Fast Design and Optimization of the Low Energy Lunar Escaping Trajectory

被引：0
|
作者：
Liu Yue [1 ]
Qian Yingjing [2 ]
Jing Wuxing [3 ]
机构：
[1] DFH Satellite Co Ltd, Beijing 100094, Peoples R China
[2] Beijing Inst Technol, Beijing 100022, Peoples R China
[3] Harbin Inst Technol, Harbin 150001, Peoples R China
来源：
PROCEEDINGS OF THE 28TH CHINESE CONTROL AND DECISION CONFERENCE (2016 CCDC) | 2016年
关键词：
Fast; Design; Optimization; Low Energy; Moon Escaping;
D O I：
暂无
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
In this paper, a fast design and optimizing method of the low energy lunar escaping trajectory is introduced in the earth-moon elliptical four body system. Firstly, to find the optimal escaping conditions rapidly, the energy demand of the spacecraft is analyzed and it's found that when Moon is getting near its perigee and Sun becomes co-linear with Earth and Moon the escaping will consume the least amount of fuel. Then, given the appropriate launching opportunity the Manifold Degeneration Method is introduced to optimize the escaping energy. Finally, the computing process of the escaping trajectory design and optimization which contains 5 steps is given. According to the simulation results, the computing process proposed is effective in searching the optimal escaping trajectory and over 25% of the launching impulse can be saved with the optimal escaping orbit.
引用
收藏
页码：1203 / 1208
页数：6
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