The present invention relates to a rotor (1, 1', 1'', 1''', 1'''', 1''''') for helicopter comprising a shaft (2) adapted to be put into rotation by at least one engine element, a hub (3) splined to the shaft (2), at least four blades (4) radially connected to the hub (2) and rotationally movable thereabout, at least one damping connection assembly (9, 9', 9'', 9''') provided between at least one first blade and at least one second blade of the at least four blades (4), the at least one first blade and the at least one second blade being radially non-adjacent, wherein radially non-adjacent means that said at least one first blade and said at least one second blade define each a radius of said rotor and said rotor comprise at least one third blade interposed between said at least one first blade and said at least one second blade which defines a third radius of said rotor. The at least one damping connection assembly (9, 9', 9'', 9''') comprises at least one upper connection rod (10) arranged above the hub (3) and connected to the first blade at a first end (11) of the at least one damping connection assembly (9, 9', 9'', 9'''), at least one lower connection rod (12) arranged below the hub (3) connected to the second blade at a second end (13) of the at least one damping connection assembly (9, 9', 9'', 9'''), and at least one damper element (14, 14', 14'') interposed between the first end (11) and the second end (13). The present invention also relates to a helicopter adopting the rotor (1, 1', 1'', 1''', 1'''', 1''''').


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    Title :

    ROTOR FOR HELICOPTER WITH IMPROVED DAMPING


    Additional title:

    ROTOR FÜR HUBSCHRAUBER MIT VERBESSERTER DÄMPFUNG
    ROTOR POUR HÉLICOPTÈRE À AMORTISSEMENT AMÉLIORÉ


    Contributors:

    Publication date :

    2024-05-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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