Composite laminates are increasingly being used in more complex structural applications where edges and cut outs are inevitable. These applications include wing skins of military and civil aircraft, further aerospace applications as well as automotive panels and critical structures. Parts of composite structures are particularly vulnerable to impacts, including near the edge of an inspection port or other aperture. Furthermore, impacts to such areas may be to the edge of the laminate rather than the surface. The research described here includes both experimental investigations and finite element simulations of impact damage on the plane of the laminate but near the edge (near-edge), and on the edge (on-edge) of composite laminates. The damage size and mechanisms have been explored. The results demonstrate the vulnerability of composite laminates to on-edge impact.
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