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2015 | OriginalPaper | Chapter

6. Microdamage Modeling in Laminates

Author : Janis Varna

Published in: Damage Growth in Aerospace Composites

Publisher: Springer International Publishing

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Abstract

During service life structures made of laminated composites are subjected to complex combinations of thermo-mechanical and environmental loads. The final macroscopic failure of composite laminate is preceded by initiation and evolution of several microdamage modes in layers. This is because the transverse tensile strain to failure of unidirectional composites is lower than other failure strain components. Therefore transverse cracking of layers with off-axis orientation with respect to the main load direction, caused by combined action of transverse tensile stress and shear stress, is usually the first mode of damage (Parvizi and Bailey, J. Mater. Sci. 13:2131–2136, 1978 [1]; Jamison et al., ASTM STP 836:21–55, 1984 [2]).

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previous chapter Influence of Intralaminar Damage on the Delamination Crack Evolution
next chapter Finite Element Study of Delaminations in Notched Composites
Appendix
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Metadata
Title
Microdamage Modeling in Laminates
Author
Janis Varna
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_6

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