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CZM-Based FVDAM Analysis of Damage Evolution in Cross-Ply Laminates



Progressive cracking of 90 plies and concomitant delamination of the 0 / 90 ply interface in graphite/epoxy cross-ply laminates are analyzed using the 0th-order parametric FVDAM theory with recently incorporated damage evolution capability based on the cohesive-zone model (CZM). Gradual separation of adjacent phases as well as crack evolution may be simulated with this capability within a unified framework based on discontinuity functions recently introduced into the FVDAM framework. The FVDAM simulations of evolving damage in graphite/epoxy cross-ply laminates are compared with available experimental results on the homogenized axial stress-strain and transverse Poisson's responses, as well as crack density as a function of applied load. The effects of resin-rich region along the 0 / 90 ply interface, residual stress and variable strength of the 90 plies are included in the simulations. The newly developed framework offers a unified methodology in simulating on the fly damage evolution in a class of composite laminates due to cracking or progressive interfacial degradation, and in identifying underpinning damage mechanisms that manifest themselves in the homogenized laminate response.

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