Abstract
Critical buckling and natural frequencies behavior of laminated composite thin plates subjected to in-plane uniform load is obtained using classical laminated plate theory (CLPT). Analytical investigation is presented using Ritz- method for eigenvalue problems of buckling load solutions for laminated symmetric and anti-symmetric, angle and cross ply composite plate with different elastic supports along its edges. Equation of motion of the plate was derived using principle of virtual work and solved using modified Fourier displacement function that satisfies general edge conditions. Various numerical investigation were studied to exhibit a convergence and accuracy of the present solution for considering some design parameters such as edge conditions, aspect ratio, lamination angle, thickness ratio, orthotropic ratio, the results obtained gives good agreement with those published by other researchers.
Highlights
The composite materials (C.M) reinforced by fiber are perfect for structural applications where high stiffness and strength to weight of ratios are necessary
Presented a study of bending and free vibration analysis based on simple first order shear deformation theory (FSDT)
Results and Discussion cross and angle ply with different aspect and modulus ratio and give a good agreement when compared with results obtained by J
Summary
The composite materials (C.M) reinforced by fiber are perfect for structural applications where high stiffness and strength to weight of ratios are necessary. Developed an exact solution on the base of the first order shear deformation theory (FSDT) to investigate the buckling behavior of symmetrical supported cross ply rectangular plates subjected to unidirectional linearly varying in-plane loads. Presented a study of buckling and post buckling behavior of supported composite plates subjected to non-uniform in-plane loading. The analytical solutions for laminated plate based on higher order shear deformation theory. Presented a study of bending and free vibration analysis based on simple first order shear deformation theory (FSDT). Presented an exponential shear deformation theory which extended for buckling and free vibration analysis. Studied buckling behavior and free vibration of composite plates subjected to in plane parabolic, linear and uniform distributed loads using (CLPT). Analytical investigation is shows using Ritz method for eigenvalues problems of buckling loads solution for laminated plate. The functions used in the Ritz technique are chosen by way of either a hybrid polynomial-trigonometric series or a pure polynomial series
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