A semi-analytical, three-dimensional, layer-wise theory is proposed, to solve for various orders of natural frequencies, and mode shapes of thick, arbitrarily laminated, composite cylindrical panels with three-dimensional boundary conditions at the four edges being any combination of free, simply supported, clamped and guided, for each layer.  The displacement field is modeled by finite element interpolation shape functions along the thickness direction and by beam functions in the two in-plane directions. Numerical results from the present work are compared with those from first order transverse shear deformation theory (FSDT) and higher order shear deformation theory (HSDT).  Results indicate that the present method predicts the frequencies more accurately than either FSDT or HSDT.  The present study represents a significant improvement in the capability for modeling complex three dimensional boundary conditions.
 

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