One of the main causes of failure of composite laminated structures is delamination damage, which is significantly derived from interlaminar stresses [1]. Analytical solution of a first-order shear deformation theory is developed to study interlaminar stresses of antisymmetric angle-ply laminated rectangular plates subjected to forced vibration. In the theoretical formulations the effects of all the rotational inertia terms are considered. Also the change in the plate thickness is taken into account due to its important role in the edge effects. The governing equations of laminated plates are established by applying Hamilton\\\'s principle and are solved by using Levy\\\'s solution method. It is assumed that the plates have two simply supported opposite edges and the remaining boundary conditions are arbitrary. The functions of displacement components are obtained using the results of free vibration, which are obtained by solving the homogeneous form of equations of motion analytically using the state-space approach. Also the function of time is obtained using orthogonality relation, the Laplace transform and convolution integral. First the natural frequencies and mode shapes for the case of free vibration and the time responses for the case of transient vibration are obtained and then dynamic interlaminar stresses are determined by integrating the three-dimensional local equations of motion and imposing given boundary conditions at the top or bottom surface of the laminate. The accuracy and effectiveness of the first-order theory in describing the localized three-dimensional effects are demonstrated by comparing the results of the present theory with those obtained from finite element method. Numerical results show that boundary conditions, configurations, E1/E2 ratio, side-to-thickness ratio and aspect ratio have significant effect on dynamic interlaminar stresses.

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