航天器最优受控绕飞轨迹推力幅值延拓设计方法

朱小龙; 刘迎春; 高扬

doi:10.6052/0459-1879-14-030

航天器最优受控绕飞轨迹推力幅值延拓设计方法

1.
中国科学院空间应用工程与技术中心, 北京100094l
2. 中国科学院大学, 北京100049

基金项目: 国家自然科学基金资助项目（11372311）.

详细信息

作者简介:
高扬，研究员，主要研究方向：航天飞行动力学与控制.E-mail：gaoyang@csu.ac.cn

中图分类号: V412.4
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出版历程
- 收稿日期: 2014-01-21
- 修回日期: 2014-04-04
- 刊出日期: 2014-09-17

THRUST-AMPLITUDE CONTINUATION DESIGN APPROACH FOR SOLVING SPACECRAFT OPTIMAL CONTROLLED FLY-AROUND TRAJECTORY

1.
Technology and Engineering Center for Space Utilization, Chinese Academy of Sciences, Beijing 100094, China
2. University of Chinese Academy of Sciences, Beijing 100049, China

Funds: The project was supported by the National Natural Science Foundation of China (11372311).

摘要

摘要: 针对航天器燃料最优可变周期绕飞轨迹的求解问题，提出了一种以推力幅值为延拓参数的延拓方法. 问题求解从最为简单的双脉冲绕飞轨迹出发，首先利用有限推力替代脉冲推力，设定推力序列为“开— 关— 开”，然后逐步减小推力幅值，最终得到最小推力绕飞轨迹；此后，再逐步增加推力幅值，结合主矢量曲线判断最优推力开关序列，将最小推力解延拓至有限推力以及脉冲推力燃料最优解. 该方法通过对推力幅值的延拓，实现了有限推力bang-bang 控制与脉冲推力燃料最优绕飞轨迹优化问题的一并求解，同时避免了最优控制问题中协态变量的随机猜测. 慢速与快速绕飞算例的优化结果验证了所提出方法的有效性.
- 绕飞轨迹 /
- 延拓方法 /
- 轨迹优化 /
- 燃料最优 /
- 有限推力 /
- 脉冲推力
Abstract: A continuation approach in which the thrust amplitude is the continuation parameter is proposed to solve the fuel-optimal spacecraft fly-around trajectories. On the basis of the two-impulse solution, the minimum thrust amplitude that ensures the feasibility of the fly-around trajectory is obtained by replacing impulsive thrust with finite thrust and decreasing the thrust amplitude gradually. Once obtaining the minimum-thrust solution, the thrust amplitude is increased step by step and the optimal thrusting switching sequence is determined by the primer vector in each step. Consequently, the fuel-optimal trajectories with both finite thrust and impulsive thrust are obtained by continuation from the minimum-thrust fly-around trajectory solution. By continuation on all feasible thrust amplitudes, the fuel-optimal solutions with both finite thrust and impulsive thrust are solved, and the costate variables in the optimal control problem are no longer acquired randomly. Numerical examples of slow and fast fly-around trajectories show the effectiveness of the proposed continuation approach.
- fly-around trajectory /
- continuation approach /
- trajectory optimization /
- fuel-optimal /
- finite thrust /
- impulsive thrust

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