The invention relates to a rotor device adjusting mechanism of an aircraft, which comprises an aircraft body and a power unit, the power unit comprises a base and a rotor device, and the base is connected with the aircraft body through a support; a driving device is arranged on the base, the rotor wing device is pivoted to the base through a rotating shaft, the driving device drives the rotating shaft to drive the rotor wing device to rotate, the rotor wing attack angle adjusting mechanism comprises an attack angle driving device, a rotating isolation mechanism and a transmission mechanism, and the attack angle driving device adjusts the attack angle of the rotor wing device through the transmission mechanism; the working mode that the rotors with the large diameter and mass keep rotating at the constant speed is adopted, the output size of the thrust of the rotors is adjusted by changing the attack angles of the rotors, therefore, posture changes are controlled, and the unmanned aerial vehicle has the advantages of being convenient to adjust, good in stability and high in efficiency.

    本发明涉及一种飞行器的旋翼装置调节机构,包括飞行器本体和动力单元,动力单元包括基座和旋翼装置,基座通过支架与飞行器本体连接;基座上设置有驱动装置,旋翼装置通过转轴枢接在基座上,驱动装置驱动转轴带动旋翼装置转动,旋翼攻角调节机构,旋翼攻角调节机构包括攻角驱动装置、旋转隔离机构和传动机构,攻角驱动装置通过传动机构来调节旋翼装置的攻角;本发明采用较大直径和质量的旋翼保持匀速旋转的工作方式,通过改变旋翼攻角的大小来调节旋翼推力的输出大小,从而控制姿态变化,具有调节方便、稳定性好、效率高的特点。


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    Titel :

    Rotor wing device adjusting mechanism of aircraft


    Weitere Titelangaben:

    一种飞行器的旋翼装置调节机构


    Beteiligte:
    ZHANG QIANFAN (Autor:in)

    Erscheinungsdatum :

    2024-03-26


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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