A rotor for an aircraft is described that comprises: a hub rotatable about an axis and, in turn, comprising a plurality of blades; a mast connectable to a drive member of the aircraft and connected to the hub to drive the hub in rotation about the axis; and damping means to dampen the transmission of vibrations to the mast in a plane orthogonal to the axis; the damping means comprising at least a first mass and a second mass that can eccentrically rotate about the axis with a first and a second speed of rotation, respectively; the first mass and second mass are operatively connected to the mast to generate, respectively, a first and a second damping force on the mast having a main component in a direction radial to the axis; the rotor comprises a transmission unit, which is interposed between the mast and the first and second masses so as to drive the first and second masses in rotation.


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    Titel :

    Rotor for a hover-capable aircraft


    Beteiligte:
    COLOMBO ATTILIO (Autor:in) / BOTTASSO LUIGI (Autor:in) / PISANI PAOLO (Autor:in) / FAVAROTTO ANDREA (Autor:in) / COLOMBO DARIO (Autor:in) / MONTAGNA FEDERICO (Autor:in) / REGONINI ROBERTO (Autor:in) / BRAGHIN FRANCESCO (Autor:in) / CINQUEMANI SIMONE (Autor:in)

    Erscheinungsdatum :

    03.05.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F16H Getriebe , GEARING



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