Experimental Evaluation of Initial Flaw Criticality and Analysis Methods for Damage Tolerant Air Force Aircraft

    Published: Jan 1982

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    This paper considers two aspects of the United States Air Force analytical and experimental damage tolerance design requirements for metallic airframes: the locations of initial damage and the accuracy of crack growth analysis. Following a summary of the requirements, an assessment is made of the validity of the initial continuing damage locations specified in the requirements. Guidelines are provided for selecting the initial primary damage location needed but not specified in the requirements. Analyses and test results are presented for typical aircraft structure (that is, chordwise splices, spanwise splices, stringer-reinforced continuous skin, 2-bay wing panels, etc.). The analytical and experimental results are correlated in order to assess the accuracy of the state-of-the-art analytical capability to satisfy the Air Force damage tolerance requirements.


    damage tolerance, fracture mechanics, fatigue crack growth, residual strength, design criteria, initial damage, aircraft structure, fastener holes, mechanical joints

    Author Information:

    Rudd, JL
    Aerospace Engineer, Air Force Wright Aeronautical Laboratories, Wright-Patterson Air Force Base, Ohio

    Brussat, TR
    Senior Research Specialist, Lockheed-California Company, Burbank, Calif.

    Chiu, ST
    Senior Research Specialist, Lockheed-California Company, Burbank, Calif.

    Creager, M
    President, Del West Engineering, Chatsworth, Calif.

    Committee/Subcommittee: E08.08

    DOI: 10.1520/STP28858S

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