Title :
Automatic landing controller design and simulation of flying-wing unmanned aerial vehicle
Author :
Zhang Jianfeng ; Jia Caijuan
Author_Institution :
365 Instn., NorthWestern Polytech. Univ., Xian, China
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.
Keywords :
aerospace computing; aircraft landing guidance; autonomous aerial vehicles; control engineering computing; control system synthesis; mathematics computing; nonlinear equations; wind tunnels; Matlab; UAV; automatic landing controller design; automatic landing plan; control law; flying-wing aircraft; flying-wing unmanned aerial vehicle simulation; nonlinear equations; small disturbance equations; wind tunnel data; Elevators; Equations; Mathematical model; Silicon; automatic landing; flying-wing; simulation; unmanned aerial vehicle;
Conference_Titel :
Measurement, Information and Control (ICMIC), 2013 International Conference on
Conference_Location :
Harbin
Print_ISBN :
978-1-4799-1390-9
DOI :
10.1109/MIC.2013.6758104
