A rotor (3) for a hover-capable aircraft (1) is described that comprises: a hub (5) rotating about an axis (A) and, in turn, comprising a plurality of blades (9), a mast (6) connectable to a power unit of the aircraft (1) and operatively connected to the hub (5) to drive the hub (5) in rotation about said axis (A), and an attenuating device (15) to attenuate the transmission of vibrations from the mast (6) to the aircraft (1) parallel to said (A); the attenuating device (15), in turn, comprising a casing (20), a first mass (21) free to oscillate parallel to said axis (A) with respect to the casing (20) and elastically connected to the casing (20), a second mass (25) free to oscillate parallel to said axis (A), connection means (30) adapted to make the first and second masses (21, 25) integrally movable along said axis (A) when the angular speed (Ω) of the mast (6) assumes a first value (Ω1), and actuator means (35) activatable to decouple the first and second masses (21, 25) when the angular speed (Ω) of the mast (6) assumes a second value (Ω2), different from the first value (Ω1).


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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


    Contributors:

    Publication date :

    2021-08-04


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F16F SPRINGS , Federn



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