A rotorcraft tail rotor comprising at least two blade elements, each blade element being suitable for pivoting about a collective pitch variation axis Z in order to vary the collective pitch of each blade element of the tail rotor, each blade element including at least one compensation weight comprising a projection emerging substantially perpendicularly to a main inertia axis of the blade element, the main inertia axis being parallel to a longitudinal direction of the blade element. In the invention, the tail rotor is wherein the compensation weight includes a deformable portion that is movable relative to the projection in a plane P that is parallel to the main inertia axis of the blade element.


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    Titel :

    Rotorcraft tail rotor, a rotorcraft fitted with such a tail rotor, and a method of statically and/or dynamically balancing a rotorcraft tail rotor


    Beteiligte:
    CERTAIN BERNARD (Autor:in) / JOUVE JEREMY (Autor:in)

    Erscheinungsdatum :

    19.11.2019


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F16F SPRINGS , Federn






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