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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

朱小龙, 刘迎春, 高扬. 航天器最优受控绕飞轨迹推力幅值延拓设计方法[J]. 力学学报, 2014, 46(5): 756-769. doi: 10.6052/0459-1879-14-030
引用本文: 朱小龙, 刘迎春, 高扬. 航天器最优受控绕飞轨迹推力幅值延拓设计方法[J]. 力学学报, 2014, 46(5): 756-769. doi: 10.6052/0459-1879-14-030
Zhu Xiaolong, Liu Yingchun, Gao Yang. THRUST-AMPLITUDE CONTINUATION DESIGN APPROACH FOR SOLVING SPACECRAFT OPTIMAL CONTROLLED FLY-AROUND TRAJECTORY[J]. Chinese Journal of Theoretical and Applied Mechanics, 2014, 46(5): 756-769. doi: 10.6052/0459-1879-14-030
Citation: Zhu Xiaolong, Liu Yingchun, Gao Yang. THRUST-AMPLITUDE CONTINUATION DESIGN APPROACH FOR SOLVING SPACECRAFT OPTIMAL CONTROLLED FLY-AROUND TRAJECTORY[J]. Chinese Journal of Theoretical and Applied Mechanics, 2014, 46(5): 756-769. 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

doi: 10.6052/0459-1879-14-030
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

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

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

     

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出版历程
  • 收稿日期:  2014-01-22
  • 修回日期:  2014-04-05
  • 刊出日期:  2014-09-18

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