You are being redirected because this document is part of your ASTM Compass® subscription.
    This document is part of your ASTM Compass® subscription.


    Prediction Methods for Fatigue Crack Growth in Aircraft Material

    Published: 0

      Format Pages Price  
    PDF (476K) 32 $25   ADD TO CART
    Complete Source PDF (8.8M) 586 $60   ADD TO CART

    Cite this document

    X Add email address send
      .RIS For RefWorks, EndNote, ProCite, Reference Manager, Zoteo, and many others.   .DOCX For Microsoft Word


    In the first part of the paper a survey is given of relevant knowledge on fatigue crack growth and qualitative and quantitative understanding of predictions. Aspects of cycle-by-cycle predictions and characteristic K prediction methods are discussed. In the second part recent work on prediction problems is reported. This includes (a) crack growth under flight-simulation loading with crack closure measurements, (b) predictions for flight-simulation loading based on a constant crack opening stress level, and (c) crack growth under pure random loading with different Srms-values, two irregularities and two crest factors.

    The random load tests were also carried out to explore the usefulness of Krms. The paper is concluded with some indications for future research and a number of conclusions.


    crack propagation, fatigue (materials), predictions, flight-simulation loading, random loading, crack closure, fractures (materials)

    Author Information:

    Schijve, J
    Professor, Delft University of Technology, Delft,

    Committee/Subcommittee: E08.08

    DOI: 10.1520/STP36962S