scholarly journals Wind Tunnel Research on the Unmanned Aerial Vehicle Rotor Blade Setting Angle

2020 ◽  
Vol 14 (4) ◽  
pp. 104-114
Author(s):  
Ksenia Siadkowska
Keyword(s):  
Wind Tunnel ◽  
Unmanned Aerial Vehicle ◽  
Rotor Blade ◽  
Setting Angle ◽  
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.

scholarly journals A New Method for Adjusting Setting Angle of Rotor Blade for Axial Fan in Wind Tunnel

2019 ◽  
Vol 37 (3) ◽  
pp. 580-586
Author(s):  
Xiaoli Qu ◽  
Zebin Ren ◽  
Wenguo Yang ◽  
Yuanqiang Luo ◽  
Chenghua Cong
Keyword(s):  
Wind Tunnel ◽  
Flow Velocity ◽  
Test Section ◽  
Rotor Blade ◽  
New Method ◽  
Axial Fan ◽  
Low Speed ◽  
Rotating Speed ◽  
Setting Angle ◽  
Low Speed Wind Tunnel

Combining the fan aerodynamic efficiency with the wind tunnel pressure loss coefficient, a new equation which points out the inherent relationship of the fan blade setting angle, fan rotating speed and gas flow rate in wind tunnel circuit is derived according to the two-dimensional flow theory of the axial fan rotor blades and the aerodynamic characteristics of the low speed wind tunnel. So a new method for setting angle adjustment of fan rotor blade to satisfy the fan performance at off-design point by getting the test results of fan operation parameters but without the fan total pressure rise in the low speed wind tunnel is developed. Flowing the new method, the setting angle adjusting value of fan rotor blade was provided only with the fan rotating speed and flow velocity in the test section of a low speed wind tunnel directly before the fan setting angle altered, the adjusting target was achieved by the new blade setting angle successfully and the time and cost of the wind tunnel commissioning test were saved. The test results show that, after increasing the fan rotor blade setting angle by 4.5 degrees, when the flow velocity in the wind tunnel test section reaches 60 m/s, the fan rotating speed is 570 r/min, the deviation from the predicted fan rotating speed value of 575 r/min is 0.9%. For the same test section flow velocity, the predicted value of the fan rotating speed is in a good agreement with the real value, it proves that this method is reliable and accurate in practical application.

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 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 Spray drift characteristics test of unmanned aerial vehicle spray unit under wind tunnel conditions

2020 ◽  
Vol 13 (3) ◽  
pp. 13-21 ◽  
Author(s):  
Changling Wang ◽  
◽  
Aijun Zeng ◽  
Xiongkui He ◽  
Jianli Song ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Unmanned Aerial Vehicle ◽  
Spray Drift ◽  
Aerial Vehicle
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