Sliding mode fault tolerant control for over-actuated aircraft

This paper proposes an integral sliding mode fault tolerant control scheme for over-actuated aircraft, which has fault reconstruction error and time delay, position and rate limiting. The instruction restricts module is used to limit control command saturation and instantaneous disturbance. An integral siding mode control law is designed to ensure system stability with fault reconstruction error and time delay. The simulation results show good track performance, as well as the robust and tolerant ability.