Aircraft Middle and Final Stage Attitude Control on Fully Actuated System Theory

This paper takes the attitude control of the middle and final stages of the aircraft as the research background, and explores a new nonlinear control method for the strong nonlinearity, strong coupling, fast time-varying and uncertainty characteristics of the aircraft. A second-order fully actuated system model of the aircraft is constructed, which is starting from the six degree of freedom mathematical model, including aerodynamic coupling and control coupling. It is a nonlinear model, including roll, yaw and pitch full three channels. Also, the paper designed an attitude controller on fully actuated system, which is based on the PD control method, and proved the stability of the controller through Lyapunov stability analysis method. Then, the controller is integrated into the aircraft simulation, and mathematical simulation verification is carried out under benchmark conditions, achieving good attitude control effect.