A finite element parametric modeling technique of aircraft wing structures

Tang, Jiapeng; Xi, Pengcheng; Baoyuan, Zhang; Hu, Bifu

doi:10.1016/j.cja.2013.07.019

Cited by 25 publications

(12 citation statements)

References 11 publications

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“…Mode shapes for rigidity coupling = 2×106 and various geometric coupling of cantilever wing It appears clearly from Tables 3, 4 and 5 that the three first naturel frequencies , and are almost similar for the Dynamic Stiffness Method[1] with the cubic and high-order finite element formulations varying both geometric coupling and material coupling .Figs. 3, 4and 5 show the bending and torsion mode shapes of the three first natural frequencies of cubic and high-order formulations for the coupled bending-torsional composite wing.…”

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confidence: 77%

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Measurement of vibrations of composite wings using high-order finite element beam

Bennamia¹,

Badereddine²,

Zebbiche³

2018

J. meas. eng.

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The purpose of this study is to show the influence of bending-torsion coupling on natural frequencies and mode shapes of aircraft wings by using two finite element beam formulations. The bending-torsion coupling parameters are the geometric parameter (distance between the mass axis and elastic axis of the cross-section of the beam) and the material coupling due to laminated composites. Cubic and high-order Hermite finite element interpolations are presented in this study, in order to show the influence of geometric and material coupling on natural frequencies and mode shapes. Starting by the governing partial differential equations of motion for the coupled bending-torsion beam with the bending and torsion equations, the Galerkin's method is used with high-order finite element interpolation to obtain the high-order Hermitian shape functions. The mass and stiffness matrices are obtained using the kinetic energy and potential energy, respectively. The beam finite element has two nodes, the cubic element has three degrees of freedom at each end (transvers displacement, slope and torsion), where the high order element has five degrees of freedom at each end (transvers displacement, slope, curvature, gradient of curvature and torsion). The mass matrix contains geometric coupling terms and the stiffness matrix contains terms of material bending-torsion coupling. The obtained results using cubic and high-order finite element Euler-Bernoulli beam formulations are compared for a free vibration analysis of Goland metallic wing (geometric coupling) and validated with Dynamic Stiffness Method for composite wings.

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confidence: 77%

“…A finite element parametric modeling technique of aircraft wing structures is given by Tang and Xi. [6]. The composite beam models are used to study the dynamic response and aeroelasticity for high-aspect-ratio of composite wings [7][8][9][10].…”

Section: Introductionmentioning

confidence: 99%

Measurement of vibrations of composite wings using high-order finite element beam

Bennamia¹,

Badereddine²,

Zebbiche³

2018

J. meas. eng.

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“…The Finite Element Method (FEM) and TO have been considered to represent significant tools in the aircraft design area (17) . Integrated application of FEM and TO for an aircraft can result in a significant weight reduction, thereby saving material costs without impacting the final model's robustness or strength properties (18,19) . The optimisation processes achieved by combining CFD with Computational Structural Mechanics (CSM) result in the determination of a wing shape with optimal aerodynamic performance in all operational flight conditions while keeping its minimum design weight (20) .…”

Section: Introductionmentioning

confidence: 99%

Wing component allocation for a morphing variable span of tapered wing using finite element method and topology optimisation – application to the UAS-S4

et al. 2021

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This work presents the Topology Optimisation of the Morphing Variable Span of Tapered Wing (MVSTW) using a finite element method. This topology optimisation aims to assess the feasibility of internal wing components such as ribs, spars and other structural components. This innovative approach is proposed for the telescopic mechanism of the MVSTW, which includes the sliding of the telescopically extended wing into the fixed wing segment. The optimisation is performed using the tools within ANSYS Mechanical, which allows the solving of topology optimisation problems. This study aims to minimise overall structural compliance and maximise stiffness to enhance structural performance, and thus to meet the structural integrity requirements of the MVSTW. The study evaluates the maximum displacements, stress and strain parameters of the optimised variable span morphing wing in comparison with those of the original wing. The optimised wing analyses are conducted on four wingspan extensions, that is, 0%, 25%, 50% and 75%, of the original wingspan, and for different flight speeds to include all flight phases (17, 34, 51 and 68m/s, respectively). Topology optimisation is carried out on the solid wing built with aluminium alloy 2024-T3 to distribute the wing components within the fixed and moving segments. The results show that the fixed and moving wing segments must be designed with two spar configurations, and seven ribs with their support elements in the high-strain area. The fixed and moving wing segments’ structural weight values were reduced to 16.3 and 10.3kg from 112 to 45kg, respectively. The optimised MVSTW was tested using different mechanical parameters such as strains, displacements and von Misses stresses. The results obtained from the optimised variable span morphing wing show the optimal mechanical behaviour and the structural wing integrity needed to achieve the multi-flight missions.

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“…The Finite Element Method (FEM) and topology optimization (TO) have been linked with computer-aided engineering (CAE), and they are now considered the most advanced tools and methodologies in the aircraft design field. The combination of the FEM with TO makes it possible to obtain major weight reductions, thus resulting in material and fuel savings while maintaining the final product's robustness properties [19,20]. Furthermore, optimization methods based on merging CFD with CSM allow the determination of the optimal wing shape, which could decrease the aircraft's weight by obtaining its optimal aerodynamic performance [21].…”

Section: Introductionmentioning

confidence: 99%

Structural Sizing and Topology Optimization Based on Weight Minimization of a Variable Tapered Span-Morphing Wing for Aerodynamic Performance Improvements

2021

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This article proposes the integration of structural sizing, topology, and aerodynamic optimization for a morphing variable span of tapered wing (MVSTW) with the aim to minimize its weight. In order to evaluate the feasibility of the morphing wing optimization, this work creates a numerical environment by incorporating simultaneous structural sizing and topology optimization based on its aerodynamic analysis. This novel approach is proposed for an MVSTW. A problem-specific optimization approach to determine the minimum weight structure of the wing components for its fixed and moving segments is firstly presented. The optimization was performed using the OptiStruct solver inside HyperMesh. This investigation seeks to minimize total structure compliance while maximizing stiffness in order to satisfy the structural integrity requirements of the MVSTW. The aerodynamic load distribution along the wingspan at full wingspan extension and maximum speed were considered in the optimization processes. The wing components were optimized for size and topology, and all of them were built from aluminum alloy 2024-T3. The optimization results show that weight savings of up to 51.2% and 55.7% were obtained for fixed and moving wing segments, respectively. Based on these results, the optimized variable-span morphing wing can perform certain flight missions perfectly without experiencing any mechanical failures.

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A finite element parametric modeling technique of aircraft wing structures

Cited by 25 publications

References 11 publications

Measurement of vibrations of composite wings using high-order finite element beam

Measurement of vibrations of composite wings using high-order finite element beam

Wing component allocation for a morphing variable span of tapered wing using finite element method and topology optimisation – application to the UAS-S4

Structural Sizing and Topology Optimization Based on Weight Minimization of a Variable Tapered Span-Morphing Wing for Aerodynamic Performance Improvements

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