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Simulation of High Velocity Impact on Composite Structures - Model Implementation and Validation

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Abstract

High velocity impact on composite aircraft structures leads to the formation of flexural waves that can cause severe damage to the structure. Damage and failure can occur within the plies and/or in the resin rich interface layers between adjacent plies. In the present paper a modelling methodology is documented that captures intra- and inter-laminar damage and their interrelations by use of shell element layers representing sub-laminates that are connected with cohesive interface layers to simulate delamination. This approach allows the simulation of large structures while still capturing the governing damage mechanisms and their interactions. The paper describes numerical algorithms for the implementation of a Ladevèze continuum damage model for the ply and methods to derive input parameters for the cohesive zone model. By comparison with experimental results from gas gun impact tests the potential and limitations of the modelling approach are discussed.

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Acknowledgments

Part of 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.

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Authors and Affiliations

  1. German Aerospace Center (DLR), Institute of Structures and Design, Pfaffenwaldring 38-40, 70569, Stuttgart, Germany

    Dominik Schueler, Nathalie Toso-Pentecôte & Heinz Voggenreiter

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  1. Dominik Schueler
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  2. Nathalie Toso-Pentecôte
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  3. Heinz Voggenreiter
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Correspondence to Dominik Schueler.

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Schueler, D., Toso-Pentecôte, N. & Voggenreiter, H. Simulation of High Velocity Impact on Composite Structures - Model Implementation and Validation. Appl Compos Mater 23, 857–878 (2016). https://doi.org/10.1007/s10443-016-9489-0

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  • DOI: https://doi.org/10.1007/s10443-016-9489-0

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