INDIRECT OPTIMIZATION OF LOW-THRUST EARTH ESCAPE TRAJECTORIES

被引：0
|
作者：
Huang, Hao [1 ]
Gong, Qi [2 ]
Han, Chao [1 ]
机构：
[1] Beihang Univ, Sch Astronaut, Beijing 100191, Peoples R China
[2] Univ Calif Santa Cruz, Appl Math & Stat, Santa Cruz, CA 95064 USA
来源：
SPACEFLIGHT MECHANICS 2013, PTS I-IV | 2013年 / 148卷
关键词：
D O I：
暂无
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
Indirect optimization is used in this paper to compute fuel-optimal earth escape trajectory. By shooting backward in time we convert the unknowns from initial Lagrange multipliers to orbit states at the final time. The three-dimensional long-time fuel-optimal escape trajectory with control constraint is designed by first solving a two-dimensional short-time fuel-optimal escape trajectory without control constraint; then using a curve fitting technique to generate initial guess for the final state. This accuracy and efficiency of the proposed method is demonstrated on a low thrust escape trajectory optimization problem.
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页码：1523 / 1531
页数：9
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