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2015 | OriginalPaper | Chapter

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

Authors : Sören Nilsson, Anders Bredberg, Tonny Nyman

Published in: Damage Growth in Aerospace Composites

Publisher: Springer International Publishing

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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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previous chapter Finite Element Study of Delaminations in Notched Composites
next chapter A Fast Numerical Methodology for Delamination Growth Initiation Simulation
Literature
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Prasad, C.B., Ambur, D.R., Starnes J.H.: Response of laminated composites plates to low-speed impact by airgun-propelled and dropped-weight impactors. AIAA paper 93-1402-CP, pp. 887–900, (1993)
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Metadata
Title
Effect of the Damage Extension Through the Thickness on the Calculation of the Residual Strength of Impacted Composite Laminates
Authors
Sören Nilsson
Anders Bredberg
Tonny Nyman
Copyright Year
2015
Book
Damage Growth in Aerospace Composites

Print ISBN: 978-3-319-04003-5

Electronic ISBN: 978-3-319-04004-2

Copyright Year: 2015

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

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