The invention relates to a tilting mechanism of an electric vertical take-off and landing aircraft for integrally tilting wings, which is characterized in that the wings tilt by connecting a steering engine with a coupler to output torque to a power shaft A, the power shaft A drives a gear A and a gear B, the gear B drives a power shaft B, the power shaft B drives a gear C, the gear C drives a gear D, the gear D acts on an aluminum pipe, and the aluminum pipe drives a lug; and then the whole wing is driven to tilt. The vertical take-off and landing of the airplane can be realized, and the application prospect is wide; the reliability is high, and the steering engine load is reduced through the reduction gear set.

    本发明涉及一种用于机翼整体倾转的电动垂直起降飞行器倾转机构,机翼倾转通过舵机连接联轴器输出扭矩到动力轴A,动力轴A带动齿轮A、齿轮B,齿轮B带动动力轴B,动力轴B带动齿轮C,齿轮C带动齿轮D,齿轮D作用到铝管,铝管带动耳片,进而带动整机翼进行倾转。本发明可实现飞机垂直起降,具有广阔应用前景;本发明可靠性高,通过减速齿轮组降低舵机负载。


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    Title :

    Tilting mechanism of electric vertical take-off and landing aircraft for integrally tilting wings


    Additional title:

    一种用于机翼整体倾转的电动垂直起降飞行器倾转机构


    Contributors:
    DUAN YIWEI (author) / YANG YOUXU (author) / YE BO (author) / ZHANG ZHIWEI (author) / WANG BIN (author) / WU YIFEI (author) / LIU BEI (author)

    Publication date :

    2024-09-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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