An automatic landing system for an unmanned aerial vehicle (UAV) is presented in the following paper. The nonlinear aircraft model with thrust, elevator, rudder and aileron deflections as control inputs is established using the appropriate aerodynamic data. The flight trajectory the airplane is expected to travel during landing is then defined. A nonlinear control law, using feedback linearization method, is designed to develop the automatic landing controller for the UAV aircraft. A linear state-feedback control law is also designed for means of comparison with the nonlinear controller. The elevator is employed for longitudinal control whereas the rudder and aileron aid in lateral control. Thrust is the control input for velocity control, which is held constant during landing. A nonlinear simulation, incorporating wind shear and ground effects, is run using MATLAB/Simulink to assess the controllers’ integrity. The auto-landing system designed in this paper is meant to increase the autonomy of the UAV to eventually reach a fully autonomous system. Simulation results show the importance of designing the controller considering such effects. Landing trajectory tracking performance by the nonlinear controller is of great tone.
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ASME 2011 International Mechanical Engineering Congress and Exposition
November 11–17, 2011
Denver, Colorado, USA
Conference Sponsors:
- ASME
ISBN:
978-0-7918-5493-8
PROCEEDINGS PAPER
A Nonlinear Automatic Landing Control System for a UAV Available to Purchase
Ghassan M. Atmeh,
Ghassan M. Atmeh
The University of Texas at Arlington, Arlington, TX
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Wahba I. Al-Taq,
Wahba I. Al-Taq
ALPHA Ref. & A/C Est., Amman, Jordan
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Zeaid Hasan
Zeaid Hasan
Texas A&M University, College Station, TX
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Ghassan M. Atmeh
The University of Texas at Arlington, Arlington, TX
Wahba I. Al-Taq
ALPHA Ref. & A/C Est., Amman, Jordan
Zeaid Hasan
Texas A&M University, College Station, TX
Paper No:
IMECE2011-63264, pp. 383-392; 10 pages
Published Online:
August 1, 2012
Citation
Atmeh, GM, Al-Taq, WI, & Hasan, Z. "A Nonlinear Automatic Landing Control System for a UAV." Proceedings of the ASME 2011 International Mechanical Engineering Congress and Exposition. Volume 7: Dynamic Systems and Control; Mechatronics and Intelligent Machines, Parts A and B. Denver, Colorado, USA. November 11–17, 2011. pp. 383-392. ASME. https://doi.org/10.1115/IMECE2011-63264
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