scholarly journals Implementation of a Hybrid Electro-Active Actuated Morphing Wing in Wind Tunnel

2017 ◽  
Vol 260 ◽  
pp. 85-91 ◽  
Author(s):  
Gurvan Jodin ◽  
Johannes Scheller ◽  
Eric Duhayon ◽  
Jean François Rouchon ◽  
Marianna Braza
Keyword(s):  
Wind Tunnel ◽  
Shape Memory ◽  
Low Frequency ◽  
Aerodynamic Performance ◽  
Point Of View ◽  
Morphing Wing ◽  
Wind Tunnel Experiments ◽  
Trailing Edge ◽  
Actuation System ◽  
Hybrid Actuation

Amongst current aircraft research topics, morphing wing is of great interest for improving the aerodynamic performance. A morphing wing prototype has been designed for wind tunnel experiments. The rear part of the wing - corresponding to the retracted flap - is actuated via a hybrid actuation system using both low frequency camber control and a high frequency vibrating trailing edge. The camber is modified via surface embedded shape memory alloys. The trailing edge vibrates thanks to piezoelectric macro-fiber composites. The actuated camber, amplitude and frequency ranges are characterized. To accurately control the camber, six independent shape memory alloy wires are controlled through nested closed-loops. A significant reduction in power consumption is possible via this control strategy. The effects on flow via morphing have been measured during wind tunnel experiments. This low scale mock-up aims to demonstrate the hybrid morphing concept, according to actuator capabilities point of view as well as aerodynamic performance.

Note on the Possibility of Flight by Human Power

1937 ◽  
Vol 41 (319) ◽  
pp. 609-611
Author(s):  
H. C. H. Townend
Keyword(s):  
Wind Tunnel ◽  
Point Of View ◽  
Wind Tunnel Experiments ◽  
Dynamic Soaring ◽  
Human Power ◽  
Made In

The object of this note is to draw attention to a few facts which, taken together, suggest that, from a purely aerodynamic point of view, the difficulties involved in flight by human power may not be as great as is generally supposed.Some years ago, in a lecture delivered to the Royal Aeronautical Society, the German soaring pilot, Lippisch, referred to an account of dynamic soaring given by Lanchester in his “ Aerodonetics ” and to some wind tunnel experiments made in Vienna.

Novel morphing wing actuator control-based Particle Swarm Optimisation

2019 ◽  
Vol 124 (1271) ◽  
pp. 55-75 ◽  
Author(s):  
S. Khan ◽  
T. L. Grigorie ◽  
R. M. Botez ◽  
M. Mamou ◽  
Y. Mébarki
Keyword(s):  
Control System ◽  
Wind Tunnel ◽  
Experimental Model ◽  
Experimental Testing ◽  
Pressure Sensors ◽  
Particle Swarm ◽  
Particle Swarm Optimisation ◽  
Morphing Wing ◽  
Software Model ◽  
Actuation System

AbstractThe paper presents the design and experimental testing of the control system used in a new morphing wing application with a full-scaled portion of a real wing. The morphing actuation system uses four similar miniature brushless DC (BLDC) motors placed inside the wing, which execute a direct actuation of the flexible upper surface of the wing made from composite materials. The control system of each actuator uses three control loops (current, speed and position) characterised by five control gains. To tune the control gains, the Particle Swarm Optimisation (PSO) method is used. The application of the PSO method supposed the development of a MATLAB/Simulink® software model for the controlled actuator, which worked together with a software sub-routine implementing the PSO algorithm to find the best values for the five control gains that minimise the cost function. Once the best values of the control gains are established, the software model of the controlled actuator is numerically simulated in order to evaluate the quality of the obtained control system. Finally, the designed control system is experimentally validated in bench tests and wind-tunnel tests for all four miniature actuators integrated in the morphing wing experimental model. The wind-tunnel testing treats the system as a whole and includes, besides the evaluation of the controlled actuation system, the testing of the integrated morphing wing experimental model and the evaluation of the aerodynamic benefits brought by the morphing technology on this project. From this last perspective, the airflow on the morphing upper surface of the experimental model is monitored by using various techniques based on pressure data collection with Kulite pressure sensors or on infrared thermography camera visualisations.

Wind-Tunnel Testing of Shape Memory Alloys Actuators as Morphing Wing Driving Systems

2009 ◽  
Author(s):  
Thomas Georges ◽  
Vladimir Brailovski ◽  
Emeric Morellon ◽  
Daniel Coutu ◽  
Patrick Terriault
Keyword(s):  
Wind Tunnel ◽  
Shape Memory Alloys ◽  
Shape Memory ◽  
Wind Tunnel Testing ◽  
Morphing Wing ◽  
Original Design ◽  
Active Elements ◽  
Sma Actuator ◽  
Force Displacement ◽  
Tunnel Testing

A morphing wing, composed of flexible extrados, rigid intrados and a Shape Memory Alloys (SMA) actuator group located inside the wing box, is used to adapt an airfoil profile to variable flight conditions. The SMA actuator group developed for the morphing wing prototype consists of three main subsystems: the SMA active element, the transmission system, and the passive bias element. The functional requirements for the actuator group were determined using a coupled fluid-structure model of the flexible extrados. An original design approach was applied to determine the geometry and assembly conditions of the SMA active elements. For validation purposes, the morphing wing powered by SMA actuators was tested in a wind tunnel under subsonic flight conditions (Mach = 0.2 to 0.3 and α = −1 to 2°). The ability of the actuator group to move the flexible extrados up to 8 mm of vertical displacement and to bring it back to the initial profile has been successfully proven for all of the wind tunnel testing conditions. During the repetitive actuation, the force, displacement and temperature of the SMA active elements were measured and the results obtained in the force-displacement-temperature space were used to validate the SMA performances predicted during the design phase.

scholarly journals Horizontal Wind Effect on the Aerodynamic Performance of Coaxial Tri-Rotor MAV

2020 ◽  
Vol 10 (23) ◽  
pp. 8612
Author(s):  
Yao Lei ◽  
Yiqiang Ye ◽  
Zhiyong Chen
Keyword(s):  
Wind Tunnel ◽  
Power Consumption ◽  
Aerodynamic Characteristics ◽  
Aerodynamic Performance ◽  
Horizontal Wind ◽  
Wind Effect ◽  
Rotor Speed ◽  
Wind Tunnel Experiments ◽  
Air Vehicle ◽  
Power Loading

The coaxial Tri-rotor micro air vehicle (MAV) is composed of three coaxial rotors where the aerodynamic characteristics of is complicated in flight especially when the wind effect is introduced. In this paper, the hovering performance of a full-scale coaxial Tri-rotor MAV is analyzed with both the simulations and wind tunnel experiments. Firstly, the wind effect on the aerodynamic performance of coaxial Tri-rotor MAV is established with different rotor speed (1500–2300 rpm) and horizontal wind (0–4 m/s). Secondly, the thrust and power consumption of coaxial Tri-rotor (L/D = 1.6) were obtained with low-speed wind tunnel experiments. Furthermore, the streamline distribution, pressure distribution, velocity contour and vortex distribution with different horizontal wind conditions are obtained by numerical simulations. Finally, combining the experiment results and simulation results, it is noted that the horizontal wind may accelerate the aerodynamic coupling, which resulting in the greater thrust variation up to 9% of the coaxial Tri-rotor MAV at a lower rotor speed. Moreover, the aerodynamic performance is decreased with more power consumption at higher rotor speed where the wind and the downwash flow are interacted with each other. Compared with no wind flow, the shape of the downwash flow and the deformation of the vortex affect the power loading and figure of metric accordingly.

Development of a Morphing Wing Actuated by Shape Memory Alloys and Its Wind Tunnel Test

2017 ◽  
Vol 2017.66 (0) ◽  
pp. 810
Author(s):  
Tadashige IKEDA ◽  
Toshiyuki KOJIMA ◽  
Masato TAMAYAMA ◽  
Hitoshi ARIZONO ◽  
Atsuhiko SENBA
Keyword(s):  
Wind Tunnel ◽  
Shape Memory Alloys ◽  
Shape Memory ◽  
Wind Tunnel Test ◽  
Morphing Wing

scholarly journals Fuzzy Logic-Based Control for a Morphing Wing Tip Actuation System: Design, Numerical Simulation, and Wind Tunnel Experimental Testing

Biomimetics ◽  
2019 ◽  
Vol 4 (4) ◽  
pp. 65
Author(s):  
Khan ◽  
Grigorie ◽  
Botez ◽  
Mamou ◽  
Mébarki
Keyword(s):  
Numerical Simulation ◽  
Fuzzy Logic ◽  
Wind Tunnel ◽  
Experimental Testing ◽  
Aviation Industry ◽  
Morphing Wing ◽  
Brushless Dc ◽  
Wing Model ◽  
Actuation System ◽  
Prime Concern

The paper presents the design, numerical simulation, and wind tunnel experimental testing of a fuzzy logic-based control system for a new morphing wing actuation system equipped with Brushless DC (BLDC) motors, under the framework of an international project between Canada and Italy. Morphing wing is a prime concern of the aviation industry and, due to the promising results, it can improve fuel optimization. In this idea, a major international morphing wing project has been carried out by our university team from Canada, in collaboration with industrial, research, and university entities from our country, but also from Italy, by using a full-scaled portion of a real aircraft wing equipped with an aileron. The target was to conceive, manufacture, and test an experimental wing model able to be morphed in a controlled manner and to provide in this way an extension of the laminar airflow region over its upper surface, producing a drag reduction with direct impact on the fuel consumption economy. The work presented in the paper aims to describe how the experimental model has been developed, controlled, and tested, to prove the feasibility of the morphing wing technology for the next generation of aircraft.

The Aerodynamics of an Actively Twisted Wing

Aerospace ◽  
2005 ◽  
Author(s):  
James R. Sonnenmeier ◽  
Oladipo Onipede ◽  
Andrew J. Detar ◽  
Heather L. Myers
Keyword(s):  
Wind Tunnel ◽  
Shape Memory Alloy ◽  
Angle Of Attack ◽  
Aerodynamic Performance ◽  
Simple Test ◽  
Wind Tunnel Experiments ◽  
Aerodynamic Forces ◽  
Aerodynamic Model ◽  
Separate Control ◽  
Control Surfaces

Aerodynamic performance of aircraft can be changed by moving separate surfaces which are mechanically connected to the main wing and moved with complex linkages. A possible alternative method of changing performance with less mechanical complexity is presented. Instead of separate control surfaces, the shape of complete aerodynamic structures can be changed with shape memory alloy (SMA) materials as part of the structure. In this work SMA wire is wrapped around a simple test wing. When activated by heating, the wire contracts which results in twisting the wing. The angle of attack along the wingspan changes which changes the aerodynamic forces on the wing. This could be used to optimize the flight condition. Results are presented from initial wind tunnel experiments which show the change in lift due to twisting. Aerodynamic models that account for the variable angle of attack along the span are also developed. The results from the experiments and aerodynamic model are compared.

Wind Tunnel Testing of a Helicopter Rotor Trailing Edge Flap Actuated via Pneumatic Artificial Muscles

2010 ◽  
Author(s):  
Benjamin K. S. Woods ◽  
Norman M. Wereley ◽  
Curt S. Kothera
Keyword(s):  
Wind Tunnel ◽  
Aerodynamic Load ◽  
Artificial Muscles ◽  
Specific Work ◽  
Test Model ◽  
Trailing Edge ◽  
Actuation System ◽  
Wide Range ◽  
Pneumatic Artificial Muscles ◽  
Trailing Edge Flap

A novel active trailing edge flap actuation system is under development. This system differs significantly from previous trailing edge flap systems in that it is driven by a pneumatic actuator technology. Pneumatic Artificial Muscles (PAMs) were chosen because of several attractive properties, including high specific work and power output, an expendable operating fluid, and robustness. The actuation system is sized for a full scale active rotor system for a Bell 407 scale helicopter. This system is designed to produce large flap deflections (±20°) at the main rotor rotation frequency (1/rev) to create large amplitude thrust variation for primary control of the helicopter. Additionally, it is designed to produce smaller magnitude deflections at higher frequencies, up to 5/rev (N+1/rev), to provide vibration mitigation capability. The basic configuration has a pair of Pneumatic Artificial Muscles mounted antagonistically in the root of each blade. A bellcrank and linkage system transfers the force and motion of these actuators to a trailing edge flap on the outboard portion of the rotor. A reduced span wind tunnel test model of this system has been built and tested in the Glenn L. Martin Wind Tunnel at the University of Maryland at wind speeds up to M = 0.3. The test article consisted of a 5-ft long tip section of a Bell 407 rotor blade cantilevered from the base of the tunnel with a 34 in, 15% chord plain flap that was driven by the PAM actuation system. Testing over a wide range of aerodynamic conditions and actuation parameters established the considerable control authority and bandwidth of the system at the aerodynamic load levels available in the tunnel. Comparison of quasi-static experimental results shows good agreement with predictions made using a simple system model.

scholarly journals A hybrid fuzzy logic proportional-integral-derivative and conventional on-off controller for morphing wing actuation using shape memory alloy Part 1: Morphing system mechanisms and controller architecture design

2012 ◽  
Vol 116 (1179) ◽  
pp. 433-449 ◽  
Author(s):  
T. L. Grigorie ◽  
R. M. Botez ◽  
A. V. Popov ◽  
M. Mamou ◽  
Y. Mébarki
Keyword(s):  
Fuzzy Logic ◽  
Shape Memory ◽  
Research Work ◽  
Pressure Sensors ◽  
Proportional Integral Derivative ◽  
Morphing Wing ◽  
Proportional Integral ◽  
Sma Actuators ◽  
Hybrid Controller ◽  
Actuation System

AbstractThe present paper describes the design of a hybrid actuation control concept, a fuzzy logic proportional-integral-derivative plus a conventional on-off controller, for a new morphing mechanism using smart materials as actuators, which were made from shape memory alloys (SMA). The research work described here was developed for the open loop phase of a morphing wing system, whose primary goal was to reduce the wing drag by delaying the transition (from laminar to fully turbulent flows) position toward the wing trailing edge. The designed controller drives the actuation system equipped with SMA actuators to modify the flexible upper wing skin surface. The designed controller was also included, as an internal loop, in the closed loop architecture of the morphing wing system, based on the pressure information received from the flexible skin mounted pressure sensors and on the estimation of the transition location.The controller’s purposes were established following a comprehensive presentation of the morphing wing system architecture and requirements. The strong nonlinearities of the SMA actuators’ characteristics and the system requirements led to the choice of a hybrid controller architecture as a combination of a bi-positional on-off controller and a fuzzy logic controller (FLC). In the chosen architecture, the controller would behave as a switch between the SMA cooling and heating phases, situations where the output current is 0A or is controlled by the FLC.In the design phase, a proportional-integral-derivative scheme was chosen for the FLC. The input-output mapping of the fuzzy model was designed, taking account of the system’s error and its change in error, and a final architecture for the hybrid controller was obtained. The shapes chosen for the inputs’ membership functions weres-function,π-function, andz-function, and product fuzzy inference and the center average defuzzifier were applied (Sugeno).

scholarly journals Aerodynamic Performance of Hex-Rotor UAV Considering the Horizontal Airflow

2019 ◽  
Vol 9 (22) ◽  
pp. 4797
Author(s):  
Yao Lei ◽  
Mingxin Cheng
Keyword(s):  
Wind Tunnel ◽  
Numerical Simulations ◽  
Aerodynamic Performance ◽  
Wind Tunnel Experiments ◽  
Low Speed ◽  
Pressure Distributions ◽  
Hover Performance ◽  
Power Loading ◽  
Aerial Vehicle ◽  
Low Speed Wind Tunnel

In this paper, the aerodynamic performance of a Hex-rotor unmanned aerial vehicle (UAV) with different rotational speeds (1500–2300 RPM) considering the horizontal airflow conditions is analyzed by both simulations and experiments. A low-speed wind tunnel experiments platform is applied to measure the thrust, torque, and power consumption of a Hex-rotor UAV with different rotational speeds in horizontal airflow, which varied from 0 m/s–4 m/s. First, this paper introduces the effect of horizontal airflow on a UAV. Then, the low-speed wind tunnel experiments were carried out on a Hex-rotor UAV (D/L = 0.56) with different horizontal velocities to determine the hover performance. Finally, numerical simulations were obtained with the streamline distributions, pressure distributions, velocity contour, and vortex distributions at different horizontal airflow conditions to describe the aerodynamic interference effect of different horizontal airflows. Combined with the experimental results and numerical simulations results, the horizontal airflow proved to have a significant influence on the aerodynamic performance of the Hex-rotor UAV with an increase in thrust and power. Indeed, the streamlines in the flow field were coupled to each other at the presence of the incoming airflow. Especially when the incoming airflow was larger, the Hex-rotor UAV could properly use low-speed flight to maintain high power loading. Finally, it is inferred that the aerodynamic performance of the Hex-rotor UAV is also related to the movement and deformation of the vortex at the tip of the rotor.

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