Effects of Unbalanced Lamination Parameters on the Static Aeroelasticity of a High Aspect Ratio Wing

Li, Jinyang; Wang, Junli; Ren, Zhigui; Wei, Weifeng

doi:10.1155/2021/3949078

Cited by 2 publications

(3 citation statements)

References 25 publications

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“…When the unbalanced coefcient is 0.5 (balanced lay-up), the structural deformation is minimal, and subsequently either decreasing or increasing the unbalanced coefcient will lead to an increase in the deformation of the laminate. Tis is in agreement with the description of the paper [28].…”

Section: Efect Of Unbalanced Coefcients On Structural Failuresupporting

confidence: 91%

“…In the spatial discretization term, the viscous fux vector is chosen in the central format and the convective fux vector is chosen in the Roe-FDS format. In the time discretization term, the LU-SGS implicit time discretization method is used to advance the solution [27,28]. Te boundary conditions at the wing root are set as symmetric boundary conditions, the wing surface is set as no-slip boundary conditions, and the rest are set as pressure far-feld boundary conditions.…”

Section: Computational Modelmentioning

confidence: 99%

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Failure Analysis and Optimization Design of Wing Skin Unbalanced Lay-Up

Wang

2022

Advances in Materials Science and Engineering

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To clarify the influence of the unbalanced coefficient and the change in lay-up angle on the failure characteristics of the laminate in the static aeroelastic problem of the aircraft, numerical simulations were performed based on the classical laminate theory and the Tsai-Wu failure criterion, as well as the fluid-structure coupling calculation method. The structure’s stress-strain and failure curves are found to decrease as the unbalanced coefficient increases. The stress curve’s slope is relatively stable, whereas the strain and failure curves’ slopes change three times, indicating that strain may be the primary cause of structural failure. Unbalanced coefficient laminates are classified into three types based on their mechanical properties low unbalanced coefficient laminates (Unbalanced coefficient 0.2 to 0.3), quasi-balanced coefficient laminates (Unbalanced coefficient 0.4 to 0.6, Balanced laminate when the Unbalanced coefficient is 0.5), and high unbalanced coefficient laminates (Unbalanced coefficient 0.7 to 0.8). Within their respective spanning intervals, the mechanical properties of the three types of laminates remain relatively stable. An increase in the ply angle reduces both the elastic deformation of the structure and the failure factor. The variation patterns of structural strain and failure at 45° and 60° ply angles decrease as unbalanced coefficients increase, whereas the opposite is true for 30° ply angles. Finally, a two-level optimization method based on “equalized plies” and “equal-angle plies” was developed, resulting in a 23.93% reduction in elastic deformation and a 37.04% reduction in the laminated structure's failure coefficient when compared to the preoptimization results.

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Section: Efect Of Unbalanced Coefcients On Structural Failuresupporting

confidence: 91%

Section: Computational Modelmentioning

confidence: 99%

Failure Analysis and Optimization Design of Wing Skin Unbalanced Lay-Up

Wang

2022

Advances in Materials Science and Engineering

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“…They reduced the original variables and derived the analytical solution of simply supported plates and verified it. Li et al [7] discussed the relationship between the distribution law of static aeroelastic deformation and the unbalanced coefficient of high-aspectratio wing with layering unbalanced coefficient as a single variable. Xu et al and Mostefa and Yousef [8,9] studied the deformed wing by numerical simulation and experiment, taking into account the influence of layering angle, layer thickness and position, and other variables according to the finite element analysis method.…”

Section: Introductionmentioning

confidence: 99%

Effect of Aeroelastic Tailoring Design on Wing Mode

Wang

et al. 2023

International Journal of Aerospace Engineering

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In this paper, in order to clarify the influence of structural parameters of laminates on the modal characteristics of high-aspect-ratio wings under prestress, the CFD/CSD coupling method was used to study the modal characteristics of nonlinear structures under the influence of layering angle, layering unbalanced coefficient, and layering reference direction. The results show that the first six order modal frequencies of wing structure increase with the increase of layering angle, and the increment change of frequency increases with the increase of layering angle. The frequency results of positive and negative layering angles are basically the same, and there is no great difference. The modal frequency of airfoil structure is not very sensitive to the change of unbalanced coefficient. The modal frequencies obtained by the mixed angle layering scheme are obviously larger than those obtained by the layering scheme composed of only two angles. With the change of the reference direction of laying, the lowest frequency is generally present in the 0° reference direction and has one or two minima in each order of modal frequency. The layer reference direction angle mainly in the second quadrant is beneficial to the enhancement of modal frequency. After determining the related layer parameters, the appropriate adjustment of the layer reference direction will be beneficial to change the vibration characteristics of the wing structure.

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Effects of Unbalanced Lamination Parameters on the Static Aeroelasticity of a High Aspect Ratio Wing

Cited by 2 publications

References 25 publications

Failure Analysis and Optimization Design of Wing Skin Unbalanced Lay-Up

Failure Analysis and Optimization Design of Wing Skin Unbalanced Lay-Up

Effect of Aeroelastic Tailoring Design on Wing Mode

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