Experiment and analysis on the response of curved laminated composite panels subjected to low velocity impact

Transverse central impact on thin fiber-reinforced composite cylindrical panels is studied with emphasis on the importance of in-plane membrane effects. Both small and large deformation impact responses are examined in this context. A nonlinear system of equations is derived for the impact problem, including Hertz' contact law, and solved over time using Runge-Kutta integration. Drop weight impact tests were performed to validate the analyses. Impact force and displacement histories are compared with the test data and the work of other researchers for small and large deformation of hat and curved panels. Understanding the scatter of test data and limits on the assumptions enables both quantitative and qualitative examination of the parameters which govern the impact response. (C) 1998 Elsevier Science Ltd. All rights reserved.