STP1189

    An Evaluation of Fracture Mechanics Properties of Various Aerospace Materials

    Published: Jan 1993


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    Abstract

    This paper presents results from a series of fracture mechanics tests that used a variety of aerospace materials, including 6063 aluminum in the T5 and T6 tempers, 2014-T651 aluminum welded with a 4043 filler material, Inconel 718, A286 steel, superalloy MP35N, beryllium SR-200E, magnesium AZ-31B-H24 and ZK-60A-T5, beryllium-copper CDA172, and aluminum-bronze CDA630. The fatigue crack growth data for these materials were curve fit using the crack propagation and other related equations that will be incorporated into an updated version of the NASA/FLAGRO computer program. This program will help achieve more reliable fracture mechanics assessments of space systems hardware.

    Keywords:

    crack propagation, fatigue (materials), fracture mechanics, toughness, aerospace materials, fatigue crack growth


    Author Information:

    Henkener, JA
    Senior associate engineers, Lockheed Engineering & Sciences Co., Houston, TX

    Lawrence, VB
    Senior associate engineers, Lockheed Engineering & Sciences Co., Houston, TX

    Forman, RG
    Senior materials engineer, NASA Lyndon B. Johnson Space Center, Houston, TX


    Paper ID: STP24284S

    Committee/Subcommittee: E08.08

    DOI: 10.1520/STP24284S


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