Robust Adaptive Fault-Tolerant Control of High-Speed Flight Vehicle via High-Order Sliding-Mode Differentiator

This paper proposes a robust adaptive fault-tolerant control method for a high-speed flight vehicle encountering actuator faults. By using a low-pass filter to augment the system, a chattering-reduced control input signal can be constructed. A neural network is employed to approximate the unknown nonlinear terms containing actuator faults. The attitude angle derivatives used in controller design are estimated by the high-order sliding mode differentiator, and robust adaptive technique is integrated into the controller design to update the control signals for attenuating the adverse effects induced by the faults. Finally, the uniformly ultimate boundedness of closed-loop system signals is proven by Lyapunov theory, and simulation results are presented to validate the effectiveness of the proposed scheme.