Buckling analysis of laminated composite and sandwich beams by the finite element method

Kahya, Volkan

doi:10.1016/j.compositesb.2016.01.031

Cited by 52 publications

(18 citation statements)

References 27 publications

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“…Table 1 shows the convergence study for the buckling analysis of laminated composite under boundary condition of CC, CF, HH and CH support. Table 1 also presented the validation of dimensionless critical buckling load (ω × a 2 )/(E 2 × bh 3 ) with the results available in [23,31] and it shows that present results using C ∘ FEM through HSDT the agreement with available results using FSDT and refined beam theory. The effective convergence results are obtained from initial, so for the convenience 30 number of elements were selected for the further study.…”

Section: Convergence and Validation Studymentioning

confidence: 52%

“…In the Table 2, the accuracy of the present HSDT with FEM model of laminated composite beam is checked by comprising it with the [23,49,50]. For the validation purpose E 1 = 25 × E 2 , G 12 = 0.5 × E 2 , G 12 = G 13 , G 23 = 0.2 × E 2 , and υ 12 = 0.25 properties are get utilized with different stacking sequence (nL) and varying aspect ratio of the beam.…”

Section: Convergence and Validation Studymentioning

confidence: 99%

“…Using classical laminate theory (CLT) buckling behaviour examined with varying plate aspect ratio. Kahya et al [23] analyzed the composite laminated beam (CLB) by FEM for predicting the buckling response using first order shear deformation (FSDT) theory under different boundary conditions and laminate stacking sequence. Atlihan [24] investigated the buckling response of the laminated composite beam by application of unit compressive load over free end of the beam.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Thermo-Mechanical Post Buckling Analysis of Multiwall Carbon Nanotube-Reinforced Composite Laminated Beam under Elastic Foundation

Lal

Markad

2019

Curved and Layered Structures

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In present paper, buckling analysis is performed over laminated composite beam incorporating multi walled carbon nanotube (MWCNT) polymer matrix and then reinforced with E-glass fiber in an orthotropic manner under inplane varying thermal and mechanical loads by finite element method (FEM). Aim of the study is to develop a model which accurately perform the buckling deterministic analysis of multi-walled carbon nanotube reinforced composite laminated beam (MWCNTRCLB) with the evaluation of material property by applying Halpin–Tsai model. Combined Higher order shear deformation theory and Pasternak elastic foundation based on von Karman nonlinear kinematics and Winkler cubic nonlinearity respectively, are successfully implemented. Through minimum potential energy principle, generalized static analysis is performed using FEM, based on interactive MATLAB coding. The critical buckling load and critical buckling temperature is presented under the action of inplane variable mechanical and thermal load, with different boundary conditions, beam thickness ratio and MWCNT aspect ratio, variation with MWCNT volume fraction and coefficient of thermal expansion, with and without foundation for linear and nonlinear cases.

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Section: Convergence and Validation Studymentioning

confidence: 52%

Section: Convergence and Validation Studymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Thermo-Mechanical Post Buckling Analysis of Multiwall Carbon Nanotube-Reinforced Composite Laminated Beam under Elastic Foundation

Lal

Markad

2019

Curved and Layered Structures

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“…On the basis of Ritz method, Mantari and Canales [27,28] presented the analytical solutions for free vibration and buckling analysis of laminated beams. Kahya [29] developed a finite element model based on FSDT, for buckling analysis of composite beams. As well as, Osman and Suleiman [30] presented a isoparametric three-node element for free vibration of laminated beams.…”

Section: Introductionmentioning

confidence: 99%

A new three-node element for bending, free vibration and buckling analysis of composite laminated beams based on FSDT theory

Karkon

2020

J Braz. Soc. Mech. Sci. Eng.

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In this paper, a new three-node element with three degrees of freedom per node is proposed for bending, free vibration and buckling analysis of laminated beams. The element's formulation is based on the first-order shear deformation theory (FSDT). For this aim, transverse displacement and rotation field of the element are selected from fifth and fourth order, respectively. Moreover, the shear strain is varied as quadratic function throughout the element. It is worth noting that the quadratic function can be used for axial displacement field. By employing equilibrium equation, curvature and shear strain relations of laminated beam with FSDT theory, the exact and explicit shape functions of the displacement fields are obtained. By utilizing the obtained shape functions, the explicit form of the stiffness matrix is calculated for the element. On the other hand, by using the governing equation of the free vibration and buckling of the beam, the explicit form of the translation and rotary mass matrices, and geometric stiffness matrix of the element are obtained. It should be mentioned, the proposed element is free of shear locking. Finally, several numerical tests fulfill to assess the robustness of the developed element. For this purpose, bending, free vibration and buckling analysis of laminated beams with different boundary conditions and aspect ratios are performed. The results of the numerical tests demonstrate high accuracy and efficiency of the proposed element for free vibration and buckling analysis of laminated beams.

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“…Many researchers have experimentally and numerically examined the post-buckling behaviour of pristine and impacted composite stiffened panels subjected to compression [12]- [20]. Numerical investigations of CAI behaviour can capture the inter-laminar and intra-laminar damage initiation and propagation.…”

Section: Introductionmentioning

confidence: 99%

Numerical FEA parametric analysis of CAI behaviour of CFRP stiffened panels

Gaitanelis

Giannopoulos

Theotokoglou

2019

Thin-Walled Structures

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This paper examined the effect of numerical modelling parameters on the accuracy and computational efficiency of Carbon Fibre Reinforced Polymer (CFRP) stiffened panels under Compression After Impact (CAI). Pristine and damaged CFRP stiffened panels were subjected to compression in Abaqus ® software using Cohesive Zone Model (CZM) method. Various case studies were examined and the effect of the stiffness parameters of the cohesive elements was critically assessed. Moreover, the required number of cohesive zones to fully capture the damage mechanisms of the impacted and pristine panels under compressive loading was examined. The results showed that a wrong set of parameters can even lead to neglecting the induced damage and can cause severe convergence problems in the numerical model. The importance of the Overall Meshing Factor (OMF) was highlighted and a user-defined subroutine (USDFLD) was applied to capture the decrease in the load bearing capability of an impacted panel prior to the compressive loading, since CZM was found insufficient for this scope. The above-mentioned remarks illustrated the process of investigating the optimum numerical parameters set to achieve an accurate and efficient finite element modelling of the stiffened panels structural performance and maximum load-carrying capability, when subjected to CAI loading.

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Buckling analysis of laminated composite and sandwich beams by the finite element method

Cited by 52 publications

References 27 publications

Thermo-Mechanical Post Buckling Analysis of Multiwall Carbon Nanotube-Reinforced Composite Laminated Beam under Elastic Foundation

Thermo-Mechanical Post Buckling Analysis of Multiwall Carbon Nanotube-Reinforced Composite Laminated Beam under Elastic Foundation

A new three-node element for bending, free vibration and buckling analysis of composite laminated beams based on FSDT theory

Numerical FEA parametric analysis of CAI behaviour of CFRP stiffened panels

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