Modelling of an articulated flying body and control system design

Güzelcan, Burçin Tutku
This study presents the conceptual design of an articulated coaxial rotor Unmanned Air Vehicle (UAV) with three-dimensional dynamical models and a control strategy. Conventional rotary-wing aircrafts operate maneuvers via swashplates which is a complex mechanism adding bulky elements to the aircrafts. While designing light weight UAVs, there appears a need for less complex and compact mechanisms for maneuverability rather than swashplates. There are different methods and mechanisms to acquire maneuvering without swashplates. Three DoF Stewart Mechanism as means of articulation forms a base platform for the coaxial rotor in this design. The Steward Mechanism is designed to tilt the coaxial rotor shaft connected to its upper platform to perform maneuvers. The coaxial rotor tilted by the Steward Mechanism provides a beneficial design with reduced complexity, enhanced maneuverability and agility.


Unlusoy, Levent; Şahin, Melin; Yaman, Yavuz (2012-07-04)
In this study, the detailed finite element model (FEM) of an unmanned aerial vehicle wing torque box was verified by the experimental modal testing. During the computational studies the free-free boundary conditions were used and the natural frequencies and mode-shapes of the structure were obtained by using the MSC Software. The results were then compared with the experimentally obtained resonance frequencies and mode-shapes. It was observed that the frequencies were in close agreement having an error with...
Design and aerodynamic analysis of a VTOL tilt-wing UAV
Cakir, Hasan; Kurtuluş, Dilek Funda (2022-01-01)
The aerodynamic design and analysis of an Unmanned Air Vehicle, capable of vertical take-off and landing by employing fixed four rotors on the tilt-wing and two rotors on the tilt-tail, will be presented in this study. Both main wing and the horizontal tail can be tilted 90 degrees. During VTOL, transition and forward flight, aerodynamic and thrust forces have been employed. Different flight conditions, including the effects of angle of attack, side slip, wing tilt angle and control surfaces deflection angl...
Hovering Control of a Tilt-Wing UAV
Çakır, Hasan; Kurtuluş, Dilek Funda (2019-09-20)
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 t...
Experimental Investigation of Aerodynamics of Flapping-Wing Micro-Air-Vehicle by Force and Flow-Field Measurements
Deng, Shuanghou; Perçin, Mustafa; van Oudheusden, Bas (2016-02-01)
This study explores the aerodynamic characteristics of a flapping-wing micro aerial vehicle (MAV) in hovering configuration by means of force and flowfield measurements. The effects of flapping frequency and wing geometry on force generation were examined using a miniature six-component force sensor. Additional high-speed imaging allowed identification of the notable different deformation characteristics of the flexible wings under vacuum condition in comparison to their behavior in air, illustrating the re...
Design, Modeling, and Control Allocation of a Heavy-Lift Aerial Vehicle Consisting of Large Fixed Rotors and Small Tiltrotors
Ozdogan, Gokhan; Leblebicioğlu, Mehmet Kemal (2022-02-01)
In this article, we propose an unconventional heavy-lift aerial vehicle (HLAV), present the design and its control allocation analysis, and prove the concept by the demonstration of the experimental test prototype in the outdoor environment. We aim for a mechanically robust and simple vehicle design that efficiently performs heavy lifting compared to other common aerial vehicles under certain width constraints, without using a complex swashplate mechanism. The HLAV performs the task of carrying the main loa...
Citation Formats
B. T. Güzelcan, “Modelling of an articulated flying body and control system design,” M.S. - Master of Science, Middle East Technical University, 2022.