Effect of multiple delaminations on buckling behavior of laminated composite materials

Composites are being user in many different fields. Layered composites are one of the most used composite kind in industry. There can be discontunities due to various reasons (resistence differences between layers, pulsed loadings, defects in production etc.). These discontinuties effects to layered composites negatively. The geometry of discontinuties (delaminations), their amounts between layers and their positions effects to composite's mechanical properties in many levels but always negatively. So that, in this study; positioning, how numbering between layers and geomety of delaminations effects to layered composites' mechanical properties in buckling behaviour are inspected experimentally. As a result of buckling experiment, loading displacement graphic has obtained. Critic buckling load has calculated by loading displacement graph. Additionaly, transverse displacements are obtained, which occured with the effect of applied load in delamination area in direction of plate thickness. Comparsion of critic buckling loads and such properties like optimum amount and dimension of a delemination have obtained.