The present invention relates generally to a composite seal for use in bearings and more particularly to a composite annular seal assembly having a resilient ring disposed between (e.g., sandwiched between) two annular retaining rings, for use in hourglass type bearings for use in aircraft and more particularly in a drop linkage assembly of a trailing edge flap arrangement of such aircraft. An edge flap arrangement (2) for an aircraft wing comprises a main flap element (3) and an actuator (7) for moving the main flap element (3) relative to the aircraft wing; a linkage arrangement supporting the main flap element (3) from the aircraft wing (1) for movement relative to the aircraft wing (1), the linkage arrangement including a drop hinge link arrangement (5) , the drop hinge link arrangement including a fixed strut (5a) secured to the aircraft wing (1) and a drop link (5c) secured to the main flap element (3), the fixed strut (5a) and the drop link (5c) being pivotally connected by a hinge point (5b); the hinge point (5b) comprising at least a first bearing (20) comprising: an outer race (50) having a first inner surface (54) and an interior area; an inner race (30) having an outer surface (36), a portion of the inner race (30) being disposed in the interior area; an annular seal assembly (70, 80) snap-fit into the outer race (50), the annular seal assembly (70, 80) comprising: a first annular retaining ring (72) defining a first radially outermost portion (72X); a second annular retaining ring (74) defining a second radially outermost portion (74X); and a resilient ring (76) defining a third radially outermost portion (76X), the resilient ring (76) being disposed between the first annular retaining ring (72) and the second annular retaining ring (74); the first radially outermost portion (72X), the second radially outermost portion (74X) and the third radially outermost portion (76X) being aligned with one another; the resilient ring (76) projecting radially inward from the first annular retaining ring (72) and the second annular retaining ring (74); and the resilient ring (76) being more compressible and flexible than the first annular retaining ring (72) and the second annular retaining ring (74).


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    An edge flap arrangement for an aircraft wing


    Weitere Titelangaben:

    Klappenanordnung für einen Flügel eines Flugzeugs
    Système de volet pour une aile d'aéronef


    Beteiligte:
    HABIBVAND ALEX (Autor:in)

    Erscheinungsdatum :

    08.05.2019


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F16C SHAFTS , Wellen




    Aircraft wing flap support

    TSAI KEVIN / JOHNSON KYLE | Europäisches Patentamt | 2022

    Freier Zugriff

    Sub-wing mounted trailing edge double fold flap for aircraft wing

    CAZIN RONALD JOHN / TSAI KEVIN R | Europäisches Patentamt | 2024

    Freier Zugriff

    WING, FLAP, AND AIRCRAFT

    MURAYAMA MITSUHIRO / YAMAMOTO KAZUOMI | Europäisches Patentamt | 2018

    Freier Zugriff

    WING, FLAP, AND AIRCRAFT

    MURAYAMA MITSUHIRO / YAMAMOTO KAZUOMI | Europäisches Patentamt | 2016

    Freier Zugriff