Direct adaptive control-based reconfiguration flight control system

In general, the failure information is needed in the design of reconfiguration flight control system. However, no failure information is required for reconfiguration actuator failures by using the direct adaptive control scheme. Moreover, a fault aircraft perfectly tracks the output trajectory of the reference model. A feedback compensator is designed by utilizing the optimization method in order to ensure the strictly positive real of the failure plants. The asymptotical stability of the adaptive reconfiguration systems is proved by applying Lyapunov function. The proposed scheme is applied to the design of a lateral motion of an aircraft. The results show that an aircraft has good dynamic performance in the condition of control surface failure.