Experimental Approach on the Behavior of Composite Laminated Shell under Transverse Impact Loading

Abstract

Composites are to be considered for many structural applications structural weight. These materials have high strength‐to‐weight and stiffness‐to‐weight ratios. However, they are susceptible to impact loading because they are laminar systems with weak interfaces. Matrix cracking and delamination are the most common damage mechanisms of low velocity impact and are dependent on each other. This paper is to study the behavior of composite shell under transverse impact loading. In this study, carbon‐epoxy composite laminates with various curvatures was used. Low velocity impact tests were performed using a drop weight testing machine. The 100mm×100mm shells were clamped in order to produce a central circular area (φ=80mm). An hemispherical impactor (m=0.1kg and φ=10mm) was used and the tests were done with velocities ranging from 2.8 to 4.8 m/s. The real curve force/time was registered in order to obtain the maximum contact force and contact time. And then, we know that contact force and delamination area of flat‐plate is higher than cylindrical shell panel in the same kinetic energy level, and flat‐plate is easily penetrated than cylindrical shell panel. And contact force, deflection and delamination area decrease as the curvature increase.