Optimization of postbuckling behaviour of variable thickness composite panels with variable angle tows: Towards “Buckle-Free” design concept

Wu, Zhangming; Raju, Gangadharan; Weaver, Paul M.

doi:10.1016/j.ijsolstr.2017.08.037

Cited by 71 publications

(27 citation statements)

References 30 publications

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“…Similar study is made considering laminate with induced defects under compressive load by Venkatachari et al . Wu et al have recently dealt with the optimization of postbuckling behavior of panel with variable tow angle and obtained the first‐level optimal solutions in terms of lamination parameters. The effect of various structural models in predicting the mechanical and thermal behavior of curvilinear fiber‐reinforced composite laminates is assessed in the work of Venkatachari et al .…”

Section: Introductionmentioning

confidence: 91%

“…The lamina made of such fibers is referred as 〈 θ 1 θ 2 〉. The fiber path function x 2 and the associated orientation angle θ ( x 1 )that permit for a wide range of properties are defined for the k th lamina as .

x_{2} = ({, \begin{array}{c} \frac{a}{2 ((), θ_{1} - θ_{0})} ({}, - \ln ((), \cos θ_{0}) + \ln false[\cos false(θ_{0} - 2 ((), θ_{1} - θ_{0}) x_{1} / a false]) - \frac{a}{2} \leq x_{1} \leq 0 \\ \frac{a}{2 ((), θ_{1} - θ_{0})} ({}, \ln ((), \cos θ_{0}) - \ln false[\cos false(θ_{0} + 2 ((), θ_{1} - θ_{0}) x_{1} / a false]) 0 \leq x_{1} \leq \frac{a}{2} \end{array})

θ ((), x_{1}) = ({, \begin{array}{c} - \frac{2}{a} ((), θ_{2} - θ_{1}) x_{1} + θ_{1} - \frac{a}{2} \leq x_{1} \leq 0 \\ \frac{2}{a} ((), θ_{2} - θ_{1}) x_{1} + θ_{1} 0 \leq x_{1} \leq \frac{a}{2} \end{array})

…”

Section: Theoretical Formulationmentioning

confidence: 99%

“…To avoid kinking, it is a general practice followed in the manufacturing process by limiting the magnitude of the maximum curvature value for any ply in the direction of fiber path less than certain allowable value. For instance, at each point along the fiber path, the magnitude of the curvature κ is limited to <3.28 m −1 . In case the fiber curvature constraint is not satisfied along the fiber path direction, such ply is eliminated for manufacturing.…”

Section: Theoretical Formulationmentioning

confidence: 99%

See 2 more Smart Citations

Thermoelastic Stability Behavior of Curvilinear Fiber‐Reinforced Composite Laminates With Different Boundary Conditions

et al. 2018

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In this article, the thermoelastic stability behavior of curvilinear fiber‐reinforced composite laminates is investigated using a shear flexible plate theory. The laminate is composed of layers that make use of curvilinear fibers to create spatial variation of stiffness due to the continuous change of fiber orientation within the lamina. Such composite laminates, subjected to different thermal loads like uniform and non‐uniform temperature distributions, are considered in this analysis. The governing equations obtained using the principle of minimization of total potential energy, are solved for evaluating the critical buckling temperature. The displacement fields of pre‐buckling of the laminate are evaluated before proceeding for the thermal buckling analysis. The formulation is checked against available solutions in the literature. A detailed parametric study considering important design parameters such as curvilinear fiber angles, lay‐up, thickness ratio, coefficients of thermal expansion, and modular ratio on the thermoelastic stability/buckling behavior of composite laminates is made. The present analysis highlights the substantial change in the critical buckling loads due to the curvilinear fiber angles, lay‐up and boundary conditions. The new results presented here for curvilinear fiber‐reinforced composite laminate with clamped/mixed boundary conditions may be useful in assessing similar studies based on higher‐order theories or other numerical studies. POLYM. COMPOS., 40:2876–2890, 2019. © 2018 Society of Plastics Engineers

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Section: Introductionmentioning

confidence: 91%

x_{2} = ({, \begin{array}{c} \frac{a}{2 ((), θ_{1} - θ_{0})} ({}, - \ln ((), \cos θ_{0}) + \ln false[\cos false(θ_{0} - 2 ((), θ_{1} - θ_{0}) x_{1} / a false]) - \frac{a}{2} \leq x_{1} \leq 0 \\ \frac{a}{2 ((), θ_{1} - θ_{0})} ({}, \ln ((), \cos θ_{0}) - \ln false[\cos false(θ_{0} + 2 ((), θ_{1} - θ_{0}) x_{1} / a false]) 0 \leq x_{1} \leq \frac{a}{2} \end{array})

θ ((), x_{1}) = ({, \begin{array}{c} - \frac{2}{a} ((), θ_{2} - θ_{1}) x_{1} + θ_{1} - \frac{a}{2} \leq x_{1} \leq 0 \\ \frac{2}{a} ((), θ_{2} - θ_{1}) x_{1} + θ_{1} 0 \leq x_{1} \leq \frac{a}{2} \end{array})

…”

Section: Theoretical Formulationmentioning

confidence: 99%

Section: Theoretical Formulationmentioning

confidence: 99%

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Thermoelastic Stability Behavior of Curvilinear Fiber‐Reinforced Composite Laminates With Different Boundary Conditions

et al. 2018

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“…Since, the benefits of VAT have been used and researched numerically into increasing mechanical properties, such as stiffness [19], buckling [10,18,20,44] and post-buckling [43,42,35] capabilities for laminates alone, or along the interac- tion of stiffeners in a bay design [15,32] and linear buckling of VAT filament-wound cylinders [38]. These benefits have been proven in experiments to increase properties in different applications, such as bending [37] and buckling for cylinders [24,25] and plates [27,29].…”

Section: Introductionmentioning

confidence: 99%

Modelling of fibre steered plates with coupled thickness variation from overlapping continuous tows

Vertonghen¹,

Castro²

2020

Preprint

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Previous research has hinted on further improvements of the buckling behaviour of variable-stiffness laminates by incorporating overlaps, resulting in a variable thickness profile that is non-linearly coupled to the steering angles. The present study compares two modelling strategies to consider the variable thickness distribution: 1) as manufactured with discrete thicknesses; and 2) smoothed with a continuous thickness distribution. The as-manufactured discrete thickness created by overlapping tows is obtained by means of virtually manufactured laminates. The smeared approximation is much simpler to implement, whereby the local thickness is a non-linear function of the local steering angle. Linear buckling analyses are performed by means of fast semi-analytical models based on the Ritz method using hierarchical polynomials and classical plate formulation. By assuming a smooth manufacturing mould on one side, a one-sided thickness variation is produced, resulting in non-symmetric laminates for which the mid-plane surface is varied accordingly. Modelling guidelines are provided regarding the use of the smeared model in a study covering a wide range of geometries, loading and boundary conditions. With these guidelines, one can apply the smeared thickness technique in semi-analytical models to reach a correlation within ±5% compared to a costly discrete-thickness finite element model.

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“…In a curved panel with VAT laminates, the boundary conditions and fiber angles considerably influence the buckling and dynamic instability behavior [31]. Furthermore, it has been reported that fiber placement at an angle of 0° and thickness build-up at transversely supported regions of composite panels can help realize a high axial compressive stiffness [32].…”

Section: Introductionmentioning

confidence: 99%

Effect of Fiber Orientation Path on the Buckling, Free Vibration, and Static Analyses of Variable Angle Tow Panels

Fallahi

Viglietti²,

Carrera

et al. 2020

FU Mech Eng

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In this work, the effect of the fiber orientation on the mechanical response of variable angle tow (VAT) panels is investigated. A computationally efficient high-order one-dimensional model, derived under the framework of the Carrera unified formulation (CUF), is used. In detail, a layerwise approach is adopted to predict the complex phenomena that may appear in VAT panels. Static, free-vibration and buckling analyses are performed, considering several material properties, geometries, and boundary conditions, and the results are assessed with those obtained using existing approaches. Considering the findings of the comparative analysis, several best design practices are suggested to improve the mechanical performances of VAT panels.

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Optimization of postbuckling behaviour of variable thickness composite panels with variable angle tows: Towards “Buckle-Free” design concept

Cited by 71 publications

References 30 publications

Thermoelastic Stability Behavior of Curvilinear Fiber‐Reinforced Composite Laminates With Different Boundary Conditions

Thermoelastic Stability Behavior of Curvilinear Fiber‐Reinforced Composite Laminates With Different Boundary Conditions

Modelling of fibre steered plates with coupled thickness variation from overlapping continuous tows

Effect of Fiber Orientation Path on the Buckling, Free Vibration, and Static Analyses of Variable Angle Tow Panels

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