Dynamic inversion fuzzy integration control in high angle-of-attack flight

A method for design of flight controllers that provides desired handling qualities over a wide range of flight conditions is presented. The aircraft considered in this paper is capable of flight at very high angles of attack and has thrust vectoring as well as conventional aerodynamic control surfaces. This paper only considers the longitudinal control. The control design method is to use an inner-loop, dynamic inversion controller and an outer-loop, the main-auxiliary fuzzy controller without quantification. The dynamic inversion controller linearizes the pitch rate dynamics of the aircraft. However, since model uncertainties prevent exact linearization, there will always be errors associated with this controller. The outer-loop fuzzy controller provides robustness to errors due to the lack of exact cancellation of the pitch rate dynamics by the dynamic inversion controller. In addition, its simulation results ate also provided.