Dynamic delamination modeling using cohesive finite elements
Résumé
In this paper we present a methodology for the prediction of impact induced damage in aeronautical composite structures. Material under consideration is a carbon fiber and epoxy resin (T800S/M21) unidirectional laminate. Continuum damage mechanics is applied for plies and cohesive finite elements are used for delamination prediction. The numerical simulation results from finite element codes are compared with experimental results.
Origine | Fichiers produits par l'(les) auteur(s) |
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