Free vibration of laminated composite plates with a central circular hole

This paper presents finite element results and some experimental data on the free vibration of symmetric laminated composite plates containing a central hole. The varying parameters in the study are the hole sizes, the boundary conditions along the edges of the plate and the aspect ratio of the plate. Hole diameters ranging from 0.1 to 0.9 times the width of the plate and the aspect ratio varying from 1 to 4 were analysed in the numerical study. The other parameters such as the stacking sequence and the lamination materials are kept constant. The stacking sequence and material properties chosen for the study are those typically found in aircraft structural applications. The close correlation between numerical and experimental data provides some confidence in the finite element method used.