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A Global/Local Finite Element Approach for Predicting Interlaminar and Intralaminar Damage Evolution in Composite Stiffened Panels Under Compressive Load

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Abstract

This paper addresses the prediction of intralaminar and interlaminar damage onset and evolution in composite structures through the use of a finite element based procedure. This procedure joins methodologies whose credibility has been already assessed in literature such as the Virtual Crack Closure Technique (for delamination) and the ply discount approach (for matrix/fiber failures). In order to establish the reliability of the procedure developed, comparisons with literature experimental results on a stiffened panel with an embedded delamination are illustrated. The methodology proposed, implemented in ANSYS © as post-processing routines, is combined with a finite element model of the panel, built by adopting both shell and solid elements within the frame of an embedded global/local approach to connect differently modelled substructures.

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Acknowledgements

The research leading to these results has received funding from the European Community’s Seventh Framework Programme FP7/2007–2013 under grant agreement n°213371-MAAXIMUS. Part of the work reported in this paper has been presented to the 2nd ECCOMAS Thematic Conference on the Mechanical Response of Composites (London, 2009).

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  1. CIRA Italian Aerospace Research Center, via Maiorise, 81043, Capua, Italy

    Elisa Pietropaoli & Aniello Riccio

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  1. Elisa Pietropaoli
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  2. Aniello Riccio
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Correspondence to Elisa Pietropaoli.

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Pietropaoli, E., Riccio, A. A Global/Local Finite Element Approach for Predicting Interlaminar and Intralaminar Damage Evolution in Composite Stiffened Panels Under Compressive Load. Appl Compos Mater 18, 113–125 (2011). https://doi.org/10.1007/s10443-010-9135-1

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  • DOI: https://doi.org/10.1007/s10443-010-9135-1

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