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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    Title :

    Hybrid hinge and latch beam


    Additional title:

    Hybrider Scharnier- und Verschlussriegel
    Faisceau charnière et verrou hybride


    Contributors:

    Publication date :

    2020-03-11


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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