Abstract
A validated experimental approach to obtaining critical mode I and mode II energy release rates for interfacial failure in a sandwich composite panel is outlined in this paper. By modifying the geometry of the sandwich structure to align the face sheet-core interface to coincide with the neutral axis, it is possible to obtain critical mode I and mode II energy release rates by conducting Double Cantilever Beam (DCB) and End Notch Flexure (ENF) tests, respectively. The values so obtained were used to predict the crack growth histories of modified DCB and ENF tests, and a Single Leg Bend (SLB) test, using a discrete cohesive zone method (DCZM). In addition, the influence of material and geometry were also analyzed.
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