A Longitudinal Automatic landing System Design Based on Recursive Sliding Mode Dynamic Surface Control With Nonlinear Gains under icing condition

Abstract

This paper presents a recursive sliding mode dynamic surface control method with nonlinear gains for the design of a nonlinear aircraft auto-landing controller under icing condition. The landing maneuver is formulated into a flight path tracking problem based on longitudinal iced aircraft dynamic model. The reference landing trajectory is designed according to the FAA rules. By introducing a function with nonlinear gains and developing a recursive sliding mode dynamic surface control method, the controller is established and it can guarantee precise tracking of flight-path angle of the system with the change of aerodynamic coefficients due to icing and the influence of external disturbance. The stability of control system is analyzed that all the signals of the control system are semi-global uniform ultimately bounded. The ultimate tracking error of the flight-path angle can be made arbitrarily small. Simulation results show the excellent tracking of the proposed strategy.