The present application discloses a three-steering gear direct-drive coaxial rotor system and a control strategy, and belongs to the technical field of helicopter structures. The system includes an upper rotor power module, an upper rotor assembly, an upper tilting mechanism, a driving steering gear group assembly, a lower tilting mechanism, a lower rotor assembly, a lower rotor power module, an upper fixing mast, and a lower fixing mast. According to the present application, three steering gears directly drives an upper-layer swashplate and a lower-layer swashplate, to make cyclic pitch and add-subtract collective pitch on rotors. The synchronous tilting mechanism of the present application provides a flexible design solution for the characteristic of cyclic pitch phase angle offset of the rotors gear.


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    Titel :

    THREE-STEERING GEAR DIRECT-DRIVE COAXIAL ROTOR SYSTEM AND FLIGHT CONTROL METHOD FOR CONTROLLING COAXIAL ROTOR AIRCRAFT


    Beteiligte:
    GE XUN (Autor:in) / SHEN YUAN (Autor:in) / GUO SHUZHEN (Autor:in) / LI LIANGWEI (Autor:in) / LIU WEIDONG (Autor:in)

    Erscheinungsdatum :

    16.09.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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