High Performance Controller Design Using Linear Matrix Inequalities for Pitch Angle Regulation of Aircraft

This paper proposes high performance proportional integral derivative (PID) controller for the pitch angle regulation of aircraft. The proposed controller is modeled by using linearized model of aircraft. The linear matrix inequality method has been used to achieve the optimum performance of the controller. The motivation of designing the controller is to stabilize the pitch angle deviation of an aircraft in an acceptable range. The performance of the proposed controller is simulated by using Matlab and compared with conventional linear quadratic regulator (LQR) controller. The results show that the LMI PID controller achieves the high performance for pitch angle control of aircraft.