The invention provides a tail rotor component for a helicopter. The tail rotor component comprises a rotor disc; a first blade group and a second blade group, wherein the first blade group comprises at least three first blades which are distributed on the periphery of the rotor disc at intervals; an included angle between two adjacent first blades in the first blade group is no less than a first preset angle and a difference between two adjacent included angles is between a second preset angle and a third preset angle; and the second blade group is symmetrically arranged, relative to the circle center of the rotor disc, with the first blade group on the rotor disc and comprises at least three second blades which are distributed on the periphery of the rotor disc at intervals; an included angle between two adjacent second blades in the second blade group is no less than the first preset angle and a difference between two adjacent included angles is between the second preset angle and the third preset angle. By arranging the blades on the rotor disc in a non-uniform mode, the tail rotor component for the helicopter can be used for greatly reducing the noise level of a tail rotor.


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    Titel :

    Tail rotor component for helicopter


    Beteiligte:
    WANG HAOWEN (Autor:in) / LIU FENG (Autor:in) / ZHANG YUWEN (Autor:in) / JIANG CHEN (Autor:in)

    Erscheinungsdatum :

    2015-05-27


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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