Robust maneuvering control design of an aircraft via dynamic inversion and μ-synthesis

Abstract

Abstract

In this research, a robust controller for a nonlinear model of an aircraft with unmodelled dynamic uncertainty is designed. The closed-loop system (aircraft) should remain stable and perform manoeuvring acceptably. By using the ‘Dynamic Inversion Method’ the nonlinear responses are transformed into linear ones. Then, using the μ-analysis and synthesis technique a robustly performed controller is designed against uncertainties and control-surface limitations. Next, the actual response of the aircraft is computed using simulation. Finally, the order of the controller is reduced and the same analysis is repeated for the reduced order controller. It shows that the controller performs robustly and stably.