Design of Automatic Landing Systems Using Mixed H/H Control

Abstract

Mixed H2/HX control technique is employed to develop controllers for auto-landing systems for a commercial airplane. A linear model of the aircraft in longitudinal motion is established using the appropriate aerodynamic coefficients. With the control actuator, tracking errors, and altitude motion, the aircraft is shown to be governed by an augmentation system along with its filter model. Two kinds of optimal and robust control requirements are designed, which need to be satisfied simultaneously. One of requirements is with respect to an optimal trajectory selection for landing routes. The H2 method is used to minimize a cost function such that the optimal gain for trajectory optimization can be obtained. The other requirement is with respect to the disturbance attenuation. The Hm technique is employed to obtain the necessary formulation for the robust control gain to minimize the affection of the disturbance to the performance output. An algorithm is developed based on the convex theory for the mixed H2I Hn control and filter gains, which provides a suboptimal solution. A large commercial aircraft (Boeing 747-200) is employed to illustrate the potential of the proposed method. It is shown that the glide slope capture motion and flare maneuver of the aircraft are accomplished quite well, and the amplitudes of all maneuver are within FAA requirements. L INTRODUCTION Control of aircraft under difficult maneuvers is a problem of both theoretical and practical interest. Control under one of these difficult maneuvers, that of landing, is discussed and addressed in this paper. Design of automatic landing systems has been achieved using both robust and optimal control methods [1-3]. Reference [1] employed the #„ synthesis to design an automatic landing controller for an F-14 aircraft. Design of landing systems encountering windshear is given in