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

Afonso, Frederico; Coelho, Mónica B.; Vale, José; Lau, Fernando; Suleman, Afzal

doi:10.3390/aerospace7110166

Cited by 9 publications

(7 citation statements)

References 36 publications

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“…Various design and manufacturing aspects were discussed and analyzed, while normal modes for both models were obtained both numerically, as well as experimentally and compared via the Modal Assurance Criterion (MAC). Furthermore, the aeroelastic scaling of a reduced scaled wing model designed with three different scaling sets of primary quantities was investigated in [17]. The results in terms of aerodynamics, structural dynamics as well as the nonlinear aeroelastic response of the scaled models were compared with the one estimated for the full-size model.…”

Section: Motivationmentioning

confidence: 99%

Towards Structural and Aeroelastic Similarity in Scaled Wing Models: Development of an Aeroelastic Optimization Framework

Filippou,

Kilimtzidis,

Kotzakolios

et al. 2024

Aerospace

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The pursuit of more efficient transport has led engineers to develop a wide variety of aircraft configurations with the aim of reducing fuel consumption and emissions. However, these innovative designs introduce significant aeroelastic couplings that can potentially lead to structural failure. Consequently, aeroelastic analysis and optimization have become an integral part of modern aircraft design. In addition, aeroelastic testing of scaled models is a critical phase in aircraft development, requiring the accurate prediction of aeroelastic behavior during scaled model construction to reduce costs and mitigate the risks associated with full-scale flight testing. Achieving a high degree of similarity between the stiffness, mass distribution and flow field characteristics of scaled models and their full-scale counterparts is of paramount importance. However, achieving similarity is not always straightforward due to the variety of configurations of modern lightweight aircraft, as identical geometry cannot always be directly scaled down. This configuration diversity has a direct impact on the aeroelastic response, necessitating the use of computational aeroelasticity tools and optimization algorithms. This paper presents the development of an aeroelastic scaling framework using multidisciplinary optimization. Specifically, a parametric Finite Element Model (FEM) of the wing is created, incorporating the parameterization of both thickness and geometry, primarily using shell elements. Aerodynamic loads are calculated using the Doublet Lattice Method (DLM) employing twist and camber correction factors, and aeroelastic coupling is established using infinite plate splines. The aeroelastic model is then integrated within an Ant Colony Optimization (ACO) algorithm to achieve static and dynamic similarity between the scaled model and the reference wing. A notable contribution of this work is the incorporation of internal geometry parameterization into the framework, increasing its versatility and effectiveness.

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Section: Motivationmentioning

confidence: 99%

Towards Structural and Aeroelastic Similarity in Scaled Wing Models: Development of an Aeroelastic Optimization Framework

Filippou,

Kilimtzidis,

Kotzakolios

et al. 2024

Aerospace

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“…Beam-ribs with variable cross-section were applied to the horizontal tail model to obtain a reasonable mass distribution and stiffness distribution. Compared to the flat-plate wing model, the present three-dimensional model may have more similar dynamic characteristics to the actual aircraft [28][29][30][31][32]. In addition, the thicknesses of the bending and torsion leaf-springs were selected as 3.5 mm and 3.2 mm, respectively.…”

Section: Model Design and Manufacturementioning

confidence: 99%

Experimental Aeroelastic Investigation of an All-Movable Horizontal Tail Model with Bending and Torsion Free-Plays

Bai

Qian

et al. 2023

Aerospace

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In this study, an experimental investigation is performed on a scaled, all-movable horizontal tail to study the aeroelastic behaviors induced by multiple free-plays. The dynamic response in wind tunnel tests is measured by strain gauges, an accelerometer, and a binocular vision measurement system. The obtained results indicate that the present aeroelastic system exhibits highly nonlinear characteristics and undergoes two independent limit cycle oscillations (LCOs) induced by bending free-play and torsion free-play, respectively. Further, various parametric studies are conducted to evaluate the effects of the free-play angles, angle of attack, flow velocity, and gust excitation on the LCOs. It is found that the value of free-play angle has no significant effect on the critical flow velocity which leads to the occurrence of LCOs. The amplitude and frequency of LCOs increase with the increasing free-play angle and flow velocity. Moreover, the horizontal tail experiences high-order harmonic resonances when LCOs appear. Finally, the stability of limit cycles is analyzed based on the gust excitation experiment. Overall, compared to an all-movable horizontal tail with single free-play, the multiple free-plays system exhibits more complex dynamic behaviors. In this paper, the measured results of the scaled model, which has a similar mass distribution and stiffness distribution as actual aircraft, may be valuable for predicting such LCOs induced by multiple free-plays, and providing a reference for the design of all-movable horizontal tail to prevent LCOs.

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“…Besides, previous studies on free-play-induced LCO mostly focused on two-dimensional airfoil models, and studies on the influence of free-play nonlinearity on 3D models are further needed. [35][36][37] Therefore, one convenient method which can be efficiently applied to any 3D model with complex structures, and can be verified experimentally is demanded.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic investigation on an all-movable horizontal tail with free-play nonlinearity

Ai,

Bai,

Qian

et al. 2023

Journal of Low Frequency Noise, Vibration and Active Control

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Free-play-induced nonlinear dynamic behavior has been one of the most important topics of aeroelastic research in recent decades. In this paper, the describing function (DF) method is developed to investigate the complex dynamic response of a popular all-movable horizontal tail with free-play. Piecewise expressions for the time history and phase portrait of limit cycle oscillation (LCO) are derived by the developed DF method, which is conducive to understand the mechanism of free-play-induced LCO. Another advantage of the developed DF method is the ability to predict the high-order harmonics, which cannot be realized by the classic DF method. A three-dimensional (3D) all-movable horizontal tail model with torsional free-play was designed and manufactured to implement wind tunnel tests via various initial parameters. A good agreement was found between the numerical and experimental results, which can demonstrate the effectiveness of the proposed method. The influence of the initial parameters of the all-movable horizontal tail on the LCO characteristics is analyzed by both numerical calculations and wind tunnel tests. The method and results in this paper can provide a significant reference for the design of all-movable horizontal tail versus the free-play-induced LCO.

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

Cited by 9 publications

References 36 publications

Towards Structural and Aeroelastic Similarity in Scaled Wing Models: Development of an Aeroelastic Optimization Framework

Towards Structural and Aeroelastic Similarity in Scaled Wing Models: Development of an Aeroelastic Optimization Framework

Experimental Aeroelastic Investigation of an All-Movable Horizontal Tail Model with Bending and Torsion Free-Plays

Aeroelastic investigation on an all-movable horizontal tail with free-play nonlinearity

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