A rotor (3,3'') for an aircraft (1) is described that comprises: a hub (5) rotatable about an axis (A) and, in turn, comprising a plurality of blades (9); a mast (6) connectable to a drive member of the aircraft (1) and connected to the hub (5) to drive the hub (5) in rotation about the axis (A); and damping means (15; 20a, 20b; 21a, 21b) to dampen the transmission of vibrations to the mast (6) in a plane orthogonal to the axis (A); the damping means (15; 20a, 20b; 21a, 21b) comprising at least a first mass (20a, 20b) and a second mass (21a, 21b) that can eccentrically rotate about the axis (A) with a first and a second speed of rotation ((N-1) *©; -(N+1)*©), respectively; the first mass (20a, 20b) and second mass (21a, 21b) are operatively connected to the mast (6) to generate, respectively, a first and a second damping force on the mast (6) having a main component in a direction radial to the axis (A); the rotor (3, 3") comprises a transmission unit (19''), which is interposed between the mast (6) and the first and second masses (20a, 20b; 21a, 21b) so as to drive the first and second masses in rotation (20a, 20b; 21a, 21b).


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    Title :

    ROTOR FOR A HOVER-CAPABLE AIRCRAFT


    Additional title:

    ROTOR FÜR EIN SCHWEBEFÄHIGES FLUGZEUG
    ROTOR POUR UN AÉRONEF CAPABLE DE VOL STATIONNAIRE



    Publication date :

    2019-08-21


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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