Buckling of laminated composite and sandwich beams due to axially varying in-plane loads

Karamanlı, Armağan; Aydoğdu, Metin

doi:10.1016/j.compstruct.2018.11.067

Cited by 39 publications

(16 citation statements)

References 51 publications

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“…Also, as the orientation angle is get increased, the critical buckling load parameter shows the significant effect. Observed results follow the same nature and close agreement with the result presented in [32] using deformable beam theory. Table 3 elaborate the detailed analysis of the three layered laminated composite beam for the critical buckling analysis under distributed compressive N mx 1 loading with varying the thickness ratio of beam under CC bound- ary condition.…”

Section: Convergence and Validation Studysupporting

confidence: 88%

“…Also relation between classical and shear deformation theory were established. Karamanli and Aydogdu [32] performed the buckling analysis of CLB with the inplane variable load with different boundary conditions and beam aspect ratio.…”

Section: Introductionmentioning

confidence: 99%

“…Geometrical configuration of MWCNTRCLB under variable polynomial inplane loading Variation of axially variable inplane buckling load through the beam length[32] …”

mentioning

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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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 Studysupporting

confidence: 88%

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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“…In the case of tubes and pressure vessels, the angle of fibre location (depending on the target strength properties) is determined to the nearest 1°. Due to the complexity of the problem, the optimisation of composite structures is more difficult and poses an interesting problem for the researchers [ 12 , 13 , 14 ]. The problem of stability in carbon composite (CFRP) thin-walled profiles with open cross-sections has been widely studied [ 15 , 16 , 17 , 18 , 19 , 20 , 21 , 22 ].…”

Section: Introductionmentioning

confidence: 99%

Optimisation of the Thin-Walled Composite Structures in Terms of Critical Buckling Force

Szklarek

Gajewski

2020

Materials

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The paper presents the optimisation of thin-walled composite structures on a representative sample of a thin-walled column made of carbon laminate with a channel section-type profile. The optimisation consisted of determining the configuration of laminate layers for which the tested structure has the greatest resistance to the loss of stability. The optimisation of the layer configuration was performed using two methods. The first method, divided into two stages to reduce the time, was to determine the optimum arrangement angle in each laminate layer using finite element methods (FEM). The second method employed artificial neural networks for predicting critical buckling force values and the creation of an optimisation tool. Artificial neural networks were combined into groups of networks, thereby improving the quality of the obtained results and simplifying the obtained neural networks. The results from computations were verified against the results obtained from the experiment. The optimisation was performed using ABAQUS® and STATISTICA® software.

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“…Thus, a large number of works has been recently published to conceive novel structural solutions, systems, and devices, while adopting different types of reinforcement phase, such as graphene nanoplatelets [6][7][8][9][10][11][12][13][14], or carbon nanotubes [15][16][17][18][19]. Among a large variety of numerical strategies, higher order theories represent the most useful tool for the investigation of the static and dynamic response of materials at different scales [20][21][22][23][24]. Classical theories, indeed, beams with arbitrary lay-ups.…”

Section: Introductionmentioning

confidence: 99%

A Modified Couple Stress Elasticity for Non-Uniform Composite Laminated Beams Based on the Ritz Formulation

et al. 2020

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Due to the large application of tapered beams in smart devices, such as scanning tunneling microscopes (STM), nano/micro electromechanical systems (NEMS/MEMS), atomic force microscopes (AFM), as well as in military aircraft applications, this study deals with the vibration behavior of laminated composite non-uniform nanobeams subjected to different boundary conditions. The micro-structural size-dependent free vibration response of composite laminated Euler–Bernoulli beams is here analyzed based on a modified couple stress elasticity, which accounts for the presence of a length scale parameter. The governing equations and boundary conditions of the problem are developed using the Hamilton’s principle, and solved by means of the Rayleigh–Ritz method. The accuracy and stability of the proposed formulation is checked through a convergence and comparative study with respect to the available literature. A large parametric study is conducted to investigate the effect of the length-scale parameter, non-uniformity parameter, size dimension and boundary conditions on the natural frequencies of laminated composite tapered beams, as useful for design and optimization purposes of small-scale devices, due to their structural tailoring capabilities, damage tolerance, and their potential for creating reduction in weight.

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Buckling of laminated composite and sandwich beams due to axially varying in-plane loads

Cited by 39 publications

References 51 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

Optimisation of the Thin-Walled Composite Structures in Terms of Critical Buckling Force

A Modified Couple Stress Elasticity for Non-Uniform Composite Laminated Beams Based on the Ritz Formulation

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