Buckling strength optimization of laminated composite plates

Chai, Gin Boay; Ooi, Kim Tiow; Khong, P.W.

doi:10.1016/0045-7949(93)90169-e

Cited by 21 publications

(7 citation statements)

References 3 publications

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“…Jana & Bhaskar (2006) carried out a buckling analysis of a simply supported rectangular plate without cutout subjected to various types of non-uniform compressive loads. Chai et al (1993) investigated the influence of boundary conditions, plate aspect ratios on the optimal ply angle and associated optimal buckling loads of anti-symmetrically laminated composite plates without cutout under various linearly varying in-plane loading conditions. Hu et al (2003) examined the buckling behaviour of a graphite/epoxy symmetrically laminated composite rectangular plate without cutout under parabolic variation of axial loads.…”

Section: Introductionmentioning

confidence: 99%

Buckling analysis of rectangular composite plates with rectangular cutout subjected to linearly varying in-plane loading using fem

Narayana¹,

Rao²,

Kumar³

2014

Sadhana

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A numerical study is carried out using finite element method, to examine the effects of square and rectangular cutout on the buckling behavior of a sixteen ply quasi-isotropic graphite/epoxy symmetrically laminated rectangular composite plate [0 • /+45 • /-45 • /90 • ] 2s, subjected to various linearly varying in-plane compressive loads. Further, this paper addresses the effects of size of square/rectangular cutout, orientation of square/rectangular cutout, plate aspect ratio(a/b), plate length/thickness ratio(a/t), boundary conditions on the buckling bahaviour of symmetrically laminated rectangular composite plates subjected to various linearly varying in-plane compressive loading. It is observed that the various linearly varying in-plane loads and boundary conditions have a substantial influence on buckling strength of rectangular composite plate with square/rectangular cutout.

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Section: Introductionmentioning

confidence: 99%

Buckling analysis of rectangular composite plates with rectangular cutout subjected to linearly varying in-plane loading using fem

Narayana¹,

Rao²,

Kumar³

2014

Sadhana

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“…The displacement field of a rectangular shear deformable plate can be expressed as (1) From the theory of large displacement, the strain-displacement relations can be written as 2aand 2bwhere () ,x and () ,y represent partial differentiation with respect to x and y. The relationship between stress resultants and the strain terms for the laminated plate may be written as (3) and the shear resultants may be written as (4) where stretching, stretching-bending and bending stiffnesses are defined as (5) where [Q ij ] k represents transformed plane stress reduced stiffness matrix of the kth lamina, which is a function of ply-angles (θ 1 , θ 2 , θ 3 . .…”

Section: Finite Element Formulationmentioning

confidence: 99%

“…Many investigators [1][2][3][4] in the past studied the thermal buckling behavior of laminated plates. Chai et al [5] optimized the ply-angles of anti-symmetric laminated composite plates subjected to in-plane compression using complex optimization technique. Shin et al [6] optimized the relative ply-thicknesses of symmetric laminated plates for maximum buckling load.…”

Section: Introductionmentioning

confidence: 99%

Optimum Design of Laminated Composite Plates for Maximum Thermal Buckling Loads

SINGHA

RAMACHANDRA

BANDYOPADHYAY

2000

Journal of Composite Materials

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Buckling temperatures of graphite/epoxy laminated composite plates are maximized for a given total thickness considering fiber-directions and relative thicknesses of layers as design variables. Thermal buckling analysis is carried out using the finite element method with 4 node shear deformable plate element, while genetic algorithm (GA) is employed to optimize as many as ten variables for the five layered plates. In addition to traditional three-operator approach, i.e., reproduction, crossover and mutation, other variants of GAs such as the elitist model, two-point crossover models are also discussed. The study includes composite plates of three different aspect ratios, two support conditions and three different numbers of layers. The presented results reveal that the buckling loads can be increased significantly with appropriately orienting the fiber directions and varying the thickness of different layers. The authors also recommend the judicious selection of specific thicknesses and fiber orientations needed for the practical implementation highlighting the importance of their theoretical values so that they may also be made available in near future for fabrication.

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“…Jana and Bhaskar [1] carried out a buckling analysis of a simply supported rectangular plate subjected to various types of non-uniform compressive loads. Chai et al [2] investigated the influence of boundary conditions, plate aspect ratios on the optimal ply angle and associated optimal buckling loads of antisymmetric laminated composite plates under various linearly varying in-plane loading conditions. Hurang Hu et al [3] investigated the buckling behavior of a graphite/epoxy symmetrically laminated composite rectangular plate under parabolic variation of axial loads.…”

Section: Introductionmentioning

confidence: 99%

Buckling analysis of anti-symmetric cross and angle-ply laminated composite plates

Bouyaya

2018

Matériaux & Techniques

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This article has for objective to analyze the buckling behavior of the unidirectional laminated plates. In this purpose, we propose an analytically method, based on the theory of classical, orthotropic plate theory. The governing equations are solved using Navier solution for uniform uniaxial loading in longitudinal direction. We were interested to identify the critical buckling load for simply supported antisymmetric cross-ply and antisymmetric angle-ply laminates of rectangular shape. Some important progress has been made on these relatively complicated buckling problems, involving coupling between bending and midplane stretching during a buckling deformation. Effects of different parameters such as fiber orientation angles, aspect ratio, modular ratio and number of layers were examined. Results are presented in the form of plots showing the variation in non-dimensional buckling load.

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Buckling strength optimization of laminated composite plates

Cited by 21 publications

References 3 publications

Buckling analysis of rectangular composite plates with rectangular cutout subjected to linearly varying in-plane loading using fem

Buckling analysis of rectangular composite plates with rectangular cutout subjected to linearly varying in-plane loading using fem

Optimum Design of Laminated Composite Plates for Maximum Thermal Buckling Loads

Buckling analysis of anti-symmetric cross and angle-ply laminated composite plates

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