Investigation of Impact Resistance of Laminated Composites

In this study, a sandwich panel that can be used as an internal structural material in aircraft and other transportation vehicles has been produced. The core of this sandwich panel was obtained by baking neat EVA sheets without reinforcement and with three rows of steel wire reinforcement at 180 ˚C for 30 minutes. On the upper and lower surfaces of these cores, 0.5 mm thick 5457 aluminum sheets were adhered with polyurethane adhesive and thus composite panels were obtained. The sandwich panels were subjected to impact tests at various levels (20J, 30J, 40J and 50J). After the tests, force-time and force-displacement graphs of the specimens corresponding to different energy values were obtained. It was observed that as the wire reinforcement increases, the elasticity of the material decreases and the strength of the material increases, and accordingly, the maximum displacement generally decreases.