Wind Tunnel Test of Smart Un-manned Aerial Vehicle(SUAV) for TR-E2S1 Configuration

2005 ◽  
Vol 29 (3) ◽  
pp. 295-305 ◽  
Author(s):  
SunEiun Yoon ◽  
Tahwan Cho ◽  
Jindeog Chung
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Aerial Vehicle

scholarly journals Simulation and flight experiments of a quadrotor tail-sitter vertical take-off and landing unmanned aerial vehicle with wide flight envelope

2018 ◽  
Vol 10 (4) ◽  
pp. 303-317 ◽  
Author(s):  
Ximin Lyu ◽  
Haowei Gu ◽  
Jinni Zhou ◽  
Zexiang Li ◽  
Shaojie Shen ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Unmanned Aerial Vehicle ◽  
Wind Tunnel Test ◽  
Small Scale ◽  
Level Flight ◽  
Flight Envelope ◽  
Aerial Vehicle ◽  
Attitude Controller ◽  
And Control ◽  
Thrust And Torque

This paper presents the modeling, simulation, and control of a small-scale electric powered quadrotor tail-sitter vertical take-off and landing unmanned aerial vehicle. In the modeling part, a full attitude wind tunnel test is performed on the full-scale unmanned aerial vehicle to capture its aerodynamics over the flight envelope. To accurately capture the degradation of motor thrust and torque at the presence of the forward speed, a wind tunnel test on the motor and propeller is also carried out. The extensive wind tunnel tests, when combined with the unmanned aerial vehicle kinematics model, dynamics model and other practical constraints such as motor saturation and delay, lead to a complete flight simulator that can accurately reveal the actual aircraft dynamics as verified by actual flight experiments. Based on the developed model, a unified attitude controller and a stable transition controller are designed and verified. Both simulation and experiments show that the developed attitude controller can stabilize the unmanned aerial vehicle attitude over the entire flight envelope and the transition controller can successfully transit the unmanned aerial vehicle from vertical flight to level flight with negligible altitude dropping, a common and fundamental challenge for tail-sitter vertical take-off and landing aircrafts. Finally, when supplied with the designed controller, the tail-sitter unmanned aerial vehicle can achieve a wide flight speed envelope ranging from stationary hovering to fast level flight. This feature dramatically distinguishes our aircraft from conventional fixed-wing airplanes.

Wind-tunnel test techniques for unmanned aerial vehicle separation investigations

1994 ◽  
Vol 31 (3) ◽  
pp. 585-590 ◽  
Author(s):  
S. A. Moyer ◽  
M. D. Talbot
Keyword(s):  
Wind Tunnel ◽  
Unmanned Aerial Vehicle ◽  
Wind Tunnel Test ◽  
Aerial Vehicle

Wind tunnel test of an unmanned aerial vehicle (UAV)

2003 ◽  
Vol 17 (5) ◽  
pp. 776-783 ◽  
Author(s):  
Chung Jindeog ◽  
Lee Jangyeon ◽  
Sung Bongzoo ◽  
Koo Samok
Keyword(s):  
Wind Tunnel ◽  
Unmanned Aerial Vehicle ◽  
Wind Tunnel Test ◽  
Aerial Vehicle

scholarly journals Design, Manufacturing, and Testing of a New Concept for a Morphing Leading Edge using a Subsonic Blow Down Wind Tunnel

Biomimetics ◽  
2019 ◽  
Vol 4 (4) ◽  
pp. 76
Author(s):  
David Communier ◽  
Franck Le Besnerais ◽  
Ruxandra Mihaela Botez ◽  
Tony Wong
Keyword(s):  
Wind Tunnel ◽  
Lift Coefficient ◽  
Wind Tunnel Test ◽  
Leading Edge ◽  
Test Results ◽  
Deformation Method ◽  
Blow Down ◽  
Aerial Vehicle ◽  
Compliance Mechanism ◽  
Stall Angle

This paper presents the design and wind tunnel test results of a wing including a morphing leading edge for a medium unmanned aerial vehicle with a maximum wingspan of 5 m. The design of the morphing leading edge system is part of research on the design of a morphing camber system. The concept presented here has the advantage of being simple to manufacture (wooden construction) and light for the structure of the wing (compliance mechanism). The morphing leading edge prototype demonstrates the possibility of modifying the stall angle of the wing. In addition, the modification of the stall angle is performed without affecting the slope of the lift coefficient. This prototype is designed to validate the functionality of the deformation method applied to the leading edge of the wing. The mechanism can be further optimized in terms of shape and material to obtain a greater deformation of the leading edge, and, thus, to have a higher impact on the increase of the stall angle than the first prototype of the morphing leading edge presented in this paper.

scholarly journals Design and Performance Evaluation of Propeller for Solar-Powered High-Altitude Long-Endurance Unmanned Aerial Vehicle

2018 ◽  
Vol 2018 ◽  
pp. 1-23 ◽  
Author(s):  
Donghun Park ◽  
Yunggyo Lee ◽  
Taehwan Cho ◽  
Cheolwan Kim
Keyword(s):  
Wind Tunnel ◽  
High Altitude ◽  
Test Data ◽  
Design Method ◽  
Wind Tunnel Test ◽  
Flight Test ◽  
Cfd Analysis ◽  
Aerial Vehicle ◽  
Solar Powered ◽  
Long Endurance

Design, wind tunnel test, computational fluid dynamics (CFD) analysis, and flight test data analysis are conducted for the propeller of EAV-3, which is a solar-powered high-altitude long-endurance unmanned aerial vehicle developed by Korea Aerospace Research Institute. The blade element momentum theory, in conjunction with minimum induced loss, is used as a basic design method. Airfoil data are obtained from CFD analysis, which takes into account the low Reynolds number effect. The response surface is evaluated for design variables by using design of experiment and kriging metamodel. The optimization is based on desirability function. A wind tunnel test is conducted on the designed propeller. Numerical analyses are performed by using a commercial CFD code, and results are compared with those obtained from the design code and wind tunnel test data. Flight test data are analyzed based on several approximations and assumptions. The propeller performance is in good agreement with the numerical and measurement data in terms of tendency and behavior. The comparison of data confirms that the design method, wind tunnel test, and CFD analysis used in this study are practically useful and valid for the development of a high-altitude propeller.

Static Wind Tunnel Test of Smart Un-manned Aerial Vehicle(SUAV) for TR-S4 Configuration

2006 ◽  
Vol 30 (10) ◽  
pp. 1012-1018
Author(s):  
Sung-Wook Choi ◽  
Cheol-Wan Kim ◽  
Jang-Yeon Lee ◽  
Jin-Deog Chung
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Aerial Vehicle

Response and Operational Modal Analysis from Wind Tunnel Test of the EOLO Flexible Aircraft

2021 ◽  
Author(s):  
David F. Castillo Zuñiga ◽  
Alain Giacobini Souza ◽  
Roberto G. da Silva ◽  
Luiz Carlos Sandoval Góes
Keyword(s):  
Wind Tunnel ◽  
Modal Analysis ◽  
Wind Tunnel Test ◽  
Operational Modal Analysis ◽  
Flexible Aircraft

DEVELOPMENT OF A RAPID PROTOTYPING METHODOLOGY FOR WIND TUNNEL TEST MODEL DESIGN

2019 ◽  
Author(s):  
Bruno Ricardo Massucatto Padilha ◽  
Guilherme Barufaldi ◽  
ROBERTO GIL ANNES DA SILVA
Keyword(s):  
Wind Tunnel ◽  
Rapid Prototyping ◽  
Wind Tunnel Test ◽  
Test Model ◽  
Model Design
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