Aircraft Attitude Control on High-order Fully Actuated System Theory

In this paper, a second-order fully actuated system model is derived for a six degree of freedom aircraft model with control coupling. Then a three channel joint optimal attitude control method of roll, yaw and pitch is designed on high-order fully actuated system theory. Through mathematical simulation of this controller and the traditional PID controller, it is shown that the PID control method has a great shortage in the aircraft with control coupling, and the fully actuated system theory control method can well solve the problem of aircraft coupling, achieve the stable tracking of aircraft attitude command, and has better rapidity.