A hybrid beam (500) for support of a nacelle panel of a jet engine comprises a first longitudinal composite panel (402) and a second longitudinal composite panel (404), wherein the first longitudinal composite panel (402) is integrally affixed to the second longitudinal composite panel (404) along a longitudinal edge (406). The composite panels form a composite beam structure (400) that is substantially open with a cross-section that is generally "L-shaped". A plurality of hinge stations (540) are affixed to a first side of the first longitudinal composite panel (402) and at least one track guide (520) is disposed on a second side of the first longitudinal composite panel (402). The track guides (520) receive a head portion of a slider (550) that is fixed to the translating jet engine nacelle panel. Each hinge station (540) further comprises a bushing for defining a center of rotation for the jet engine nacelle panel relative to the beam (500).


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    Titel :

    Hybrid hinge and latch beam


    Weitere Titelangaben:

    Hybrider Scharnier- und Verschlussriegel
    Faisceau charnière et verrou hybride


    Beteiligte:
    LAYLAND MICHAEL J (Autor:in) / JAMES NORMAN J (Autor:in) / FORSEY DAVID (Autor:in) / SORIA CHRISTIAN (Autor:in)

    Erscheinungsdatum :

    2020-03-11


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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