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Effect of the Damage Extension Through the Thickness on the Calculation of the Residual Strength of Impacted Composite Laminates

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Damage Growth in Aerospace Composites

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Abstract

One of the most common failure modes for composite structures is the interlaminar delamination. Delamination as a result of impact, high stress concentrations from geometrical discontinuity or a manufacturing defect can cause a significant reduction in the compressive load-carrying capacity of a structure. When a delamination is subjected to in-plane compressive dominated load, local buckling of the delaminated region may occur before global buckling of the laminate.

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Author information

Authors and Affiliations

  1. Composite Structures, Swerea SICOMP, SE-431 22, Mölndal, Sweden

    Sören Nilsson

  2. Saab Aeronautics, Linkoping, Sweden

    Anders Bredberg & Tonny Nyman

Authors
  1. Sören Nilsson
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  2. Anders Bredberg
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  3. Tonny Nyman
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Corresponding author

Correspondence to Sören Nilsson .

Editor information

Editors and Affiliations

  1. Department of Industrial and Information Engineering, Second University of Naples, Aversa, Italy

    Aniello Riccio

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Nilsson, S., Bredberg, A., Nyman, T. (2015). Effect of the Damage Extension Through the Thickness on the Calculation of the Residual Strength of Impacted Composite Laminates. In: Riccio, A. (eds) Damage Growth in Aerospace Composites. Springer Aerospace Technology. Springer, Cham. https://doi.org/10.1007/978-3-319-04004-2_8

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  • DOI: https://doi.org/10.1007/978-3-319-04004-2_8

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  • Publisher Name: Springer, Cham

  • Print ISBN: 978-3-319-04003-5

  • Online ISBN: 978-3-319-04004-2

  • eBook Packages: EngineeringEngineering (R0)

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