宇航学报

宇航学报 ›› 2020, Vol. 41 ›› Issue (8): 1058-1066.doi: 10.3873/j.issn.1000-1328.2020.08.009

• 制导、导航、控制与电子 • 上一篇    下一篇

航天器姿态大角度机动有限时间控制

黄成，王岩，邓立为   

  1. 1. 哈尔滨理工大学自动化学院，哈尔滨150080；2. 哈尔滨工业大学控制科学与工程系，哈尔滨150001
  • 收稿日期:2019-05-24 修回日期:2019-10-10 出版日期:2020-08-15 发布日期:2020-08-25
  • 基金资助:
    国家自然科学青年基金（61806060）；黑龙江省自然科学基金(LH2019F024)

Finite Time Control for Spacecraft Attitude Large Angle Maneuver

HUANG Cheng, WANG Yan, DENG Li wei   

  1. 1. School of Automation, Harbin University of Science and Technology, Harbin 150080, China; 2. Department of Control Science and Engineering, Harbin Institute of Technology, Harbin 150001, China
  • Received:2019-05-24 Revised:2019-10-10 Online:2020-08-15 Published:2020-08-25

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摘要： 针对航天器姿态大角度机动控制问题，在存在外部扰动的情况下，基于航天器姿态跟踪系统的标准级联特性，利用反步法和自适应控制设计有限时间控制器。提出的控制方法可以严格保证姿态大角度机动系统是全局有限时间稳定的。李雅普诺夫理论推导和仿真结果表明，系统在控制器的作用下可以快速机动到平衡点并保持稳定，全物理仿真试验进一步表明了所提出的控制方法的有效性和优越性。

关键词: 姿态大角度机动, 反步法, 有限时间控制, 自适应控制, 全物理仿真

Abstract: For attitude large-angle maneuver control of spacecraft, according to the standard cascading characteristic of the spacecraft attitude tracking system, a finite-time controller is designed by using the backstepping method and the adaptive control under the condition of external disturbances existing. The proposed controller can strictly guarantee that the attitude large-angle maneuver system is finite-time stable globally. The Lyapunov theory and simulation results show that the system can quickly maneuver to the equilibrium point and hold steady. The full-physical simulation experiments also demonstrate the effectiveness and superiority of the proposed control scheme.

Key words: Attitude large-angle maneuver, Backstepping method, Finite-time control, Adaptive control, Full-physical simulation

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