Linear Quadratic Regulation Method for a Roll Yaw Coupled Supersonic Flight Vehicle

Abstract

In this literature, a linear quadratic regulation (LQR) method with controller reconfiguration and state observer is proposed for analyses and designs of a supersonic roll-yaw coupled flight control system. The flight control system of some specially shaped airframe can be decomposed into a Pitch Control System and a Roll-Yaw Coupled Control System. It can be designed separately, no need for three loops to be designed together. The design process is relatively simple, which is conducive to the design of flight control systems in large airspace. The proposed method for the considered system will give the good tracking characteristic at low frequencies and robustness at middle frequencies; simultaneously. All state variables are measurable and found controllers are all realizable either in analog or digital hardware.