Application of the feedback decoupling method in the attitude control of the rolling aircraft

Considering the existence of the coupling effects that are distributed in the seeker loop, the actuators, the aerodynamic forces and the sensitive devices of the rolling aircraft, it will to some extend affect the control quality and add difficulty to the design of the control system. And in condition of strong coupling, the success or failure of the whole control system may even be affected. This paper focuses on the feedback decoupling theory the in time domain and its application in attitude control of the rolling aircraft. Firstly, the linear state feedback decoupling theory is discussed based on square system. Subsequently, for a special integral system, a simple and intuitive method is proposed to realize pole assignment of the decoupling system and obtain the expected closed loop characteristics through the comparison of closed-loop characteristic polynomial. Then, the dynamics model of the rolling aircraft is established including the body dynamics link and the actuator dynamics link. At last, an integrated design example is given as an application in the rolling aircraft control system. The simulation results have verified the validity of this method.