The cohesive element approach is proposed as a tool for simulating delamination propagation between a facesheet and a core in a honeycomb core composite panel. To determine the critical energy release rate (Gc) of the cohesive model, Double Cantilever Beam (DCB) fracture tests were performed. The peak strength (σc) of the cohesive model was determined from Flatwise Tension (FWT) tests. The DCB coupon test was simulated using the measured fracture parameters, and sensitivity studies on the parameters for the cohesive model of the interface element were performed. The cohesive model determined from DCB tests was then applied to a full-scale, 914 × 914 mm (36 × 36 in.) debond panel under edge compression loading, and results were compared with an experiment. It is concluded that the cohesive element approach can predict delamination propagation of a honeycomb panel with reasonable accuracy.
Bibliographical noteFunding Information:
The calculations have been carried out with the finite element program DIANA of TNO Building and Construction Research, the Netherlands. This research was supported by the Boeing Commercial Airplane Company, by the Multidisciplinary Center for Earthquake Engineering Research, and by Cornell University. The authors gratefully acknowledge the contributions of Dr. Peter H. Feenstra, Prof. Chung-Yuen Hui, and Dr. Paul A. Wawrzynek at Cornell University.
All Science Journal Classification (ASJC) codes
- Computational Mechanics
- Modelling and Simulation
- Mechanics of Materials