The invention discloses a braking differential type rotor wing propeller fixed wing helicopter. Two rotor wings are arranged on wing-shaped small towers at the head and the tail of a fuselage. The paddles of the rotor wings are connected with a rotor wing shaft through a paddle shell which is provided with a flapping hinge, a shimmy hinge and a variable-pitch hinge. A total pitch controller and aperiodic variable pitch controller are arranged to control the paddle pitch of the rotor wings. An upper single-wing fixed wing with high aspect ratio is arranged in the middle of the fuselage, and variable-pitch propellers are arranged on the left and right of the fixed wing. An engine is arranged to drive a differential mechanism through a gearbox and a clutch. A first output shaft of the differential mechanism drives the two rotors through an overrunning clutch, a universal shaft and a rotor synchronous reverser. A second output shaft of the differential mechanism drives the left and rightvariable-pitch propellers through an overrunning clutch, a universal shaft and a propeller synchronous reverser. A wheel type undercarriage is arranged, and different output shafts of the differentialmechanism are braked through a brake. The power of the engine is distributed to the rotor wings or variable-pitch propellers, and various flight modes of helicopters, fixed wings and autorotation rotor wings are freely switched. The helicopter has the advantages of being high in speed, low in energy consumption and suitable for taking-off and landing occasions requiring no airports.

    一种制动差速式旋翼螺旋桨固定翼直升飞机,两个旋翼设置在机身头尾的翼型小塔上,旋翼的桨叶经配有挥舞铰、摆振铰和变距铰组成的桨殼与旋翼轴连接,设置总距和周期变距控制器操纵旋翼的桨距,机身中部设置大展弦比上单翼固定翼,固定翼左右设置变距螺旋桨,设置发动机通过变速箱和离合器驱动差速器,差速器第一输出轴通过超越离合器、万向轴、旋翼同步反转器驱动两旋翼,差速器第二输出轴通过超越离合器、万向轴、螺旋桨同步反转器驱动左右变距螺旋桨,设置轮式起落架,通过制动器制动差速器的不同输出轴,将发动机功率分配给旋翼或变距螺旋桨,自由转换于直升机、固定翼、自转旋翼各种飞行模式,具有速度快、能耗小,适合要求无机场的起降场合。


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    Titel :

    Braking differential type rotor wing propeller fixed wing helicopter


    Weitere Titelangaben:

    制动差速式旋翼螺旋桨固定翼直升飞机


    Beteiligte:
    JIANG FUYU (Autor:in)

    Erscheinungsdatum :

    2020-04-10


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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