基于输入受限的轨控期间挠性卫星容错控制研究  

Fault-tolerant Control Under Constrained Input for Flexible Satellite Attitude Control System during Orbit Control

作　　者：傅艳萍[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》2012年第3期38-44,共7页Aerospace Control

基　　金：国家自然科学基金(61034005);江苏省自然科学基金(BK2010072)资助

摘　　要：轨控期间的卫星由于推力器安装偏差,实施推力时会产生较大的干扰力矩,直接影响到卫星姿态稳定。除此,考虑到执行机构提供的力矩是有限的,为保证系统的稳定性,需在设计控制器的过程中考虑输入受限问题。本文针对卫星执行机构故障情况,综合考虑输入受限和干扰问题,提出一种基于输入受限的挠性卫星姿态容错控制策略,并开展了仿真试验,验证了本文设计的姿态容错控制器的有效性。During orbit control for a flexible satellite, large disturbance torque may be caused by the misalignments, which would affect the satellites＇ attitude directly. Besides, actuators can just provide limited torque because of physical property. And input saturation should be considered to guarantee the system sta- bility. In this paper, with actuator fault and the problems mentioned above considered, we propose a toler- ant control method based on input saturation for flexible satellite attitude control system. Finally the per- formance of the proposed fault tolerant controller is demonstrated via numerical simulation forflexible satellite during orbit control.

关 键 词：挠性卫星 变结构 容错控制 输入受限 飞轮故障 

分 类 号：V448.221[航空宇航科学与技术—飞行器设计]