Numerical analysis of the residual ultimate strength of composite laminates under uniaxial compressive load

Alizadeh, F.; Sebdani, R. Mazruee; Soares, C. Guedes

doi:10.1016/j.compstruct.2022.116161

Cited by 5 publications

(2 citation statements)

References 37 publications

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“…Non-linear FE analysis was performed on laminated stiffened panels under compression load to find buckling behavior and failure load of the panel by using FEM-based ANSYS software [95]. The residual ultimate load and delamination of laminate as shown in figure 4 were found under in-plane compression load by using a developed method of FEM virtual crack closure technique [96]. The non-linear dynamic buckling was studied with a variation of loading duration, loading function, and geometry parameter of plate-stiffener by using FE software Abaqus to obtain dynamic buckling load and first ply failure of the panels [97].…”

Section: Application Of Finite Element Software Based On Femmentioning

confidence: 99%

A review on buckling of the laminated composite panel under in-plane load

Kumar,

Kant,

Poddar

et al. 2024

Eng. Res. Express

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The review paper deals with a literature review on buckling analysis by different methods of laminated plates with different types of stiffeners which has been conducted in recent years. Analytical studies, experimental studies, finite element analysis, and other computational methods have been implemented by researchers on the stiffened panels under compression and shear for determination of the buckling behavior of the panel with I-type, blade-type, T-type, and hat-stiffeners. Some literature has been found on the panel with the influence of variation of the stiffener depth for the determination of buckling capacity. Very few literatures, non-linear finite element (FE) have been implemented for the determination of the effect of debonding damage between plate-stiffener of the panel but have not been reported parametric data about the effect of cohesive parameters of plate-stiffener and delamination of plies of the composites stiffened panel for post-buckling analysis. This paper also provides a literature survey based on the buckling performance of the plates with the application of different shapes of stiffeners.

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Section: Application Of Finite Element Software Based On Femmentioning

confidence: 99%

A review on buckling of the laminated composite panel under in-plane load

Kumar,

Kant,

Poddar

et al. 2024

Eng. Res. Express

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“…1a) due to their excellent properties such as high strength-to-weight and stiffness-to-weight ratios, good corrosion and fatigue resistance [1,2]. In contrast to the aerospace industry, the marine industry currently prefers the use of glass fibre-reinforced plastics (GFRP) over carbon fibre-reinforced plastics (CFRP) due to high manufacturing costs, and these composite materials have been utilized in the construction of both complete ship hulls [3,4] and constituent parts [5][6][7][8][9][10][11]. However, as the dimensions of marine structures (such as ships and offshore wind turbines) have been steadily increasing over time (see Fig.…”

Section: Introductionmentioning

confidence: 99%

Free and Forced Vibration Analysis of Carbon/Glass Hybrid Composite Laminated Plates Under Arbitrary Boundary Conditions

Li,

Guedes Soares,

Liu

et al. 2024

Appl Compos Mater

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This paper presents the theoretical investigations on the free and forced vibration behaviours of carbon/glass hybrid composite laminated plates with arbitrary boundary conditions. The unknown allowable displacement functions of the physical middle surface are expressed in terms of standard cosine Fourier series and sinusoidal auxiliary functions to ensure the continuity of the displacement functions and their derivatives at the structural boundaries. Arbitrary boundary conditions are achieved through the introduction of an artificial spring technique. The first shear deformation theory and Lagrange equations are utilized to derive the energy expression, and the eigenvalue equations associated with free and forced vibration are obtained by Rayleigh-Ritz variational operations. Subsequently, these equations are then solved to determine the natural frequency, mode of vibration, and the steady-state displacement response under forced excitation. The new results are compared with those from references and finite element methods to verify the convergence, accuracy and efficiency of the analytical method. The effects of hybrid ratios, stacking sequences, lamination schemes, fibre orientation, boundary conditions and excitation force on the free and forced vibration behaviours of the carbon/glass hybrid composite laminated plates are analyzed in detail.

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