Papers by Keyword: Automatic Landing

Abstract: This paper presents the soft control strategies for automatic landing of Unmanned Aerial Vehicle and simulation the result of controller. The soft controller parameters can be modify and show off the results response of control surface of Unmanned Aerial Vehicle which can fly to the desirable waypoints along the flight plan, one may freely select a control scheme to stabilize and perform the target tracking with robustness. The main control system of Unmanned Aerial Vehicle is developed from Fuzzy PD+I controller with auto-tuning gain parameters and the simulation is carried out by Matlab/Simulink simulation program including with Aerosim toolbox software. The model of Unmanned Aerial Vehicle for simulation in this paper is selected the model of Aerosonde UAV from Aerosonde PTY LTD., which is developed mathematical model by Unmanned Dynamics.

Abstract: Since the angled deck is only tens miles width, the task of landing an aircraft on an aircraft carrier requires precise control, especially lateral loop. For this problem, this paper focuses on researching the aircraft automatic landing lateral control. In lateral control, the most crucial parts are controlling the off center distance and keeping the desired landing attitude. So firstly a nonlinear kinetic model of aircraft landing in lateral directional axis is established, and then transformed into error states. The controller is designed for an angle of attack of 11.7 deg and an airspeed of 40m/s, the equilibrium point. Receding horizon control methodology is employed to solve the aircraft lateral control problem. This controller is solved in MATLAB, and sent to the 3D simulation environment by network communication, to control the aircraft landing lateral loop. The simulation environment is programmed based on VC++ software. The simulation results show that receding horizon control method can achieve trajectory tracking and attitude tracking of nonlinear aircraft landing system.

Abstract: The CAT III longitudinal automatic landing control laws based on multi-objective optimization is discussed. Firstly summarized the CAT III airworthiness criteria and transformed into the specifications of control system. The configuration of the longitudinal automatic landing controllers is proposed secondly and multi-objective optimization is used to tradeoff free parameters of the controllers. The Monte Carlo simulation results show the designed control laws fulfill the CAT III requirements, when there are uncertainties of structure, measurement error and disturbances.