Simplified Model for Large Mass Impact and Delamination Onset in Curved Laminates

Impact resistance and damage tolerance remain major concerns in the design of laminated composite structures. Impact on flat panels has been the subject of extensive experimental and theoretical studies [1]. The work on curved panels is more limited although most laminates in aircraft wings and fuselages, as well as in other vehicles, are more or less curved. The existence of a delamination threshold load for flat panels has been demonstrated theoretically and experimentally [2], and experiments indicate that this may also apply for curved panels [3]. Thus, methods are needed to predict the peak load during impact on curved panels.