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Hovering Control of a Tilt-Wing UAV
Date
2019-09-20
Author
Çakır, Hasan
Kurtuluş, Dilek Funda
Metadata
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In this study, the design and analysis of hovering controller of an UAV which is capable of doing vertical take-off and landing using the fixed six rotors placed on the tilt-wing and tilt-tail will be explained. The aircraft will have four rotors on the wing and two rotors on the tail. The main wing and horizontal tail will be capable of 90° tilting. Whole flight is separated into three flight modes, which are VTOL, Transition and Forward Flight, to have a robust control on aircraft. Only hover control of the VTOL mode will be explained in this study. Both aerodynamic and thrust forces will be used to control the aircraft during VTOL mode. MATLAB/Simulink simulations will be employed to show that the aircraft is capable of VTOL. By means of this study, it is aimed to bring an aircraft, which is capable of taking off from all platforms and reconnaissance and surveillance thanks to its hovering capability, in use.
Subject Keywords
Tilt wing mechanism
,
VTOL
,
Unmanned air vehicles
URI
https://hdl.handle.net/11511/72422
Conference Name
10th Ankara International Aerospace Conference (18 - 20 Eylül 2019)
Collections
Department of Aerospace Engineering, Conference / Seminar
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BibTeX
H. Çakır and D. F. Kurtuluş, “Hovering Control of a Tilt-Wing UAV,” presented at the 10th Ankara International Aerospace Conference (18 - 20 Eylül 2019), Ankara, Türkiye, 2019, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/72422.
