 2008, 29(3): 765-771. (in Chinese) 高玉东, 郗晓宁, 白玉铸, 等. 月球探测器返回轨道快速搜索设计[J]. 宇航学报, 2008, 29(3): 765-771.
[10] Gao Y D. Study on the cislunar transfer trajectory of the lunar probe. Changsha: National University of Defense Technology, 2008. (in Chinese) 高玉东. 月球探测器地月空间转移轨道研究. 长沙: 国防科学技术大学, 2008.
[11] Zhang L, Yu D Y, Zhang H. Design of moon return trajectory with direct atmospheric reentry[J]. Spacecraft Engineering, 2010, 19(5): 50-55. (in Chinese) 张磊, 于登云, 张熇. 直接再入大气的月球返回轨道设计研究[J]. 航天器工程, 2010, 19(5): 50-55.
[12] Zhang L, Yu D Y, Zhang H. Preliminary design and characteristic analysis of Moon-to-Earth transfer trajectories[J]. Chinese Space Science and Technology, 2011, 31(3): 62-70. (in Chinese) 张磊, 于登云, 张熇. 月地转移轨道快速设计与特性分析[J]. 中国空间科学技术, 2011, 31(3): 62-70.
[13] Robinson S, Geller D. A simple targeting procedure for lunar trans-Earth injection, AIAA-2009-6107. Reston: AIAA, 2009.
[14] Zhao Y H, Hou X Y, Liu L. Characteristics of the reentry angle of lunar probes[J]. Journal of Spacecraft TT&C Technology, 2010, 29(5): 75-79. (in Chinese) 赵玉晖, 侯锡云, 刘林. 月球返回轨道再入角变化特征[J].飞行器测控学报, 2010, 29(5): 75-79.
[15] Battin R H. An introduction to the mathematics and methods of astrodynamics[M]. Revised ed. Reston: AIAA, 1999: 295-342.
[16] Liu L, Wang X. An orbital dynamics of lunar probe[M]. Beijing: National Defense Industry Press, 2006: 98-100. (in Chinese) 刘林, 王歆. 月球探测器轨道力学[M]. 北京: 国防工业出版社, 2006: 98-100.
[17] Zheng A W. Design and control of Moon-to-Earth trajectories. Beijing: Beihang University, 2013. (in Chinese) 郑爱武. 月地转移轨道设计与控制策略研究. 北京: 北京航空航天大学, 2013.
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