宇航学报

宇航学报 ›› 2015, Vol. 36 ›› Issue (4): 419-429.doi: 10.3873/j.issn.1000-1328.2015.04.008

• 制导、导航与控制 • 上一篇    下一篇

欠驱动挠性航天器的全姿态控制

张洪华，王芳，胡锦昌，王泽国   

  1. 北京控制工程研究所，北京100190
  • 收稿日期:2014-05-19 修回日期:2014-10-29 出版日期:2015-04-15 发布日期:2015-04-25
  • 基金资助:

    国家青年自然科学基金资助项目(61403031)

All Attitude Control for Underactuated Flexible Spacecraft

ZHANG Hong hua, WANG Fang, HU Jin chang, WANG Ze guo   

  1. Beijing Institute of Control Engineering， Beijing 100190，China
  • Received:2014-05-19 Revised:2014-10-29 Online:2015-04-15 Published:2015-04-25

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摘要：

考虑欠驱动挠性航天器姿态控制问题，其中执行机构配置为两轴喷气和飞轮执行机构。提出了“喷气消旋＋飞轮机动”的分段控制方法，其基本思想是：首先利用喷气推进执行机构使航天器整星角动量趋于零，为飞轮控制做准备；然后利用飞轮执行机构使航天器从任意姿态转向指定姿态并维持。针对“喷气消旋”，说明了提出的控制规律能够保证航天器角动量全局渐近收敛于任意小量；针对“飞轮机动”，证明了航天器全姿态具有大范围渐近稳定性；针对“喷气消旋＋飞轮机动”的完整过程，采用扰动系统理论分析了闭环控制系统的大范围终端有界性。

关键词: 欠驱动航天器, 挠性航天器, 姿态控制, 姿态角速度, 渐近稳定性

Abstract:

The all-attitude control of underactuated flexible spacecraft configured with jets and flywheels as actuators only in two body axes is considered. The control method called jets despinning plus flywheels slewing is proposed. The main idea contains two steps: the first is to damp the attitude angular velocity by use of jet actuators, the second is to slew the attitude to the target attitude by use of flywheels. The control laws are given and the asymptotical stability of the closed-loop system is proved. Finally, the globally ultimate boundness of the real attitude closed-loop system is analyzed. Theoretical analysis and the simulation results demonstrate the effectiveness of the proposed control method.

Key words: Underactuated spacecraft, Flexible spacecraft, Attitude control, Attitude angular velocity, Asymptotical stability

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