Closed-Loop Control Validation of a Morphing Wing Using Wind Tunnel Tests

Попов, А. В.; Grigorie, Teodor Lucian; Botez, Ruxandra Mihaela; Mamou, Mahmoud; Mébarki, Youssef

doi:10.2514/1.47281

Cited by 72 publications

(40 citation statements)

References 5 publications

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“…The elbow joint has one degree of freedom: q 3 , which allows the wings to contract or extend in sync with the flapping motion. The wrist joint has three degrees of freedom: q 4 , q 5 , q 6 . Each angle allows for the rotation of metacarpophalangeal (MCP) digits III, IV and V about axes z 4 , z 5 , z 6 respectively.…”

Section: Wing-framesmentioning

confidence: 99%

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Inertial attitude control of a bat-like morphing-wing air vehicle

Colorado¹,

Barrientos²,

Rossi³

et al. 2012

Bioinspir. Biomim.

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Abstract.This article presents a novel bat-like micro air vehicle inspired by the morphing-wing mechanism of bats. The goal of this paper is twofold. Firstly, a modelling framework is introduced for analysing how the robot should maneuver by means of changing wing morphology. This allows the definition of requirements for achieving forward and turning flight according to the kinematics of the wing modulation. Secondly, an attitude controller named backstepping+DAF is proposed. Motivated by the biological fact about the influence of wing inertia on the production of body accelerations, the attitude control law incorporates wing inertia information to produce desired roll (φ) and pitch (θ) acceleration commands (DAF function). This novel control approach is aimed at incrementing net body forces (F net ) that generate propulsion. Simulations and wind-tunnel experimental results have shown an increase about 23% in net body force production during the wingbeat cycle when the wings are modulated using the DAF function as a part of the backstepping control law. Results also confirm accurate attitude tracking in spite of high external disturbances generated by aerodynamic loads at airspeeds up to 5ms −1 . Inertial Attitude Control of a Bat-like Morphing-wing Micro Air Vehicle2

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Section: Wing-framesmentioning

confidence: 99%

“…The possibility of having actuated wings has allowed the design of new mechanisms that improve over classical fixed/rotary-wings MAV flight performance. As a result, different morphing-wing concepts and materials have emerged together with control methodologies that allow for accurate wing-actuation [4], [5], [6], [7], [8], [9].…”

Section: Introductionmentioning

confidence: 99%

Inertial attitude control of a bat-like morphing-wing air vehicle

Colorado¹,

Barrientos²,

Rossi³

et al. 2012

Bioinspir. Biomim.

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“…increase lift, decreased drag or combinations. The actuators change the airfoil shape during the flight by means of a PID controller [12][13][14]. [7,9,15].…”

Section: Application Of the Morphing Wing Concept On Uas-s4mentioning

confidence: 99%

Morphing Wing Application on Hydra Technologies UAS-S4

Segui¹,

Gabor²,

Koreanschi³

et al. 2017

Modelling, Identification and Control

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This paper presents the aerodynamic results of a morphing wing study performed on the UAS S4 Éhecatl from Hydra Technologies. Only the cruise phase of the aircraft was considered (constant altitude and constant speed). The difference, from an aerodynamic point of view, between the morphing wing and the original wing was emphasized by computing and comparing their longitudinal aerodynamic coefficients (drag and lift). The computation of the aerodynamic characteristics was done using tornado with the Vortex Lattice Method.

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“…In the open-loop configuration, the desired displacements were directly imposed on the system [25], while a novel, adaptive, neurofuzzy approach which was used to predict and control the morphing wing performance [26]. In the closed-loop configuration, the displacements were automatically determined as a function of the pressure readings from the wing upper surface [27,28]. In addition, two new controllers were developed; the first one was based on an optimal combination of the bi-positional and Proportional-Integral (PI) laws [29,30], while the second one was a hybrid fuzzy logic-PID controller [31,32].…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation and wind tunnel tests investigation and validation of a morphing wing-tip demonstrator aerodynamic performance

Gabor

Koreanschi

Botez

et al. 2016

Aerospace Science and Technology

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/npsi/ctrl?action=rtdoc&an=21277526&lang=en http://nparc.cisti-icist.nrc-cnrc.gc.ca/npsi/ctrl?action=rtdoc&an=21277526&lang=fr READ THESE TERMS AND CONDITIONS CAREFULLY BEFORE USING THIS WEBSITE.http://nparc.cisti-icist.nrc-cnrc.gc.ca/npsi/jsp/nparc_cp.jsp?lang=en Vous avez des questions? Nous pouvons vous aider. Pour communiquer directement avec un auteur, consultez la première page de la revue dans laquelle son article a été publié afin de trouver ses coordonnées. Si vous n'arrivez pas à les repérer, communiquez avec nous à PublicationsArchive-ArchivesPublications@nrc-cnrc.gc.ca. Questions? Contact the NRC Publications Archive team atPublicationsArchive-ArchivesPublications@nrc-cnrc.gc.ca. If you wish to email the authors directly, please see the first page of the publication for their contact information. NRC Publications Archive Archives des publications du CNRCThis publication could be one of several versions: author's original, accepted manuscript or the publisher's version. / La version de cette publication peut être l'une des suivantes : la version prépublication de l'auteur, la version acceptée du manuscrit ou la version de l'éditeur. For the publisher's version, please access the DOI link below./ Pour consulter la version de l'éditeur, utilisez le lien DOI ci-dessous. This paper presents the results obtained from the numerical simulation and experimental wind tunnel testing of a morphing wing equipped with a flexible upper surface and controllable actuated aileron. The technology demonstrator is representative of a real aircraft wing tip section, and it was developed following a complex, multidisciplinary design process. The model was fitted with a composite material upper skin whose shape can be morphed, as a function of the flight condition, by four electrical actuators placed inside the wing structure. The optimizations were performed with the aim of controlling the extent of the laminar flow region, and the resulting shapes were scanned using high-precision photogrammetry. The numerical simulations were performed using Computational Fluid Dynamics (CFD) and included a model for predicting the laminar-to-turbulent flow transition over the entire wing surface. The analyses included cases with three aileron deflection angles and angles of attack situated within five degrees range. The CFD results were compared with infrared thermography measurements in terms of transition location, surface pressure measurements and balance loads measurements acquired during subsonic wind tunnel tests performed at the National Research Council Canada.

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Closed-Loop Control Validation of a Morphing Wing Using Wind Tunnel Tests

Cited by 72 publications

References 5 publications

Inertial attitude control of a bat-like morphing-wing air vehicle

Inertial attitude control of a bat-like morphing-wing air vehicle

Morphing Wing Application on Hydra Technologies UAS-S4

Numerical simulation and wind tunnel tests investigation and validation of a morphing wing-tip demonstrator aerodynamic performance

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