Commercial aircraft advanced composite wing surface panels were tested for durability and damage tolerance. The wing of a fuel-efficient, 200-passenger airplane for 1990 delivery was sized using grahite-epoxy materials. The damage tolerance program was structured to allow a systematic progression from material evaluations to the optimized large panel verification tests. The program included coupon testing to evaluate toughened material systems, static and fatigue tests of compression coupons with varying amounts of impact damage, element tests of three-stiffener panels to evaluate upper wing panel design concepts, and the wing structure damage environment was studied. A series of technology demonstration tests of large compression panels is performed. A repair investigation is included in the final large panel test.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Damage Tolerant Composite Wing Panels for Transport Aircraft


    Beteiligte:
    P. J. Smith (Autor:in) / R. D. Wilson (Autor:in) / M. N. Gibbins (Autor:in)

    Erscheinungsdatum :

    1985


    Format / Umfang :

    59 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Damage tolerant composite wing panels for transport aircraft

    Smith, Peter J. / Wilson, Robert D. / Gibbins, M. N. | NTRS | 1985




    AIRCRAFT WING COMPOSED OF COMPOSITE AND METAL PANELS

    JOHNSON MILES O / MUNSEN VICTOR A / MCGINTY DANIEL E et al. | Europäisches Patentamt | 2020

    Freier Zugriff

    Damage tolerance and fail safety of welded aircraft wing panels

    Zhang, Xiang / Li, Yazhi | Tema Archiv | 2005