Design of Aircraft Control System Based on Adaptive Optimal Control

For the uncertainty of the aircraft dynamics parameters, the adaptive control method was used to design the control parameters so as to ensure the stability of the aircraft control system. When designing the reference model of the controller, the linear quadratic optimal control method was used to make the reference model behave as a typical second-order link. Based on the Lyapunov stability theory, the self-adaptation law was deduced to ensured the closed-loop stability of the system. The simulation results showed that the control method designed in this paper can keep track of the reference model when the aircraft dynamics parameters changed.