宇航学报 ›› 2012, Vol. 33 ›› Issue (9): 1255-1261.doi: 10.3873/j.issn.1000-1328.2012.09.010

• 制导、导航与控制 • 上一篇    下一篇

挠性航天器混合H2/H∞输出反馈姿态控制(英)

刘华1,2, 张玉民2, 杨照华2   

  1. (1.杭州电子科技大学生命信息与仪器工程学院,杭州 310018;
    2.北京航空航天大学仪器科学与光电工程学院,北京 100191)
  • 收稿日期:2011-05-25 修回日期:2011-12-09 出版日期:2012-09-15 发布日期:2012-09-11
  • 基金资助:
    收稿日期:20110525;
    \ 修回日期:20111209
    基金项目:国家自然科学基金(60774013, 60925012, 60474050); 国家973计划(2009CB724001)

Mixed H2/H∞ Output Feedback Attitude Control for
Flexible Spacecraft

LIU Hua1,2, ZHANG Yumin2, YANG Zhaohua2   

  1. (1.College of Life Information Science and Instrument Engineering, Hangzhou Dianzi University, Hangzhou 310018, China;

    2.School of Instrument Science and Opto\|Electronics Engineering, Beijing University of Aeronautics and Astronautics,
    Beijing 100191, China)

  • Received:2011-05-25 Revised:2011-12-09 Online:2012-09-15 Published:2012-09-11

关键词: 挠性航天器, 振动抑制, 姿态控制, 输出反馈, 混合H2/H∞控制

Abstract: he H 2 /H ∞ output feedback attitude control problem of the flexible spacecraft composed of a central rigid body and some attached appendages is researched in this paper. The attitude control problem of such flexible spacecrafts is always difficult because the vibration of the elastic appendages can affect the central rigid motion and the measurement of the vibration modes is not easy in practice. A dynamic output feedback H 2 /H ∞ controller is designed here to perform attitude control in the presence of flexible vibration, model uncertainties and space environmental disturbances. The proposed algorithm with H ∞ output controller can implement the attitude control and the elastic mode stabilization at the same time. The system dynamics is also improved via
the H 2 design. Simulation shows the effectiveness of the presented algorithm.

Key words: Flexible spacecraft, Vibration suppression, Attitude control, Output feedback, H2/H∞ control

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