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陈新民, 周天帅, 朱冬阁, 王建明. 有限推力变轨的月球探测器发射轨道设计[J]. 深空探测学报(中英文), 2016, 3(3): 253-261. DOI: 10.15982/j.issn.2095-7777.2016.03.009
引用本文: 陈新民, 周天帅, 朱冬阁, 王建明. 有限推力变轨的月球探测器发射轨道设计[J]. 深空探测学报(中英文), 2016, 3(3): 253-261. DOI: 10.15982/j.issn.2095-7777.2016.03.009
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
Citation: 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

有限推力变轨的月球探测器发射轨道设计

Launch Trajectory Design for Lunar Probes with Finite Thrust Maneuver

  • 摘要: 月球探测器的发射是一个多体问题,也是严格的轨道交会问题。发射轨道方案从理论上有很多种形式,但在工程应用中,受到火箭能力、发射场和测控条件等多种因素制约,方案选择限制非常严格。利用现有火箭,采用有限推力从停泊轨道转移发射是最常用的一种发射方式。本文以某典型火箭为例,对采用有限推力变轨方案的奔月轨道设计流程、发射方案、轨道设计方法、精度分析、发射窗口设计进行了详细分析和研究。

     

    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.

     

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