Linear Feedback and LQR Controller Design for Aircraft Pitch Control

摘要

In this paper, the pitch control system of aircraft is designed using Linear Feedback and Linear Quadratic Regulator (LQR) approach. The model we used in this research work is F-16 aircraft model. As the controllers we used can be applied to the linear system, so we used linearized aircraft model. Pole placement technique is used to find the value of feedback gain K for Linear Feedback Controller. The value of feedback gain matrix K in LQR control technique is calculated by choosing suitable values of Q and R matrices, where Q and R are weighing matrix. Block diagrams, MATLAB simulation diagrams, and Simulation results are presented. Finally, according to the initialization of state space vector, the response of pitch control system is analyzed and compared the performance of both controllers.