STP1012

    Fatigue Life Prediction of Cross-Ply Composite Laminates

    Published: Jan 1989


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    Abstract

    Fatigue damage development in cross-ply laminates consists of transverse matrix cracking followed by longitudinal matrix cracking, local delaminations at crack intersections, and ultimately longitudinal fiber breakage of the load-carrying plies. Ultimate failure is determined by the manner in which the load is redistributed and transferred into the load-carrying plies. A model was developed for predicting fatigue life of cross-ply laminates which develop transverse cracking up to the characteristic damage state (CDS) level before fatigue failure. The fatigue life consists of two portions: the portion necessary to reach the CDS and the residual life after attainment of the CDS. A procedure for estimating the CDS life is described based on the relationship between residual stiffness and crack density and the stress-life (S-N) curve of the 90° lamina. The residual life after CDS was obtained by calculating the stress carried by the 0° plies and assuming that these plies within the damaged laminate behave like a 0° lamina under cyclic loading. Fatigue life predictions were in good agreement with experimental results for three graphite/epoxy cross-ply laminates.

    Keywords:

    graphite/expoxy, cross-ply laminates, matrix cracking, fatigue, stiffness degradation, fatigue life, damage accumulation


    Author Information:

    Lee, J-W
    Research assistant, professor, and visiting assistant professor, Northwestern University, Evanston, IL

    Daniel, IM
    Research assistant, professor, and visiting assistant professor, Northwestern University, Evanston, IL

    Yaniv, G
    Research assistant, professor, and visiting assistant professor, Northwestern University, Evanston, IL


    Paper ID: STP10406S

    Committee/Subcommittee: D30.02

    DOI: 10.1520/STP10406S


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