The invention relates to a coaxial double-rotor-wing system of an aircraft. The coaxial double-rotor-wing system comprises a speed reducer, a lower rotor wing shaft, a lower rotor wing hub, a lower rotor wing, an upper rotor wing, an upper rotor wing shaft, an upper rotor wing hub, an upper rotor wing and a control link or controlling the upper rotor wing and the lower rotor wing and is characterized in that the upper rotor wing and the lower rotor wing are rigid coaxial rotor wings only provided with an axial hinge, a pull rod direct-connection structure between the upper automatic inclinator and the lower automatic inclinator of the control link is omitted, and the control link further comprises a cyclic pitch control mechanism and a differential cyclic pitch control mechanism. The coaxial double-rotor-wing system has the advantages that lift force compensation of the rotor wings is omitted by utilizing the rigid coaxial rotor wings; further aerodynamic limiting caused by air flow separation and air supersonic turbulent flows is avoided under the situation that the condition of lift force compensation is not met; a retreating propeller pitch is decreased by adding the differential cyclic pitch control mechanism, accordingly the aerodynamic resistance of the retreating positions of rotor wing blades can be reduced, ineffective consumption is reduced, and the flat flight speed is improved based on the same output power.


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    Titel :

    Coaxial double-rotor-wing system of aircraft


    Beteiligte:
    LIU HONGWEI (Autor:in) / CHENG MINGZHE (Autor:in) / HAN JIE (Autor:in)

    Erscheinungsdatum :

    2016-01-06


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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