TY - GEN
T1 - H-infinite based adaptive fault-tolerant control and active vibration suppression of flexible satellite during orbit maneuver
AU - Shi, Xiaoping
AU - Yang, Jing
AU - Li, Long
AU - Liu, Hailong
N1 - Publisher Copyright:
© 2014 IEEE.
PY - 2015/1/12
Y1 - 2015/1/12
N2 - A nonlinear fault-tolerant control and active vibration suppression design approach is presented in this paper. In the presence of flexible satellite with actuator faults, orbit control force and environment disturbance, a nonlinear adaptive fault-tolerant control approach is designed for the flexible satellite attitude control system. The control law is based on H-infinite adaptive method and designed to stabilize the attitude system under actuator failures cases and its stability analysis is given by Lyapunov function. On this basis, an active vibration suppression compensator is designed to increase the attitude control accuracy and decrease the influence of flexibility on system stability by using similar design method. At last, the fault-tolerant control and vibration suppression design approach is applied to the flexible satellite attitude system in the reaction flywheel failures cases. The simulation results which demonstrate the fault-tolerant ability and vibration suppression performance can be successfully achieved.
AB - A nonlinear fault-tolerant control and active vibration suppression design approach is presented in this paper. In the presence of flexible satellite with actuator faults, orbit control force and environment disturbance, a nonlinear adaptive fault-tolerant control approach is designed for the flexible satellite attitude control system. The control law is based on H-infinite adaptive method and designed to stabilize the attitude system under actuator failures cases and its stability analysis is given by Lyapunov function. On this basis, an active vibration suppression compensator is designed to increase the attitude control accuracy and decrease the influence of flexibility on system stability by using similar design method. At last, the fault-tolerant control and vibration suppression design approach is applied to the flexible satellite attitude system in the reaction flywheel failures cases. The simulation results which demonstrate the fault-tolerant ability and vibration suppression performance can be successfully achieved.
UR - https://www.scopus.com/pages/publications/84922496527
U2 - 10.1109/CGNCC.2014.7007560
DO - 10.1109/CGNCC.2014.7007560
M3 - 会议稿件
AN - SCOPUS:84922496527
T3 - 2014 IEEE Chinese Guidance, Navigation and Control Conference, CGNCC 2014
SP - 2500
EP - 2505
BT - 2014 IEEE Chinese Guidance, Navigation and Control Conference, CGNCC 2014
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 6th IEEE Chinese Guidance, Navigation and Control Conference, CGNCC 2014
Y2 - 8 August 2014 through 10 August 2014
ER -