Abstract:This paper studies an attitude control and vibration suppression problem for flexible spacecrafts under actuator faults, using a model transform based adaptive control technique. In order to describe the strong coupling features between the rigid body and flexible motion, the hybrid system dynamics is modeled by an interconnected partial differential equation-ordinary differential equation. A couple of auxiliary signals are designed to establish the relation between the boundary conditions and internal dynamics. A novel adaptive fault-tolerant boundary control scheme is developed to ensure the asymptotic tracking performance and vibration suppression. A complete stability analysis is provided by using the modified Lyapunov method and extended LaSalle invariance principle. A simulation study on the attitude control system of flexible spacecrafts effectively verifies the validity of the developed theoretical results.