A large portion of the fatigue crack growth threshold data in this report is inappropriate due to the load reduction test procedure that was used to generate these data. The author, in collaboration with National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) personnel, is developing new test procedures to generate threshold data under steady-state constant-amplitude loading conditions without any load history effects. The new test method involves using compression precracking to generate a crack at a V-notch and then to test the specimen under constant-amplitude loading. A large test program on the development of these fatigue crack growth databases, for use in damage-tolerant analyses for aircraft propellers and rotorcraft components, was conducted at NASA LaRC under a Memorandum of Agreement with the Federal Aviation Administration (FAA). Some materials tested and analyzed herein were 7050-T7451 and 7075-T7351 aluminum alloys and D6AC and 4340 steels. Only the steels were tested as part of the FAA program. The 7075 alloy was tested at the NASA Johnson Space Center, and the 7050 and 7075 alloys were tested at NASA LaRC. This test program was conducted to generate more accurate representations of fatigue crack growth rate behavior in the near-threshold regime and approaching fracture under a wide range of constant stress ratio. The objective of the proposed research grant was to analyze the test data on selected propeller and rotorcraft materials to develop the effective stress-intensity factor range against crack growth rate relationship for use in damage tolerance analyses.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Analysis of Fatigue Crack Growth Databses for Use in a Damage Tolerance Approach for Aircraft Propellers and Rotorcraft


    Beteiligte:
    J. C. Newman (Autor:in)

    Erscheinungsdatum :

    2007


    Format / Umfang :

    93 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Fatigue crack growth history in damage tolerance design of aircraft structures

    Siegl, Jan / Nedbal, Ivan / Kunz, Jiri | Tema Archiv | 2009



    A Damage Tolerance and Fatigue Evaluation Approach for Composite Rotorcraft Airframe Structures

    Engleder, A. / Francescatti, D. / Burger, U. et al. | British Library Conference Proceedings | 2014



    UNMANNED ROTORCRAFT WITH CROSS-SECTION PROPELLERS

    DUROV DMITRIJ SERGEEVICH | Europäisches Patentamt | 2017

    Freier Zugriff