Volume 5, Issue 5 (September 1977)

    Fatigue Damage: Stiffness/Strength Comparisons for Composite Materials

    CODEN: JTEOAD

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    Abstract

    Boron/epoxy laminates in a [0-deg/ + 45-deg/ - 45-deg/ 0-deg/0-deg/ + 45 -deg/ - 45-deg/0-deg] layup were tested statically for initial strength and fracture strain and were tested in strain-controlled fatigue loading at 30 Hz, with a strain-amplitude ratio of one tenth for five different testing sequences.

    A reduced stiffness analysis was used in conjunction with laminated plate theory to predict stiffness changes based on observed debonding and fiber breakage. Specimens used for strength analysis either fractured during fatigue or were loaded statically to failure after fatigue. All specimens were leached with a heated acid, and fiber breakage was recorded. Correlations are noted between matrix damage and stiffness changes as well as between fiber breakage and strength reduction.


    Author Information:

    O'Brien, TK
    Instructor and professormember of ASTM, Virginia Polytechnic Institute and State University, Blacksburg, Va.

    Reifsnider, KL
    Instructor and professormember of ASTM, Virginia Polytechnic Institute and State University, Blacksburg, Va.


    Stock #: JTE10547J

    ISSN: 0090-3973

    DOI: 10.1520/JTE10547J

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    Author
    Title Fatigue Damage: Stiffness/Strength Comparisons for Composite Materials
    Symposium , 0000-00-00
    Committee D30