STP338

    Aircraft Structural Fatigue Research in the Navy

    Published: Jan 1963


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    Abstract

    Twenty-six unused fighter aircraft were made available for use in an investigation to determine the fatigue characteristics of a typical fighter airplane. The primary purpose of this investigation was to obtain fatigue data on full-scale structures for use in designing new aircraft. The aircraft were disassembled into major components: wing, horizontal tail, vertical tail, nose landing gear, and main landing gear. Constant-amplitude and variable-amplitude tests were performed on the various components to determine: (1) the degree of scatter, (2) the effect of cumulative damage and the validity of various cumulative damage hypotheses for full-scale structures, (3) the effect of randomization of the load sequence within a spectrum block, (4) the effect of superimposing landing loads on a flight load spectrum, (5) the effect of prestressing, and (6) the effect of varying the mean and alternating loads. A discussion of the test results and their significance for future design use is included.


    Author Information:

    Rosenfeld, M. S.
    Superintendent, Naval Air Engineering Center, Philadelphia, PA


    Paper ID: STP44469S

    Committee/Subcommittee: E08.01

    DOI: 10.1520/STP44469S


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