Design and wind tunnel experimental validation of a controlled new rotary actuation system for a morphing wing application

Kammegne, Michel Joël Tchatchueng; Grigorie, Teodor Lucian; Botez, Ruxandra Mihaela; Koreanschi, Andreea

doi:10.1177/0954410015588573

Cited by 21 publications

(8 citation statements)

References 30 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…It is known that the flow surrounding a blunt body is mainly formed by pressure drag, and a small fraction of it is due to friction drag. The flow structure seen in Figure 17 contains the major components of a turbulent flow calculated with fluctuations of the mean flow speed, as described by the turbulence intensity I in Equation (10). In Figure 17, at position 1, the flow separates from the radar surface, and the flow transitions to its turbulent state with its intensity close to 20.6%.…”

Section: Original Radar Flow Analysismentioning

confidence: 99%

“…The LARCASE laboratory is one of the few multidisciplinary aerospace research laboratories in Canada that has four pieces of stateof-the-art research equipment, such as a Cessna Citation X Business Aircraft Research Flight Simulator, a Bombardier series regional jet CRJ-700 Research Flight Simulator, an Autonomous Aerial System UAS-S4 from Hydra Technologies and a Subsonic Wind Tunnel Price-Païdoussis. At the LARCASE, new methodologies in the aeronautical industry have been developed in the areas of actuated morphing wings and wing-tip systems [5][6][7], upper surface optimization of wing shapes for unmanned aerial systems [8][9][10][11], and Computational Fluid Dynamics models validations with experimental results from subsonic wind tunnel tests [12,13].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

New Numerical and Measurements Flow Analyses Near Radars

2021

Self Cite

View full text Add to dashboard Cite

An experimental and numerical investigation of the flow near a blunt body has been conducted in this study. Most experimental methods of flow studies use flow visualization and probes introduction into the flow field. The main goal of this research was the development of a new methodology to analyze flows, and to measure flow characteristics without taking into account the distorting effects of measuring probes. A series of experiments were performed on a ground surveillance radar in the Price-Païdoussis subsonic wind tunnel. Forces and moments were measured as functions of wind speeds and angular positions by the use of a six-component aerodynamic scale. A Computational Fluid Dynamics three-dimensional model was employed to analyze the wake region of the ground surveillance radar. A turbulence reduction system was proposed and analyzed in this research. The use of the proposed turbulence reduction system was found to be an effective way to reduce turbulent flow intensity by 50%, drag coefficients by 9.6%, and delay the flow transition point by 7.6 times.

show abstract

Section: Original Radar Flow Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

New Numerical and Measurements Flow Analyses Near Radars

2021

Self Cite

View full text Add to dashboard Cite

show abstract

“…Following this perspective, Kammegne et al 25,26 developed a control law for the position of an electrical actuator used in conjunction with a mechanical system inserted inside the wing. The goal was to reduce the drag by moving the transition location towards the trailing edge.…”

Section: Introductionmentioning

confidence: 99%

A wind tunnel tested control system for a morphing wing actuation mechanism

Kammegne

Botez

Grigorie

et al. 2016

AIAA Atmospheric Flight Mechanics Conference

View full text Add to dashboard Cite

The technique of morphing takes its origin from the bird flight and allows an airplane to change its original configuration during flight depending on the flight conditions. The main objective of the morphing is to improve the mission performance in order to optimize and control the fuel consumption efficiency. The experimental results of a morphing wing concept are presented on a part of the upper surface of the wing which is flexible. The wing was equipped with an aileron which was considered as a separated wing's entity. The objective was to reduce the drag by delaying or by moving the transition point towards the trailing edge. Another project objective was to compare the aerodynamics effects of the rigid aileron with the aerodynamic effects of the morphing aileron. The shape of the wing upper surface was modified by a set of four miniature electrical actuators inserted directly inside the wing. The positions of the actuators were controlled by four different controllers. These controllers have been designed based on the actuators simulation models. Three sets of wind tunnel tests have been performed with the manufactured demonstrator. Experimental resultsrevealed a promising controller behavior. The visualization of the flow over the wing upper surface was done with the infrared measurement technique. Using the same technique, the transition region location was estimated and compared with transition location determined by the pressure sensors array installed in the wing upper surface. Nomenclature M = Mach number α = Angle of attack β = Deflection angle CRIAQ = Consortium for Research and Innovation in Aerospace in Quebec LVDT = Linear Variable Differential Transducer

show abstract

“…In previous studies, our LARCASE team has developed morphing wing mechanisms which, by modifying the upper surface of the wing, allow the flow transition delay between the laminar and turbulent regimes around the wing [18][19][20][21][22][23][24]. This delay has the effect of reducing the drag generated by the wing.…”

Section: Introductionmentioning

confidence: 99%

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

Communier¹,

Botez²,

Wong³

2020

Aerospace

Self Cite

View full text Add to dashboard Cite

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.

show abstract

Design and wind tunnel experimental validation of a controlled new rotary actuation system for a morphing wing application

Cited by 21 publications

References 30 publications

New Numerical and Measurements Flow Analyses Near Radars

New Numerical and Measurements Flow Analyses Near Radars

A wind tunnel tested control system for a morphing wing actuation mechanism

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

Contact Info

Product

Resources

About