Design, Analysis and Experimental Testing of a Morphing Wing

2017 ◽  
Author(s):  
Joan Marc Martinez ◽  
Domenico Scopelliti ◽  
Cees Bil ◽  
Robert Carrese ◽  
Pier Marzocca ◽  
...  
Keyword(s):  
Experimental Testing ◽  
Design Analysis ◽  
Morphing Wing

scholarly journals Sensing, Actuation, and Control of the SmartX Prototype Morphing Wing in the Wind Tunnel

Actuators ◽  
2021 ◽  
Vol 10 (6) ◽  
pp. 107
Author(s):  
Nakash Nazeer ◽  
Xuerui Wang ◽  
Roger M. Groves
Keyword(s):  
Wind Tunnel ◽  
Optical Fibers ◽  
Fiber Optic ◽  
Experimental Testing ◽  
Single Mode ◽  
Fiber Optic Sensor ◽  
Sensor Data ◽  
Random Errors ◽  
Morphing Wing ◽  
Actuator Dynamics

This paper presents a study on trailing edge deflection estimation for the SmartX camber morphing wing demonstrator. This demonstrator integrates the technologies of smart sensing, smart actuation and smart controls using a six module distributed morphing concept. The morphing sequence is brought about by two actuators present at both ends of each of the morphing modules. The deflection estimation is carried out by interrogating optical fibers that are bonded on to the wing’s inner surface. A novel application is demonstrated using this method that utilizes the least amount of sensors for load monitoring purposes. The fiber optic sensor data is used to measure the deflections of the modules in the wind tunnel using a multi-modal fiber optic sensing approach and is compared to the deflections estimated by the actuators. Each module is probed by single-mode optical fibers that contain just four grating sensors and consider both bending and torsional deformations. The fiber optic method in this work combines the principles of hybrid interferometry and FBG spectral sensing. The analysis involves an initial calibration procedure outside the wind tunnel followed by experimental testing in the wind tunnel. This method is shown to experimentally achieve an accuracy of 2.8 mm deflection with an error of 9%. The error sources, including actuator dynamics, random errors, and nonlinear mechanical backlash, are identified and discussed.

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.

Numerical Optimization and Experimental Testing of a Morphing Wing with Aileron System

2016 ◽  
Author(s):  
Andreea Koreanschi ◽  
Sugar Gabor Oliviu ◽  
Tristan Ayrault ◽  
Ruxandra M. Botez ◽  
Mahmoud Mamou ◽  
...  
Keyword(s):  
Numerical Optimization ◽  
Experimental Testing ◽  
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.

scholarly journals Experimental Testing, Modeling, and Simulation of 3D Printed Composite Material for Morphing Wing Application

2020 ◽  
Author(s):  
Rebecca Rajs ◽  
Marc Palardy-Sim ◽  
Guillaume Renaud ◽  
Michael Jakubinek ◽  
Farjad Shadmehri
Keyword(s):  
Composite Material ◽  
Modeling And Simulation ◽  
Experimental Testing ◽  
Morphing Wing ◽  
3D Printed

scholarly journals Mechanical design, analysis and testing of a large-range compliant microgripper

2016 ◽  
Vol 7 (1) ◽  
pp. 119-126 ◽  
Author(s):  
Yilin Liu ◽  
Qingsong Xu
Keyword(s):  
Large Range ◽  
Mechanical Design ◽  
Experimental Testing ◽  
Design Analysis ◽  
Element Analysis ◽  
Amplification Ratio ◽  
Testing Procedures ◽  
Dual Stage ◽  
Fea Simulation ◽  
Simulation Results

Abstract. This paper presents the mechanical design, analysis, fabrication, and testing procedures of a new large-range microgripper which is based on a flexible hinge structure. The uniqueness of the gripper is that the gripper arms not only provide large gripping range but also deliver approximately rectilinear movement as the displacement in nonworking direction is extremely small. The large gripping range is enabled by a mechanism design based on dual-stage flexure amplifier to magnify the stroke of piezoelectric actuator. The first-stage amplifier is a modified version of the Scott Russell (SR) mechanism and the second-stage amplifier contains a parallel mechanism. The displacement amplification ratio of the modified SR mechanism in the gripper has been enlarged to 3.56 times of the conventional design. Analytical static models of the gripper mechanism are developed and validated through finite-element analysis (FEA) simulation. Results show that the gripping range is over 720 µm with a resonant frequency of 70.7 Hz and negligible displacement in nonworking direction. The total amplification ratio of the input displacement is 16.13. Moreover, a prototype of the gripper is developed by using aluminium 7075 for experimental testing. Experimental results validate the analytical model and FEA simulation results. The proposed microgripper can be employed in various microassembly applications such as pick-and-place of optical fibre.

Design, numerical simulation and experimental testing of a controlled electrical actuation system in a real aircraft morphing wing model

2015 ◽  
Vol 119 (1219) ◽  
pp. 1047-1072 ◽  
Author(s):  
R. M. Botez ◽  
M. J. Tchatchueng Kammegne ◽  
L. T. Grigorie
Keyword(s):  
Experimental Testing ◽  
Experimental Studies ◽  
Morphing Wing ◽  
Theoretical Simulation ◽  
Actuation Mechanism ◽  
Wing Model ◽  
Actuation System ◽  
Structural Rigidity ◽  
Bench Testing ◽  
And Control

AbstractThe paper focuses on the modelling, simulation and control of an electrical miniature actuator integrated in the actuation mechanism of a new morphing wing application. The morphed wing is a portion of an existing regional aircraft wing, its interior consisting of spars, stringers, and ribs, and having a structural rigidity similar to the rigidity of a real aircraft. The upper surface of the wing is a flexible skin, made of composite materials, and optimised in order to fulfill the morphing wing project requirements. In addition, a controllable rigid aileron is attached on the wing. The established architecture of the actuation mechanism uses four similar miniature actuators fixed inside the wing and actuating directly the flexible upper surface of the wing. The actuator was designed in-house, as there is no actuator on the market that could fit directly inside our morphing wing model. It consists of a brushless direct current (BLDC) motor with a gearbox and a screw for pushing and pulling the flexible upper surface of the wing. The electrical motor and the screw are coupled through a gearing system. Before proceeding with the modelling, the actuator is tested experimentally (stand alone configuration) to ensure that the entire range of the requirements (rated or nominal torque, nominal current, nominal speed, static force, size) would be fulfilled. In order to validate the theoretical, simulation and standalone configuration experimental studies, a bench testing and a wind-tunnel testing of four similar actuators integrated on the real morphing wing model are performed.

scholarly journals Lift distribution of washout twist morphing MAV wing

2018 ◽  
Vol 7 (4.13) ◽  
pp. 89
Author(s):  
N. I. Ismail ◽  
H. Yusoff ◽  
Hazim Sharudin ◽  
Arif Pahmi ◽  
H. Hafi ◽  
...  
Keyword(s):  
Experimental Testing ◽  
Aerodynamic Performance ◽  
Special Test ◽  
Morphing Wing ◽  
Test Rig ◽  
Biologically Inspired ◽  
Air Vehicle ◽  
Membrane Wing ◽  
Stall Angle ◽  
Wing Deformation

Micro Air Vehicle, or also commonly known as MAV, is a miniature aircraft that has been gaining interest in the industry. MAV is defined as a flying platform with 15cm wingspan and operates at a speed of around 10m/s. Recently, MAV has been exposed with the latest development and link towards the biologically-inspired designs such as morphing wing. Twist morphing wing is one of the latest MAV wing design developments. The application of Twist Morphing (TM) on MAV wing has been previously known to produce better aerodynamic performance. Previous study in washin TM wing has shown a promising possibility of generating higher lift force. Despite the benevolent performance exhibited by the washin TM wing, the lift distribution for the washout type of TM MAV is relatively unknown and still open to be explored. This is probably due to the lack of experimental test rig to produce the washout twist morphing motion on the MAV wing. Therefore, this research aims to produce a special test rig for washout TM wing that is compatible for wind tunnel experimental testing. By using the special test rig, the experimental investigation on the lift performance of washout TM MAV wing can be done. Based on the wing deformation results, it clearly shows that the proposed test rig is capable to produce up to 19.5mm tip deflection at the morphing point, which is also resulting in a significant morphing motion. Higher morphing force induces larger morphing motion. Based on the lift distribution results, they show that the morphing motion has significantly affected the overall lift distribution on the MAV wing. The morphing motion on TM wing has produced at least 17.6% and 5.33% lower CL and CLmax magnitude, respectively, with the membrane wing especially at the pre-stall region. However, the TM wing is still able to maintain the stall angle similar to the baseline wing at αstall= 31°. By maintaining high αstall value with lower CL and CLmax magnitude, TM wing produces more agility for the MAV maneuverability that will be useful for indoor mission or obstacle avoidance flight.  

scholarly journals Design and experimental testing of a control system for a morphing wing model actuated with miniature BLDC motors

2020 ◽  
Vol 33 (4) ◽  
pp. 1272-1287 ◽  
Author(s):  
Teodor Lucian GRIGORIE ◽  
Shehryar KHAN ◽  
Ruxandra Mihaela BOTEZ ◽  
Mahmoud MAMOU ◽  
Youssef MÉBARKI
Keyword(s):  
Control System ◽  
Experimental Testing ◽  
Morphing Wing ◽  
Wing Model
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