Adaptive fault-tolerant control design for hypersonic flight vehicles based on feedback linearization

In this paper, an adaptive feedback linearization controller is developed for the longitudinal dynamics of hypersonic flight vehicle with unknown parameters and actuator failures. First, the relative degree of the system is obtained by calculating the derivatives of the output repeatedly. Then, full-state feedback is applied to linearize the dynamics of the air vehicle. A nominal controller is developed to track the reference trajectory. When an actuator failure occurs, a fault-tolerant controller is designed to accommodate its effect. Adaptive laws are designed to update the parameters to implement the adaptive controller. Closed-loop stability and asymptotic output tracking are ensured. Simulation results verify the effectiveness of adaptive actuator failure compensation for the desired system performance.