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Simulation of skin‐stiffener debonding in stiffened carbon/epoxy panels
Author(s) -
Balzani Claudio,
Wagner Werner
Publication year - 2007
Publication title -
pamm
Language(s) - English
Resource type - Journals
ISSN - 1617-7061
DOI - 10.1002/pamm.200700253
Subject(s) - epoxy , fuselage , finite element method , softening , structural engineering , materials science , composite material , reduction (mathematics) , compression (physics) , work (physics) , engineering , mechanical engineering , mathematics , geometry
Aircraft fuselage structures are typically composed of a curved skin connected to longitudinal stiffeners. They are nowadays made of carbon/epoxy laminates. Skin‐stiffener debonding can lead to a significant reduction of their compressive loadcarrying capacity in the postbuckling range of response. This work examines this effect in the framework of the finite element method. A zero‐thickness interface element written in terms of cohesive tractions and relative displacements is derived which is inserted between skin and stiffener. A special cohesive law already presented in [1, 2] describes the softening behavior of the interface while taking into account contact conditions. A numerical example shows the applicability of the model. (© 2008 WILEY‐VCH Verlag GmbH & Co. KGaA, Weinheim)