A GLARE fuselage panel, representative of the crown section of the Fokker 100 fuselage in front of the wing, was tested. The panels were loaded by air pressure resulting in tangential stress in the panel by axial loading, representative of both the cabin pressure and the fuselage bending due to taxiing and gust loading. A fatigue test, simulating 180000 flights, followed by static tests were performed. The panel was loaded to failure at 1.32 ultimate load. The test set-up, the uniform strain distribution of the panel, and the fatigue loads applied at high test frequency are described. The use of GLARE leads to a substantial weight reduction without affecting the fatigue static strength.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Full scale GLARE fuselage panel tests


    Beteiligte:

    Kongress:

    FAA-NASA Symposium on Continued Airworthiness of Aircraft Structures ; 1996


    Erscheinungsdatum :

    27.08.1996


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Full Scale GLARE Fuselage Panel Tests

    R. W. A. Vercammen / H. H. Ottens | NTIS | 1996


    Full Scale GLARE Fuselage Panel Tests

    Vercammen, R. W. A. / Ottens, H. H. / International Committee on Aeronautical Fatigue | British Library Conference Proceedings | 1997


    Full-Scale Glare Fuselage Panel Tests

    R. W. A. Vercammen / H. H. Ottens | NTIS | 1997


    Full-scale glare fuselage panel tests

    Vercammen, R. W. A. / Ottens, H. H. | TIBKAT | 1997


    Full-scale fuselage panel tests

    Vercammen, R. W. A. / Ottens, H. H. | TIBKAT | 1998