Tilt Duct Vertical Takeoff and Landing Uninhabited Aerial Vehicle Concept Design Study

10.2514/1.271 ◽  
2004 ◽  
Vol 41 (2) ◽  
pp. 215-223 ◽  
Author(s):  
Ozlem Armutcuoglu ◽  
Mehmet Serif Kavsaoglu ◽  
Ozan Tekinalp
Keyword(s):  
Concept Design ◽  
Vehicle Concept ◽  
Design Study ◽  
Vertical Takeoff And Landing ◽  
Aerial Vehicle ◽  
Vertical Takeoff

Dynamic Analysis of a Ducted Fan UAV in Forward Flight

2012 ◽  
Vol 224 ◽  
pp. 510-513
Author(s):  
Wei Zhang ◽  
Ning Jun Fan
Keyword(s):  
Control System ◽  
System Design ◽  
Nonlinear Model ◽  
Control System Design ◽  
Forward Flight ◽  
Ducted Fan ◽  
Vertical Takeoff And Landing ◽  
Aerial Vehicle ◽  
And Control ◽  
Vertical Takeoff

This paper deals with the dynamic modeling of a ducted fan vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV) and focuses on the dynamic characteristics analyzing in forward flight. A 6-DOF nonlinear model has been established in terms of the forces and moments and the model can be used in the structure and control system design.

Lightweight unmanned aerial vehicle for emergency medical service – Synthesis of the layout

2020 ◽  
pp. 095441002091058 ◽  
Author(s):  
Tomasz Goetzendorf-Grabowski ◽  
Andrzej Tarnowski ◽  
Marcin Figat ◽  
Jacek Mieloszyk ◽  
Bogdan Hernik
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Forward Flight ◽  
Medical Mission ◽  
Emergency Medical ◽  
Vertical Takeoff And Landing ◽  
Aerial Vehicle ◽  
The Cost ◽  
Vertical Takeoff ◽  
Motor Failure ◽  
Selection Of

The article presents the innovative unmanned aerial vehicle project for emergency medical services. Designed unmanned aerial vehicle combines vertical takeoff and landing characteristics with fast forward flight capability that are vital to perform such an emergency medical mission. The main purpose of the designed unmanned aerial vehicle is to deliver the necessary medical package to the place where access is difficult, and estimated arrival time of conventional ambulance is too long. The cost of the support of such unmanned aerial vehicle could be significantly lower than in case of medical helicopter, which is not necessary in some cases. Designed unmanned aerial vehicle can also be used for fast delivery of essential medical substances (e.g. blood). The selection of configuration was the first and crucial step of the design. After analysis of many different copter configurations, together with selected crash reports analysis, the coaxial quadcopter configuration crossed with conventional airplane was selected. All power units for VTOL capability are electric, and they are doubled for redundancy purposes, with maximum T/W ratio about 2.0. Such configuration allows to sustain a stable flight (vertical phases) in case of one motor failure. Two versions of the vehicle are designed: fully electric (power units for the forward flight and vertical takeoff and landing are electric) and mixed where forward flight unit is a small piston engine. The final layout was the result of conceptual investigation and preliminary research, MDO and trade-off analysis, where as many aspects as possible were considered. The main problem was to meet the vertical takeoff and landing capabilities, relatively long range and endurance, expected payload (3 kg) and the requirement not to exceed 25 kg of maximum take-off weight. Paper presents the design process from initial requirement to the final configuration accepted to be manufactured.

Design and Attitude Control of a Quad-Rotor Tail-Sitter Vertical Takeoff and Landing Unmanned Aerial Vehicle

2012 ◽  
Vol 26 (3-4) ◽  
pp. 307-326 ◽  
Author(s):  
Atsushi Oosedo ◽  
Atsushi Konno ◽  
Takaaki Matsumoto ◽  
Kenta Go ◽  
Koji Masuko ◽  
...  
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Attitude Control ◽  
Vertical Takeoff And Landing ◽  
Aerial Vehicle ◽  
Vertical Takeoff

Conceptual Design Study of a Vertical Takeoff and Landing Airbreather

2021 ◽  
pp. 1-14
Author(s):  
Hiroaki Kobayashi ◽  
Yusuke Maru ◽  
Matthew P. Richardson ◽  
Kiyoshi Kinefuchi ◽  
Tetsuya Sato
Keyword(s):  
Conceptual Design ◽  
Design Study ◽  
Vertical Takeoff And Landing ◽  
Vertical Takeoff

scholarly journals Studies of 4-rotor unmanned aerial vehicle UAV in the field of control system

2018 ◽  
Vol 210 ◽  
pp. 05009 ◽  
Author(s):  
Lucjan Setlak ◽  
Rafał Kowalik
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicle ◽  
Traffic Control ◽  
Structural Instability ◽  
Unmanned Aircraft ◽  
Vertical Takeoff And Landing ◽  
Aerial Vehicle ◽  
Vertical Takeoff ◽  
Linear Nature

The key goal of this work was to develop a functional mathematical model of a 4-rotor UAV, including regulatory apparatus and identification of its parameters. The functionality of a quadrocopter traffic control has been reduced to solving differential equations that define the motion and dynamics of an unmanned aerial vehicle. It should be noted that the synthesis of the quadrocopter control system is not an easy task, due to the non-linear nature of the dynamics of this object and its structural instability. Therefore, in this article the tested object UAV was accepted as a physical model, which may cause potential material damage resulting from damage to the device as well as other elements that are located in its immediate surroundings. In addition, the article discusses the problem of improving the quality of the estimation rate of climb of unmanned aircraft of vertical takeoff and landing UAV, this problem was considered for the object in the low-ceiling range, i.e. in the range of 0-6 m, so the issue concerns autonomous take-off and landing. For the presentation of the results, the 4-rotor UAV was used, with the use of a proportional-integral-derivative PID controller in the context of the control system. The obtained results were supported by research and analysis of real results - the discussed algorithm was implemented in the 4-rotor UAV driver.

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