Abstract
In this paper, crack growth analyses on composite panels containing embedded delaminations has been performed using a geometrically non linear FEM code, based on the total Lagrangian formulation. The code has been improved with an effective virtual crack closure technique to evaluate energy release rate and with penalty method to evaluate contact forces. Validation of the proposed tool has been performed with experimental and numerical data available in the literature for double cantilever beam (DCB) specimens. Finally, the influence of the geometrical parameters of the delamination (size and location along the thickness) on the energy release rate distribution and delamination growth stability in composite panels under compression has been analyzed.
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