宇航学报

宇航学报 ›› 2018, Vol. 39 ›› Issue (6): 683-689.doi: 10.3873/j.issn.1000-1328.2018.06.011

• 制导、导航、控制与电子 • 上一篇    下一篇

转动惯量未知的再入飞行器姿态容错控制

刘伟星，耿云海，吴宝林   

  1. 哈尔滨工业大学卫星技术研究所，哈尔滨 150080
  • 收稿日期:2017-09-04 修回日期:2018-02-08 出版日期:2018-06-15 发布日期:2018-06-25

Inertia Free Fault Tolerant Attitude Tracking for a Lifting Reentry Vehicle

LIU Wei xing, GENG Yun hai, WU Bao lin   

  1. Research Center of Satellite Technology, Harbin Institute of Technology, Harbin 150080, China
  • Received:2017-09-04 Revised:2018-02-08 Online:2018-06-15 Published:2018-06-25

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摘要：

针对升力式再入飞行器再入过程中执行机构发生故障的情况，基于反步法思想，设计了一种无需飞行器转动惯量信息的姿态容错控制律，同时，该控制律能有效地抑制外界干扰。控制律的设计除了给出稳定性证明外，还给出了误差上界与控制参数的关系。以临近空间飞行器X-33为模型进行了数学仿真，结果表明了该控制律的有效性。

关键词: 再入飞行器, 姿态跟踪, 容错控制, 反步法

Abstract:

An inertia-free fault-tolerant attitude tracking law is proposed for a lifting reentry vehicle with the actuator faults. The proposed control law is based on the backstepping control. The effect on attitude control performance by the external disturbance is also suppressed by the proposed control law. The stability of the control law is ensured. Furthermore, the relationship between the upper bound of the tracking error and the design parameter is also given in this paper. To demonstrate the efficiency of the method, the simulation of X-33 vehicle in reentry mode is carried out.

Key words: Reentry vehicle, Attitude tracking, Fault tolerant control, Backstepping control

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