›› 2017, Vol. 37 ›› Issue (6): 1-.doi: 10.16708/j.cnki.1000-758X.2017.0098

• 研究探讨 •    下一篇


 雷拥军, 袁利   

  1. 1. 北京控制工程研究所,北京100094
    2. 空间智能控制技术重点实验室,北京100094
  • 收稿日期:2017-08-14 修回日期:2017-09-30 出版日期:2017-12-25 发布日期:2017-11-20

Momentum envelope analysis and momentum management for spacecraft with a flywheel array

LEI  Yong-Jun, YUAN  Li   

  1. 1. Beijing Institute of Control Engineering,Beijing 100094,China
    2. Science and Technology on Space Intelligent Control Laboratory,Beijing 100094, China
  • Received:2017-08-14 Revised:2017-09-30 Online:2017-12-25 Published:2017-11-20

摘要: 文章进行了冗余轮系航天器角动量包络分析及角动量管理问题研究。基于轮系可视化角动量包络分析,提出了一种角动量包络特征参量描述及基于特征参量的沿任意方向飞轮极限角动量的解算方法,并设计了一种基于以飞轮极限角动量为参考的零运动力矩分配轮系角动量管理策略,该方法充分利用轮系最大角动量容量,以避免系统角动量未达到包络面时出现部分飞轮角动量饱和的现象,数学仿真对比验证了所提出策略的有效性。

关键词: 航天器, 飞轮, 线性规划, 角动量包络, 角动量管理

Abstract: The problems of momentum envelope analysis and momentum management for spacecraft with a redundant flywheel array were investigated. Firstly,based on analysis of the visualized envelope, a characteristic parameter set was established, and an algorithm was proposed to determine the maximum momenta available from the wheels in a specified direction in threedimensional total momentum space. Furthermore, a momentum management strategy was developed based on a null motion allocation taking the maximum momenta as the reference, to fully utilize the momentum envelope capacity and to avoid the case where wheel momentum saturation appears before the total momentum arriving at the envelope. Finally, comparative numerical simulations were provided to illustrate the effectiveness of the proposed momentum management strategy.

Key words: spacecraft, fly wheel, linear programming, momentum envelope, momentum management