The skin of an aircraft can vibrate as a result of pressure waves caused by engine and/or aerodynamic effects. In modern fighter aircraft such as the F/A-18, sound pressure levels have been recorded up to 170 dB over the surface of the skin. In the F/A-18 cracking has occurred in the lower nacelle, typically along the boundaries of the panel. These cracks often originate from a fastener line and grow along the boundary and then turn into the centre of the panel. In the case of the F/A-18, cracking was due to higher than expected pressure levels caused by an aerodynamic disturbance at the inlet lip. Attempts have been made to repair these panels with boron fibre patches, however the cracks have continued to grow. This paper aims at attempting to understand the mechanism's of cracking of the panels subjected to acoustic excitation and the influence of bonded repairs.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Composite bonded repair of cracked panel subject to acoustic fatigue


    Weitere Titelangaben:

    Verbundstoff-Klebeinstandsetzung von gerissenen Plattenfeldern infolge einer akustischen Ermüdung


    Beteiligte:
    Callinan, R.J. (Autor:in) / Galea, S.C. (Autor:in) / Sanderson, S. (Autor:in)


    Erscheinungsdatum :

    1997


    Format / Umfang :

    10 Seiten, 12 Bilder, 6 Quellen



    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    Bonded composite repair of cracked load-bearing holes

    Paul, J. / Bartholomeusz, R.A. / Jones, R. | Tema Archiv | 1994


    Effect of Disbond on Fatigue Behavior of Cracked Aluminum Panel with Bonded Composite Patch

    Denney, J. / Mall, S. / AIAA et al. | British Library Conference Proceedings | 1996



    Adhesively Bonded Composite Patch Repair of Cracked Aluminium Alloy Structures

    Poole, P. / Young, A. / Ball, A. S. et al. | British Library Conference Proceedings | 1995