STP982

    A Simple Crack Closure Model for Predicting Fatigue Crack Growth Under Flight Simulation Loading

    Published: Jan 1988


      Format Pages Price  
    PDF (204K) 14 $25   ADD TO CART
    Complete Source PDF (11M) 14 $115   ADD TO CART


    Abstract

    This paper presents a new approach for calculating the crack growth under spectrum loading in various different industrial applications. The paper includes (1) An original model based on the crack closure concept. The model combines a cycle by cycle analysis with a conservative cycle counting method similar to the “rain flow” one. A rule that fixes the crack tip opening point at every cycle to take into account the R ratio effect and the retardation effects is developed. (2) A method used for the determination of parameters. The model requires only three parameters that can be obtained with two simple crack growth tests. These two tests give both the values of parameters and the K range where the model is valid. The three parameters depend on the material and the specimen thickness. (3) Some industrial applications—the results show a good correlation between tests and calculations for several different materials. Furthermore, calculation with standard fatigue spectra (TWIST, MINITWIST, FALSTAFF) are given for a range of parameters.

    Keywords:

    damage tolerance, fatigue crack growth model, stress spectra, fatigue tests


    Author Information:

    Aliaga, D
    Head of fatigue group, Central Laboratory Aerospatiale, Suresnes Cedex,

    Davy, A
    Fracture mechanics engineer and materials engineer, Aerospatiale, Toulouse Cedex 03,

    Schaff, H
    Fracture mechanics engineer and materials engineer, Aerospatiale, Toulouse Cedex 03,


    Paper ID: STP27227S

    Committee/Subcommittee: E08.06

    DOI: 10.1520/STP27227S


    CrossRef ASTM International is a member of CrossRef.