宇航学报

宇航学报 ›› 2014, Vol. 35 ›› Issue (3): 306-314.doi: 10.3873/j.issn.1000-1328.2014.03.009

• 制导、导航与控制 • 上一篇    下一篇

基于内模原理的复杂挠性卫星姿态控制研究

陆栋宁，刘一武   

  1. 1.北京控制工程研究所，北京 100190； 2.空间智能控制技术重点实验室，北京 100190
  • 收稿日期:2013-04-09 修回日期:2013-07-16 出版日期:2014-03-15 发布日期:2014-03-25
  • 基金资助:

    国家自然科学基金（10872028）

Research on Internal Model Principle Based Attitude Control for Complex Flexible Satellites

LU Dong ning,  LIU Yi wu   

  1. 1.Beijing Institute of Control Engineering, Beijing 100190, China;
    2.Science and Technology on Space Intelligent Control Laboratory, Beijing 100190, China
  • Received:2013-04-09 Revised:2013-07-16 Online:2014-03-15 Published:2014-03-25

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摘要：

首先对具有运动挠性附件的航天器的姿态动力学模型进行了简要讨论和分析，证明了对于受步进扰动的复杂挠性卫星系统，采用输出反馈PD控制仅能得到一致有界稳定的结论。为了获得闭环系统的渐近稳定性能，进一步构造了具有内模补偿的PD控制系统，并且根据Lyapunov理论给出了严格证明。基于美国GOES 8号静止轨道气象卫星公布的动力学参数，对PD控制及含有内模补偿的PD控制两类控制器进行了仿真对比，以校验所设计控制系统的有效性。最后，进行了总结并提出进一步的研究设想。

关键词: 对日定向太阳帆板, 内模原理, 挠性卫星, 姿态控制

Abstract:

From an attitude control point of view, spacecrafts with moving flexible appendages are much more complex than those with fixed ones. Focusing on this sort of complex spacecraft, the attitude dynamics model is discussed and analyzed briefly in this paper, and then the uniform bounded stability of the output feedback based PD control system is proved theoretically. In order to guarantee the asymptotic stability of the system, an internal model based control system is constructed, and then the stability proof is given based on Lyapunov theory. With the model parameters published by the American geostationary meteorological satellite GOES 8, the two kinds of controllers are simulated and compared with each other. This paper draws the concluding remarks and proposes a possible research topic in the end.

Key words: Sun tracking solar array, Internal model principle, Flexible satellite, Attitude control

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