STP748

    Crack Growth Behavior of Center-Cracked Panels under Random Spectrum Loading

    Published: Jan 1981


      Format Pages Price  
    PDF Version (156K) 12 $25   ADD TO CART
    Complete Source PDF (2.1M) 12 $55   ADD TO CART


    Abstract

    An assessment is made of the analytical capability to use constantamplitude fatigue crack growth rate data for center-cracked panels to predict the crack growth behavior of center-cracked panels subjected to random flight-by-flight spectrum loading. This paper is one of six such assessments made by members of ASTM Task Group E24.06.01 on Application of Fracture Data to Life Prediction. Crack growth predictions for 13 center-cracked tension specimens were made by the authors without prior knowledge of the test results. Analytical/experimental correlations and a study of the sensitivity of the correlations to two input parameters of the analysis are presented. Also presented is a comparison of the analytical/experimental correlations of the authors to those of the other members of Task Group. It is concluded that it is possible to accurately predict the crack growth behavior of center-cracked panels subjected to random flight-by-flight loading using center-cracked panel constant amplitude fatigue crack growth rate data.

    Keywords:

    fatigue crack growth, fracture mechanics, constant amplitude loading, random loading, round robin, flight by flight loading, 2219-T851 aluminum


    Author Information:

    Rudd, JL
    Aerospace engineer, Air Force Wright Aeronautical Laboratories (AFWAL/FIBEC), Wright-Patterson AFB, Ohio

    Engle, RM
    Aerospace engineer, Air Force Wright Aeronautical Laboratories (AFWAL/FIBEC), Wright-Patterson AFB, Ohio


    Paper ID: STP28336S

    Committee/Subcommittee: E08.06

    DOI: 10.1520/STP28336S


    CrossRef ASTM International is a member of CrossRef.