轨控期间挠性卫星姿控系统的容错控制  

Adaptive Backstepping Fault-tolerant Control for Flexible Satellite Attitude Control System during Orbit Control

作　　者：张娴[1] 程月华[1,2] 姜斌[1] 

机构地区：[1]南京航空航天大学自动化学院,南京210016 [2]南京航空航天大学高新院小卫星工程技术研究中心,南京210016

出　　处：《航天控制》2011年第1期41-47,共7页Aerospace Control

基　　金：江苏省自然科学基金(BK2010072)资助

摘　　要：卫星在实施轨道控制期间,轨道机动推力会影响卫星的姿态稳定。本文针对存在推力干扰的挠性卫星,研究执行器故障情况下姿控系统的容错控制问题。首先设计一种基于反步自适应变结构的被动容错控制器实现姿态稳定,在此基础上,采用分布式智能部件作为执行器,设计补偿项以更好地抑制挠性结构的振动和常值变形。最后,以轨控期间挠性卫星姿态控制系统的飞轮故障为应用实例进行数值仿真。仿真结果验证了本文所设计的姿态容错控制器的有效性和可行性。During orbit control for a flexible satellite,the orbit control force would affect the satellites＇ attitude.An adaptive backstepping fault-tolerant control method is proposed for the attitude stabilization problem of flexible spacecraft attitude control system with actuator faults.For actively damping the excited elastic vibrations and constant deformation,the strain-rate feedback control is also employed by using piezoelectric materials as additional sensors and actuators.Finally,the proposed robust fault tolerant control method is applied to a flexible satellite attitude control system in the presence of failures of reaction wheels.Simulation results demonstrate the effectiveness of the fault tolerant control method and the vibration and deformation suppression is also achieved.

关 键 词：挠性卫星 姿态控制 反步自适应变结构 振动抑制 容错控制 

分 类 号：V448.221[航空宇航科学与技术—飞行器设计]