Analyzing Elliptical Delamination in Quasi-Isotropic Composite Laminates: A New Solution Approach

Composite material (CM) has been used for manufacturing from small structures to complex structures such as aircraft, ships, and space vehicles to increase the structure's corrosion resistance and decrease the structure's weight compared to pure materials. During the production process or during the assembly of the structures, delamination may occur between two layers in different shapes such as circular, spherical or elliptical. This delamination is a common cause of failure in composite laminates of sandwich structures, which can become unstable under different loading conditions. Understanding this instability is essential in designing composite and sandwich structures. In this study, firstly, a literature review has been done to describe the effect of delamination in a composite structure. Secondly, the reasons and solutions have been depicted in the different studies. Finally, as stress and strain are critical factors in determining structural strength, strain, and potential energy have been calculated from previous studies' equations using a novel algorithm (MATLAB) to analyze the effect of elliptical delamination in a quasi-isotropic composite material. The results also have been compared with the previously calculated results done by the finite element (FE) and Rayleigh-Ritz (R-R) method.