STP787

    Fatigue Response of Composite Laminates with Internal Flaws

    Published: Jan 1982


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    Abstract

    Quasi-static response and fatigue response under tension-tension loading, R = 0.1, to 106 cycles were evaluated for two laminate types. (±45/0)s and (90/0)s, of T300-5208. All laminates contained a longitudinal notch embedded in the 0-deg plies. Results were compared with previous fatigue studies of the same laminates with a transverse notch embedded in the 0-deg plies. Nondestructive investigation methods used to evaluate damage included acoustic emission, ultrasonic attenuation, C-scan, soft X-radiography, thermography, and stiffness change. Results show that damage initiation and growth depend more on laminate type than on notch orientation. Constraining plies of ±45 deg provided better interfiber splitting resistance and delamination resistance than constraining plies of 90 deg. All nondestructive investigation techniques showed good correlation throughout the testing.

    Keywords:

    composite materials, fatigue, nondestructive tests, radiography, acoustic emission, C-scan, stiffness change


    Author Information:

    Gibbins, MN
    Research Engineer, Boeing Commercial Airplane Company, Seattle, Wash

    Stinchcomb, WW
    Professor, Virginia Polytechnic Institute and State University, Blacksburg, Va.


    Paper ID: STP28487S

    Committee/Subcommittee: D30.04

    DOI: 10.1520/STP28487S


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