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主动磁控微卫星姿态控制研究

刘海颖1，2，王惠南1，程月华2   

  1. 1：南京航空航天大学 自动化学院，江苏 南京 210016；

    2：南京航空航天大学 高新院微小卫星研究中心，江苏，南京 210016

  • 收稿日期:2006-11-27 修回日期:2007-03-02 出版日期:2007-07-30 发布日期:2007-07-30

Attitude Control of Micro-satellite with Active Magnetic Control

LIU Hai-ying1，2, WANG Hui-nan1, CHENG Yue-hua2   

  1. 1 College of Automatic Control, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China；
    2 Academy of Frontier Science,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China
  • Received:2006-11-27 Revised:2007-03-02 Online:2007-07-30 Published:2007-07-30

摘要： 采用偏置动量轮加磁力矩器作为控制方安案的非重力梯度微卫星不同于通常的速率阻尼—姿态捕获—动量轮起旋控制模式。针对这一问题，该文提出了B-DOT磁控加动量轮常值起旋、主动磁控加常值动量轮进行姿态捕获和稳定控制的方法，设计了限制姿态反馈磁控律进行捕获和稳定控制，以及LQG稳定控制律。采用磁场测量与磁控分时处理的策略，考虑测量误差和干扰力矩，以及不同偏置动量进行仿真，结果表明该方法使得整个控制过程操作简捷，初态控制阶段时间显著减少，稳态阶段具有较高的控制精度和抗干扰能力。

关键词: 微卫星, 主动磁控, B-DOT控制, 限制姿态反馈, LQG控制

Abstract: Different from the normal sequence consisting of attitude detumble, acquisition, and wheel speed-up, a method of attitude acquisition and stabilization for magnetic controlled micro-satellite is proposed, which uses B-dot controller, momentum wheel acceleration for detumble and active magnetic controller, and constant wheel. A limiting attitude feedback controller is designed for attitude capture and stabilization, and a LQG controller for attitude stabilization. Simulation is carried out using magnetic determination and control at different time. Measurement error, disturber moment and different bias momentum are considered. The result indicates that the method makes the control process simple and convenient, and can reduce initial control time with high control time with high control precision and robustness in stabilization.

Key words: micro-satellite, active magnetic control, B-DOT controller, limiting attitude feedback, LQG controller