Non-linear aeroelastic analysis in the time domain of high-aspect-ratio wings: Effect of chord and taper-ratio variation

Suleman, Afzal; Afonso, Frederico; Vale, José; Oliveira, Éder; Lau, Fernando

doi:10.1017/aer.2016.94

Cited by 8 publications

(10 citation statements)

References 61 publications

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“…With the goal of integrating the capabilities of analysing morphing solutions and novel configurations in a multidisciplinary design optimization environment, a computational framework was developed in the scope of the EU FP7 NOVEMOR project. To expand the potentialities of this tool in preliminary aircraft design, an aeroelastic module was devised with the possibilities of running linear and non-linear static aeroelastic analyses (3,35) . This framework was designed to be both modular and versatile.…”

Section: Developed Framework/methodologymentioning

confidence: 99%

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Non-linear aeroelastic response of high aspect-ratio wings in the frequency domain

et al. 2017

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A current trend in the aeronautic industry is to increase the wing aspect ratio to enhance aerodynamic efficiency by reducing the induced drag and thus reduce fuel consumption. Despite the associated benefits of a large aspect ratio, such as higher lift-to-drag ratios and range, commercial aircraft usually have a relatively low aspect ratio. This is partially explained by the fact that the wing becomes more flexible with increasing aspect ratio and thus more prone to large deflections, which can cause aeroelastic instability problems such as flutter. In this work, an aeroelastic study is conducted on a rectangular wing model of 20 m span and variable chord for a low subsonic speed condition to evaluate the differences between linear and non-linear static aeroelastic responses. Comparisons between linear and non-linear displacements, natural frequencies and flutter boundary are performed. An in-house non-linear aeroelastic framework was employed for this purpose. In this work, the influence of the aspect ratio and geometric non-linearity (highly deformed states) is assessed in terms of aeroelastic performance parameters: flutter speed and divergence speed. A nearly linear correlation of flutter speed difference (relative to linear analysis results) with vertical-tip displacement difference is observed. The flutter and divergence speeds vary substantially as the wing aspect ratio increases, and the divergence speeds always remain above the flutter speed. Furthermore, the flutter mechanism was observed to change as the wing chord is decreased.

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Section: Developed Framework/methodologymentioning

confidence: 99%

“…For this work, an in-house non-linear aeroelastic framework (3,35) with the capability of analysing the aeroelastic behaviour of very flexible low-speed aircraft was used.…”

Section: Introductionmentioning

confidence: 99%

Non-linear aeroelastic response of high aspect-ratio wings in the frequency domain

et al. 2017

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“…An in-house nonlinear aeroelastic framework described in [33,34] was used in this work. This framework is capable of analyzing flexibility effects on high aspect-ratio wings in the time domain considering both constrained, i.e., simulating wind tunnel conditions, and unconstrained i.e., emulating free-flight conditions, models.…”

Section: Aeroelastic Frameworkmentioning

confidence: 99%

“…Despite the use of low-medium fidelity aerodynamic (3D panel method with viscous and compressibility corrections) and structural (3D condensed beam model based on wing-box mass and inertia calculations) models, their applicability to preliminary design is adequate since they capture the main physical phenomena and allow exploring the design space [35,36]. The aerodynamic, structural and aeroelastic models were benchmarked [33,34] with existing data available in the literature. Furthermore, the application of this framework to estimate the aeroelastic behavior of both full and reduced size models ensures comparability between these models.…”

Section: Aeroelastic Frameworkmentioning

confidence: 99%

On the Design of Aeroelastically Scaled Models of High Aspect-Ratio Wings

et al. 2020

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Recently, innovative aircraft designs were proposed to improve aerodynamic performance. Examples include high aspect ratio wings to reduce the aerodynamic induced drag to achieve lower fuel consumption. Such solution when combined with a lightweight structure may lead to aeroelastic instabilities such as flutter at lower air speeds compared to more conventional wing designs. Therefore, in order to ensure safe flight operation, it is important to study the aeroelastic behavior of the wing throughout the flight envelope. This can be achieved by either experimental or computational work. Experimental wind tunnel and scaled flight test models need to exhibit similar aeroelastic behavior to the full scale air vehicle. In this paper, three different aeroelastic scaling strategies are formulated and applied to a flexible high aspect-ratio wing. These scaling strategies are first evaluated in terms of their ability to generate reduced models with the intended representations of the aerodynamic, structural and inertial characteristics. Next, they are assessed in terms of their potential in representing the unsteady non-linear aeroelastic behavior in three different flight conditions. The scaled models engineered by exactly scaling down the internal structure suitably represent the intended aeroelastic behavior and allow the performance assessment for the entire flight envelope. However, since both the flight and wind tunnel models are constrained by physical and budgetary limitations, custom built structural models are more likely to be selected. However, the latter ones are less promising to study the entire flight envelope.

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“…Flutter is an undesirable phenomenon that may take place in an aeroelastic wing. One way to predict the flutter speed is via theoretical calculations based on experimentally obtained wing parameters (1)(2)(3)(4)(5) . Most of these parameters are physically uncertain due to manufacturing and operational conditions.…”

Section: Introductionmentioning

confidence: 99%

Fuzzy uncertainty analysis and reliability assessment of aeroelastic aircraft wings

Rezaei¹,

Fazelzadeh²,

Mazidi³

et al. 2020

Aeronaut. j.

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In the present study, fuzzy uncertainty and reliability analysis of aeroelastic aircraft wings are investigated. The uncertain air speed and structural parameters are represented by fuzzy triangular membership functions. These uncertainties are propagated through the wing model using a fuzzy interval approach, and the uncertain flutter speed is obtained as a fuzzy variable. Further, the reliability of the wing flutter is based on the interference area in the pyramid shape defined by the fuzzy flutter speed and air speed. The ratio between the safe region volume and the total volume of the pyramid gives the reliability value. Two different examples are considered—a typical wing section, and a clean wing—and the results are given for various wind speed conditions. The results show that the approach considered is a low-cost but suitable method to estimate the reliability of the wing flutter speed in the presence of uncertainties.

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Non-linear aeroelastic analysis in the time domain of high-aspect-ratio wings: Effect of chord and taper-ratio variation

Cited by 8 publications

References 61 publications

Non-linear aeroelastic response of high aspect-ratio wings in the frequency domain

Non-linear aeroelastic response of high aspect-ratio wings in the frequency domain

On the Design of Aeroelastically Scaled Models of High Aspect-Ratio Wings

Fuzzy uncertainty analysis and reliability assessment of aeroelastic aircraft wings

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