Buckling of cross-ply laminates subject to linearly varying compressive loads and in-plane boundary restraints

Abstract

In-plane prebuckling stresses arise under axial edge loading as a result of a plate boundary being restrained from deformation in the plane of the plate. These stresses exhibit a uniform distribution only under a special set of boundary conditions and in general such uniform in-plane stress distributions do not exist under most boundary conditions encountered in practice. In the present study, in-plane prebuckling stresses are investigated for various in-plane boundary constraints and the stress contour lines are given for rectangular cross-ply laminated plates under linearly varying edge loads. The second part of the article involves the computation of the optimal layer thickness to maximize the buckling load under various combinations of in-plane boundary restraints. The numerical solutions are obtained by finite elements based on first-order shear deformable plate theory which include the in-plane deformations as nodal degrees of freedom. Numerical results show that the exclusion of the in-plane restraints may lead to errors in stability calculations and consequently in the design of laminated plates.

Buckling of laminated composite plate with various shapes of holes under uniform/nonuniform mechanical and thermal loading

“…In Equation (11), k scf is the shear correction factor. In first-order shear deformation theory the out plane shears effect is assumed to be constant and for considering this effect a constant as shear correction factor is multiplied to the shear elements of shear properties matrix.…”

“…The aforementioned researchers considered constant inplane loading, while in many situations load may vary along the edges of the plate. Some researchers [10][11][12][13][14][15][16] have focused on the buckling responses of laminates with holes under the uniform/nonuniform varying load. Zong and Gu [10] performed buckling response analysis of laminated panels under uniformly varying compression and presented an exact solution.…”

“…They noted that buckling load using uniform loading were nonconservative for nonuniform loading. Cagdas and Adali [11] considered the influence of edge support on the stress distribution and buckling load of laminated plates under linearly varying loads. Shariyat and Asemi [12] performed buckling behaviour examination of graded plates under nonuniform compression and their study revealed that the micromechanical approach gives better effective properties than that comes using the rule of mixture.…”

Buckling and vibration analysis of shape memory laminated composite beams under axially heterogeneous in-plane loads in the glass transition temperature region

“…Zhong and Gu [26] analyzed the buckling phenomenon for crossply laminates for variable in plane edge loading through FSDT. Cagdas and Adali [27] optimized the layer thickness for various fiber angle and boundary conditions for the estimation of maximum load resistant to buckling. Based on analytically derived parametric study, Kalyan and Bhaskar [28] performed buckling analysis of orthotropic plate.…”