Generalized Linear Quadratic Gaussian and Loop Transfer Recovery Design of F-16 Aircraft Lateral Control System

recovery method has been quite popular for aircraft control system design. In the proposed method we derive an optimal control law to minimize a generalized linear quadratic performance index to achieve better recovery quality in the LTR process and better some performance in time-domain responses and frequency-domain responses as well. The resulting controller can achieve a prescribed degree of stability even in the face of a non-minimum phase problem. Finally, the numerical simulation of an optimal lateral control system for an F-16 aircraft demonstrates the proposed method can provide good robustness and performance properties in both time-and frequency-domain responses.