Control System Design of a Vertical Take-off and Landing Fixed-Wing UAV

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, VTOL-FW UAV's flight characteristics are expected to be improved by enabling agile maneuvers, increasing survivability and exploiting full flight envelope capabilities. (C) 2016, IFAC (International Federation of Antomatic Control) Hosting by Elsevier Ltd. All rights reserved.


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...
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In this thesis, design of a flight control system for an uncommon quadrotor aerial vehicle is discussed. This aerial vehicle consists of two counter-rotating big rotors on longitudinal axis to increase the lift capacity and flight endurance, and two counter-rotating small tilt rotors on lateral axis to stabilize the attitude. Firstly, full nonlinear dynamic model of this vehicle is obtained by using Newton-Euler formulation. Later, derived approximate linear model around hover is statically decoupled to sim...
Design, modeling and control of a hybrid UAV
Muratoğlu, Abdurrahim; Tekinalp, Ozan; Department of Aerospace Engineering (2019)
Vertical takeoff and landing (VTOL) vehicles that can fly like conventional airplanes after the takeoff, provide a promising area to find applications in the future. These hybrid vehicles combine the advantages of rotary-wing and fixed-wing aircraft configurations such as having capability of hovering flight, takeoff and landing without utilizing a runway, long range, high speed flight with reasonable endurance. In this study, a tilt-rotor tricopter VTOL UAV having a conventional fixed-wing airframe is desi...
Control allocation for a multi-rotor e-vtol aircraft using blended-inverse
Aksoy, Emre; Yavrucuk, İlkay; Department of Aerospace Engineering (2021-2-25)
In this thesis, the control allocation problem in a flight control system design for a multi-rotor eVTOL (electric Vertical Takeoff and Landing) aircraft is proposed. The vehicle consists of 20 identical rotors that are used as flight control actuators. The dynamic system is a MIMO (Multi Input Multi Output) system with more inputs than outputs, i.e. there are many solutions of the control problem. The objective is to find an efficient and redundant control solution that provides sufficient flight performan...
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 ...
Citation Formats
F. Cakici and M. K. Leblebicioğlu, “Control System Design of a Vertical Take-off and Landing Fixed-Wing UAV,” 2016, vol. 49, Accessed: 00, 2020. [Online]. Available: