Vibration and stability of composite panels with geometrical discontinuities

Abstract

Laminated composite panels are becoming the preferred material system in a variety of industrial applications, such as aerospace vehicles, automotive structural parts and civil engineering structures for design and strengthening of concrete members. The present study deals with the numerical investigations on free vibration and buckling of composite panels with geometric non linearity such as Delamination and Cutout. A composite panel model based on first order shear deformation theory (FSDT) with provision of cut out and mid plane delamination is considered for the study of vibration and stability, in which stability is carried out only for cutout. The parametric study on composite panels showing the effect of percentage delamination and percentage cutout, aspect ratio, Number of layer, boundary conditions on Natural Frequency and buckling load has been studied. The basic understanding of the influence of the delamination and cutout on the natural frequencies and buckling load of composite panels is presented. In addition, other factors affecting the vibration and buckling region of delaminated composite plates and shells are discussed. The results indicate that the vibration and buckling behaviour is greatly influenced by the geometrical discontinuities.