Free vibration analysis of fiber metal laminated plates

Abstract

The free vibration analysis of a new aircraft material fiber metal laminated (FML) plates is investigated in the present study. A finite element based formulation is developed using firstorder Reissner/Mindlin plate theory. A four-node isoparametric quadratic element is employed in the present study with five degrees of freedom per node. The modal testing of FML plates is performed with the help of Bruel and Kjaer FFT analyzer and PULSE software. The present study deals with the effects of various parameters including aspect ratio and boundary conditions on the dynamic characteristics of the fiber metal laminates. The analysis is carried out both experimentally and numerically. There is a good agreement between numerical and experimental results. From both the results, it is concluded that with the increase of aspect ratio of FML plate the natural frequency is also increased. The boundary conditions are also considerably affecting the natural frequencies of FML plates because of restraining at edges.