Current Air Force design philosophy has imposed crack growth requirements on all new USAF flight vehicles. These requirements must be incorporated very early in the design phase to achieve the impact intended on safety and durability. This requires a capability to obtain realistic life estimates for materials evaluations based upon preliminary input information. An approach is presented which generates an average growth rate per flight, da/dF; then numerically integrates the inverse of this function from an initial crack size to the critical crack size which is calculated fro input variables. Load interaction effects are accounted for using the Wheeler retardation model on a flight-by-flight basis. The flight-by-flight crack growth is obtained using an equivalent damage concept for computational efficiency. Predictions are compared with test data from coupons subjected to the actual stress histories for four design stress levels. Agreement is very good, demonstrating that this approach is capable of realistic predictions with a minimum of complexity.


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    Titel :

    A simplified approach for assessing spectrum loading effects in preliminary design


    Weitere Titelangaben:

    Eine vereinfachte Methode zur Ermittlung der Einfluesse des Belastungsspektrums beim Vorentwurf


    Beteiligte:


    Erscheinungsdatum :

    1983


    Format / Umfang :

    5 Seiten, 3 Bilder, 1 Tabelle, 7 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch