ABSTRACT
To overcome the shortcomings of the preceding research for spacecraft attitude control systems, in this work a novel fault-tolerant attitude control strategy is addressed for flexible spacecraft in the presence of actuator faults, uncertainty inertia matrix and external disturbances. The proposed fault-tolerant attitude controller is designed by using the adaptive Lyapunov methodology and the inverse optimal technique for stabilizing systems, which is shown to be optimal with respect to a family of cost functional and achieves H
∞ distur-
bance attenuation without solving the associated HJIPD equation directly. Meanwhile, the derived control law can achieve the goal of fault-tolerant control without the need of any fault detection and isolation mechanism to determine the fault information.
