Automatic landing controller design and simulation of flying-wing unmanned aerial vehicle

Abstract

A method of guidance and control for automatic landing of flying-wing unmanned aerial vehicle (UAV) is proposed in this paper. Based on wind tunnel data of a flying-wing aircraft, small disturbance equations of the flying-wing aircraft is built using MATLAB. With the help of the model, automatic landing plan and control law is designed. Simulation and analysis are finished based on non-linear equations. The final simulation results show that the guidance and control law can meet the requirements of automatic landing of UAV, and has excellent static and dynamic performances.