Hovering Control of a Tilt-Wing UAV

Çakır, Hasan
Kurtuluş, Dilek Funda
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.


Design and analysis of a VTOL Tilt-Wing UAV
Çakır, Hasan; Kurtuluş, Dilek Funda; Department of Aerospace Engineering (2020)
In this study, the design and analysis of a UAV, which is capable of vertical take-off and landing using fixed six rotors placed on the tilt-wing and tilt-tail, will be explained. The aircraft has four rotors on its wing and two rotors on its tail. The main wing and horizontal tail are capable of 90° tilting. Both aerodynamic and thrust forces are used during VTOL, transition, and forward flight. Aerodynamic analysis has been performed in ANSYS Fluent v.18. A non-linear six DoF model, involving a 3D CAD mod...
Optimal Design of a Miniature Quad Tilt Rotor UAV
Kahvecioglu, Ahmet Caner; Alemdaroglu, Nafiz (2015-06-12)
This paper describes the design procedure of a convertible miniature (mini and micro) quad tilt rotor unmanned air vehicle (UAV), which has about 2 meters of wing span, one hour of mission time and 5 kilograms of total weight. The aircraft is driven by four brushless direct current motors, and the structure of it completely made of composite materials. When the wing and tail of the aircraft are dismounted, it operates as a quad- rotor with tilting rotors. The aircraft is planned to carry a gimbal camera wei...
Control System Design of a Vertical Take-off and Landing Fixed-Wing UAV
Cakici, Ferit; Leblebicioğlu, Mehmet Kemal (2016-05-20)
In this study, design and implementation of control system of a vertical take-off and landing (VTOL) unmanned aerial vechicle (UAV) with level flight capability is considered. The platform structure includes both multirotor and fixed-wing (FW) conventional aircraft control surfaces: therefore named as VTOL-FW. The proposed method includes implementation of multirotor and airplane controllers and design of an algorithm to switch between them in achieving transitions between VTOL and FW flight modes. Thus, VT...
Control system design and implementation of a tilt rotor UAV
Cevher, Levent; Tekinalp, Ozan; Department of Aerospace Engineering (2019)
In this thesis, a hybrid vertical take off and landing unmanned air vehicle platform is designed and developed. The platform uses tricopter configuration for takeoff and landing while it uses its fixed wings for forward flight. Control algorithms are developed for the VTOL aircraft. For this purpose, first nonlinear simulation code is developed in Matlab/Simulink environment. The simulation uses the wind tunnel experimental data for the propellers and aerodynamic data obtained from a package program XFLR 5 ...
Aerodynamic design and control of tandem wing unmanned aerial vehicle
Kaya, Taşkın; Özgen, Serkan; Department of Aerospace Engineering (2019)
This thesis presents an approach towards the design methodology of electrical propulsion, tandem wing unmanned aerial vehicle. Due to its possible rewarding features, tandem wing design is investigated as the main subject of this study. The stability and control characteristics of tandem wing aircraft are critical since the interference between the two wings may result in nonlinear aerodynamic characteristics for varying angles of attack. Thus, the design of the controller system requires careful handling, ...
Citation Formats
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.