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In this numerical and analytical study; the length-to-thickness ratio (a/t), aspect ratio (a/b), Young modulus ratio ( E 1 / E 2 ), load ratio ( N x / N y ) and different boundary conditions effect on buckling behaviour of carbon/epoxy composite laminated plate were investigated. The composite plate was assumed four plies as [θ°] 4 . The fibre orientation, θ, was chosen as 0°, 15°, 30°, 45°, 60°, 75° and 90°. The Veres-Kollar approach [ 1 ] was used to calculate the buckling load, analytically. Also, ANSYS 10 commercial software was used for determination of buckling load, numerically. The plate has simple supported boundary condition at four edges during analytical and numerical study. Good agreements between analytical and numerical results were obtained. Results showed that the buckling load changes depend on the dimension and material properties of the plate, boundary conditions and loading cases.

Buckling Behaviour of Carbon/Epoxy Laminated Composite Plates under Biaxial Loading