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Compressive Fatigue Damage in T800/924C Carbon Fibre-Epoxy Laminates with an Open Hole

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Developments in the Science and Technology of Composite Materials

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Summary

The compression fatigue behaviour of T800/924C [± 45/O2)3]s carbon fibre-epoxy laminates containing a single hole has been studied. The fatigue damage consists of fibre microbuckling, ply cracking and delamination. Fatigue lives exceed 106 cycles when the maximum compressive load in the fatigue cycle is less than 85% of the static strength. After fatigue cycling at lower peak loads the residual strength of the specimen increases: splitting and associated delamination reduce the stress concentration at the hole edge. At peak fatigue loads equal to 90% of the static strength fatigue failure occurs as a result of microbuckle initiation and growth.

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References

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Author information

Authors and Affiliations

  1. Engineering Department, Cambridge University, Trumpington St., CB2 1PZ, Cambridge, Great Britain

    C. Soutis & N. A. Fleck

Authors
  1. C. Soutis
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  2. N. A. Fleck
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Editor information

Editors and Affiliations

  1. DLR, Germany

    J. Füller , G. Grüninger  & K. Schulte ,  & 

  2. EACM, USA

    A. R. Bunsell  & A. Massiah  & 

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© 1990 Elsevier Science Publishers Ltd

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Soutis, C., Fleck, N.A. (1990). Compressive Fatigue Damage in T800/924C Carbon Fibre-Epoxy Laminates with an Open Hole. In: Füller, J., Grüninger, G., Schulte, K., Bunsell, A.R., Massiah, A. (eds) Developments in the Science and Technology of Composite Materials. Springer, Dordrecht. https://doi.org/10.1007/978-94-009-0787-4_27

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  • DOI: https://doi.org/10.1007/978-94-009-0787-4_27

  • Publisher Name: Springer, Dordrecht

  • Print ISBN: 978-94-010-6841-3

  • Online ISBN: 978-94-009-0787-4

  • eBook Packages: Springer Book Archive

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