A rotor for an aircraft is described that has a mast, an attenuating device to attenuate the transmission of vibrations from the mast in a plane orthogonal to the first axis, and a transmission device interposed between the mast and the attenuating device; the attenuating device comprises a first and a second mass unit with a first and a second mass rotatable about the first axis with a first and a second rotational speed, two control units operable to cause an additional rotation of at least one of the first and second masses, and a first and a second support assembly carrying the first and second masses; each control unit controls the angle between the first and second masses and comprises a set of drive gear teeth integral with the first support assembly, a cogwheel with a set of control gear teeth meshing with the drive gear teeth, and an actuator to cause the rotation of the cogwheel about a second axis and of the first mass about said first axis.


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    Titel :

    ROTOR FOR A HOVER-CAPABLE AIRCRAFT


    Beteiligte:
    BOTTASSO LUIGI (Autor:in) / FOSCO ERMANNO (Autor:in) / PISANI PAOLO (Autor:in) / VINCENZO FRANCESCO (Autor:in) / ROSA FRANCESCO (Autor:in) / BRAGHIN FRANCESCO (Autor:in) / CAZZULANI GABRIELE (Autor:in) / CINQUEMANI SIMONE (Autor:in)

    Erscheinungsdatum :

    18.08.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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