Optimized design of an active extrados structure for an experimental morphing laminar wing

Coutu, Daniel; Braïlovski, Vladimir; Terriault, Patrick

doi:10.1016/j.ast.2010.01.009

Cited by 39 publications

(25 citation statements)

References 19 publications

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“…27,28) To study this phenomenon, the JavaFoil airfoil analysis program 29) is used to investigate the aerodynamic characteristics of the designed morphing airfoil in order to determine the effect of altering the location and number of actuation forces. The JavaFoil program is able to calculate the distribution of the velocity on the airfoil surface and integrate it to obtain the lift and the moment coefficient.…”

Section: Morphing Airfoil Aerodynamics Simulationmentioning

confidence: 99%

Design and Analysis of a Morphing Composite Airfoil Using Unbalanced Layup and Unconventional Ply Angles

Bourchak

Dobah

2014

Trans. Japan Soc. Aero. S Sci.

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Design of morphing wings is being considered as a potential way to improve aircraft performance. Composite materials are identified as suitable candidates to achieve some of the future morphing capabilities of aircraft wings. In this work, a morphing airfoil is designed and manufactured using a woven carbon fiber reinforced plastic (CFRP) composite material and a vacuum bagging technique. The layup arrangement and stacking sequence are chosen for maximum out-of-plane deflection under the applied actuation force using finite element analysis (FEA) and composite plate bending experiments. Additionally, manual actuation loads are applied simultaneously at various feasible locations on the airfoil top surface. The morphed airfoil new shape is studied using a JavaFoil airfoil analysis program to investigate its aerodynamic characteristics in terms of lift vs. angle of attack and lift-to-drag ratio vs. angle of attack. It is found that the numbers and locations of actuation forces depend on the flight envelope stage (e.g., take-off and cruising). In general, four factors are identified to have significant effects on the maximum deflection and consequently the ease of the airfoil to morph. These factors are the ply angles, the unbalanced stacking sequence, and the number of actuation forces and their location along the airfoil skin.

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Section: Morphing Airfoil Aerodynamics Simulationmentioning

confidence: 99%

Design and Analysis of a Morphing Composite Airfoil Using Unbalanced Layup and Unconventional Ply Angles

Bourchak

Dobah

2014

Trans. Japan Soc. Aero. S Sci.

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“…Many studies have focused on active flow control by considering the employment of SMAs elements for actuation purposes. Examples of morphing applications regard the improvement of the global efficiency of aircraft wings [3][4][5], noise reduction during aircraft take-off [6], the development of a rotor blade control system [7], the fabrication of actuators for tracking helicopter blades while in-flight [8], and the application of aerodynamic control devices for wind turbine blades [9,10]. The notion of smart advanced blades, which can control themselves and reduce (or eliminate) the need for an active control system, is an appealing solution in blade technology to increase efficiency at several different flow regimes.…”

Section: Introductionmentioning

confidence: 99%

Analysis of the Aerodynamic and Structural Performance of a Cooling Fan with Morphing Blade

Suman

Fortini

Aldi

et al. 2017

IJTPP

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Abstract:The concept of smart morphing blades, which can control themselves to reduce or eliminate the need for active control systems, is a highly attractive solution in blade technology. In this paper, an innovative passive control system based on Shape Memory Alloys (SMAs) is proposed. On the basis of previous thermal and shape characterization of a single morphing blade for a heavy-duty automotive cooling axial fan, this study deals with the numerical analysis of the aerodynamic loads acting on the fan. By coupling computational fluid dynamics and finite element method approaches, it is possible to analyze the actual blade shape resulting from both the aerodynamic and centrifugal loads. The numerical results indicate that the polymeric blade structure ensures proper resistance and enables shape variation due to the action of the SMA strips.

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“…The studies can be grouped into four broad approaches: material engineering, active mechanical design, semi-active techniques and elastic structural behavior manipulation. A "Morphing Laminar Wing" (MLW) [4] concept has been introduced and it has a flexible skin and actuators connected by a transmission system. It is capable of inducing friction drag reduction by extending the laminar flow over an active wing extrados and it has been proven effective for subsonic aerodynamic conditions.…”

Section: Introductionmentioning

confidence: 99%

Experimental and FEM Modal Analysis of a Deployable-Retractable Wing

Jia¹,

Lai²,

Zhang³

et al. 2014

MME

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The aim of this paper is to conduct experimental modal analysis and numerical simulation to verify the structural characteristics of a deployable-retractable wing for aircraft and spacecraft. A modal impact test was conducted in order to determine the free vibration characteristics. Natural frequencies and vibration mode shapes were obtained via measurement in LMS Test. Lab. The frequency response functions were identified and computed by force and acceleration signals, and then mode shapes of this morphing wing structure were subsequently identified by PolyMAX modal parameter estimation method. FEM modal analysis was also implemented and its numerical results convincingly presented the mode shape and natural frequency characteristics were in good agreement with those obtained from experimental modal analysis. Experimental study in this paper focuses on the transverse response of morphing wing as its moveable part is deploying or retreating. Vibration response to different rotation speeds have been collected, managed and analyzed through the use of comparison methodology with each other. Evident phenomena have been discovered including the resonance on which most analysis is focused because of its potential use to generate large amplitude vibration of specific frequency or to avoid such resonant frequencies from a wide spectrum of response. Manufactured deployable-retractable wings are studied in stage of experimental modal analysis, in which some nonlinear vibration resulted should be particularly noted because such wing structure displays a low resonant frequency which is always optimal to be avoided for structural safety and stability.

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Optimized design of an active extrados structure for an experimental morphing laminar wing

Cited by 39 publications

References 19 publications

Design and Analysis of a Morphing Composite Airfoil Using Unbalanced Layup and Unconventional Ply Angles

Design and Analysis of a Morphing Composite Airfoil Using Unbalanced Layup and Unconventional Ply Angles

Analysis of the Aerodynamic and Structural Performance of a Cooling Fan with Morphing Blade

Experimental and FEM Modal Analysis of a Deployable-Retractable Wing

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