Article

Launch Trajectory Design for Lunar Probes with Finite Thrust Maneuver

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  • 1. China Academy of Launch Vehicle Technology, Beijing 100076, China
    2. Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China

Received date: 18 May 2016

Revised date: 19 Jun 2016

Abstract

To launch a lunar probe is a multi-celestial body problem, and also a strict orbit rendezvous problem. Many launch trajectory plans can be obtained theoretically, but selctions are strictly limited for enginnering applications with many constarints, such as launch capacity, launch site, telemetry and control conditions etc. The most conventional method is to transfer from the parking orbit with finite thrust. This paper takes a typical launch vehicle as an example, the Earth-lunar transfer scheme with constraints are analyzed and studied.

Cite this article

CHEN Xinmin, ZHOU Tianshuai, ZHU Dongge, WANG Jianming . Launch Trajectory Design for Lunar Probes with Finite Thrust Maneuver[J]. Journal of Deep Space Exploration, 2016 , 3(3) : 253 -261 . DOI: 10.15982/j.issn.2095-7777.2016.03.009

References

[1] 郗晓宁,王威,高玉东. 近地航天器轨道基础[M]. 北京:国防科技大学出版社,2003:268-313. Xi X N,Wang W,Gao Y D. Near-Earth spacecraft orbit foundation[M]. National Defence Science and Technology Press,2003:268-313.
[2] 杨维廉. 发射极月卫星的转移轨道研究[J]. 航天器工程,1997,9(3):23-32. Yang W L. Transfer trajectory research for lunar polar satellite launching[J]. Space Engineering,1997,9(3):23-32.
[3] 崔平远,乔栋,崔祜涛. 深空探测轨道设计与优化[M]. 北京:科学出版社,2014:45-64. Cui P Y,Qiao D,Cui H T. Deep-space exploration orbit design and optimize[M]. Beijing:Science Press,2014:45-64.
[4] 杨嘉墀. 航天器轨道动力学与控制(上)[M]. 北京:宇航出版社,1995:544-557. Yang J C. Space orbit dynamics and control(up)[M]. Beijing:Space Navigation Press,1995,12:544-557.
[5] 褚桂柏,张熇. 月球探测器技术[M]. 北京:中国科学技术出版社,2007:135-149. Chu G B,Zhang H. Lunar exploration technique[M]. Beijing:China Technology Press,2007,7:135-149.
[6] 黄文德,郗晓宁,王威. 从近地轨道入轨的载人登月发射窗口分析与设计[J]. 天文学进展,2010,9(3):310-319. Huang W D,Xi X N,Wang W. Launch window analysis and trajectory design for manned landing mission from near-Earth orbit injection to the Moon[J]. Progress in Astronomy. 2010,9(3):310-319.
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