The invention discloses an aircraft electric propeller heat dissipation system which comprises a cabin shell, a propeller body and a driver shell coaxial with the propeller body are arranged in the cabin shell, and a driver power assembly is arranged on the inner wall of the driver shell. The system further comprises an axial flow fan which is arranged at one end, far away from the propeller body,of the driver shell. According to the aircraft electric propeller heat dissipation system, the problems of arrangement and heat dissipation of the propeller body and the driver are solved in a limited space, the system is suitable for a high-power electric propeller, and the heat dissipation reliability is improved.

    本发明公开了一种飞行器电力推进器散热系统,包括机舱外壳,所述机舱外壳内设有推进器本体和与所述推进器本体同轴设置的驱动器外壳,所述驱动器外壳的内壁设有驱动器功率组件,还包括设于所述驱动器外壳远离所述推进器本体一端的轴流风扇。本发明所提供的飞行器电力推进器散热系统在有限空间解决了推进器本体和驱动器的布置及散热问题,适用于大功率电力推进器,提高了散热的可靠性。


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    Titel :

    Aircraft electric propeller heat dissipation system


    Weitere Titelangaben:

    一种飞行器电力推进器散热系统


    Beteiligte:
    XIAO GANG (Autor:in) / WANG SHAOBO (Autor:in) / LI MING (Autor:in) / ZHU PENGCHENG (Autor:in) / HU ZHIQIANG (Autor:in)

    Erscheinungsdatum :

    23.03.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / H02K Dynamoelektrische Maschinen , DYNAMO-ELECTRIC MACHINES



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