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 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

scholarly journals Design and Validation of a New Morphing Camber System by Testing in the Price—Païdoussis Subsonic Wind Tunnel

Aerospace ◽  
2020 ◽  
Vol 7 (3) ◽  
pp. 23 ◽  
Author(s):  
David Communier ◽  
Ruxandra Mihaela Botez ◽  
Tony Wong
Keyword(s):  
Wind Tunnel ◽  
Unmanned Aerial Vehicle ◽  
Lift Coefficient ◽  
Angle Of Attack ◽  
Leading Edge ◽  
Trailing Edge ◽  
Subsonic Wind Tunnel ◽  
Aerial Vehicle ◽  
Stall Angle

This paper presents the design and wind tunnel testing of a morphing camber system and an estimation of performances on an unmanned aerial vehicle. The morphing camber system is a combination of two subsystems: the morphing trailing edge and the morphing leading edge. Results of the present study show that the aerodynamics effects of the two subsystems are combined, without interfering with each other on the wing. The morphing camber system acts only on the lift coefficient at a 0° angle of attack when morphing the trailing edge, and only on the stall angle when morphing the leading edge. The behavior of the aerodynamics performances from the MTE and the MLE should allow individual control of the morphing camber trailing and leading edges. The estimation of the performances of the morphing camber on an unmanned aerial vehicle indicates that the morphing of the camber allows a drag reduction. This result is due to the smaller angle of attack needed for an unmanned aerial vehicle equipped with the morphing camber system than an unmanned aerial vehicle equipped with classical aileron. In the case study, the morphing camber system was found to allow a reduction of the drag when the lift coefficient was higher than 0.48.

Wind tunnel investigation of the propellers for unmanned aerial vehicle

2021 ◽  
Author(s):  
Zbigniew Czyz ◽  
Pawel Karpinski ◽  
Krzysztof Skiba
Keyword(s):  
Wind Tunnel ◽  
Unmanned Aerial Vehicle ◽  
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.

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