Abstract:

Aiming at the attitude control problem of spacecraft with actuator faults, a novel method for designing faulttolerant  controller is proposed based on adaptive fast terminal sliding mode control. The method could improve the convergent rate  of the spacecraft faulttolerant controller and guarantee the finitetime stability by selecting the sliding mode  surface with fast terminal feature. Furthermore, an adaptive control method is designed with the outcome of regulating  controller parameters online and eliminating the dependence of faultminimuminformation. Numerical simulation  demonstrates that the proposed method could achieve effective spacecraft faulttolerant control. Specifically, when  compared with the traditional sliding mode method, the convergent rates of attitude angle and angle rate decreased by  54.5% and 50% respectively, as well as the improvement of the robustness.