The invention discloses a rigid rotor system for a helicopter. The rigid rotor system comprises a rigid rotor propeller hub, a rigid rotor pitch control mechanism and rigid rotor paddles, wherein the rigid rotor pitch control mechanism and the rigid rotor paddles are glued integrally and are connected with the rigid rotor propeller hub by virtue of bolts. According to the system disclosed by the invention, deep groove ball bearings and thrust bearings in the conventional teeterboard type propeller hub structure are replaced by joint bearings, so that a series of complex structures such as pitch change shafts, flapping hinges and vertical hinges are removed, and the problems such as complexity of the conventional teeterboard type propeller hub structure, heavy weight and short service life can be solved. Meanwhile, the problems that retreating paddleseasily enter an aerodynamic stalling state so as to reduce the aerodynamic efficiency due to swinging during high-speed forward flight and the like are solved, and the rigid rotor system has the advantages of simple structure, light weight, long service life, high maintainability and the like.


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    Titel :

    Rigid rotor system for helicopter


    Beteiligte:
    HU FENGYAN (Autor:in)

    Erscheinungsdatum :

    03.02.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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