An aircraft rotor assembly has upper and lower hub plates adapted to be mounted to a central rotor mast for rotation therewith. A plurality of radial arms is connected to at least two flap bearings mounted between the hub plates and forming a discrete flap hinge, each flap hinge defining a flap axis and allowing rotation of the associated arm relative to the hub plates and about the corresponding flap axis. Each of a plurality of blade grips is rotatably connected to one of the arms for rotation about a pitch axis and adapted for mounting of a blade to each blade grip, such that each blade is capable of rotation with the grip about the pitch axis and capable of rotation together with the corresponding arm relative to the hub plates and about the corresponding flap axis.


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    Titel :

    Aircraft rotor with discrete flap hinge


    Beteiligte:
    STAMPS FRANK B (Autor:in) / POPELKA DAVID A (Autor:in) / DONOVAN TOM (Autor:in) / TISDALE PATRICK R (Autor:in) / RAUBER RICHARD E (Autor:in)

    Erscheinungsdatum :

    31.05.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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