The invention relates to a heat dissipation structure of a driving device and an aircraft. The heat dissipation structure comprises a flow guide channel arranged in the rotating axis direction of a propeller assembly of the aircraft, the two ends of the flow guide channel are provided with an air inlet end and an air outlet end, and a driving device in transmission connection with the propeller assembly is arranged close to the air outlet end; wherein an airflow acceleration structure capable of forming a Venturi effect is constructed through the arrangement of the flow guide channel, airflow guided in by the air inlet end is guided to the driving device through the airflow acceleration structure, and air cooling heat dissipation is carried out on the driving device through the accelerated airflow. According to the scheme provided by the invention, sufficient convection heat exchange can be performed on the driving device through the accelerated airflow, and the heat dissipation structure can improve the power and torque of the driving device while realizing efficient air-cooling heat dissipation on the driving device.

    本申请涉及一种驱动装置的散热结构及飞行器。该散热结构包括沿飞行器的螺旋桨组件的转动轴心方向设置的导流通道,导流通道的两端设为进风端和出风端,与螺旋桨组件传动相连的驱动装置靠近于出风端设置;其中,通过导流通道的设置构造出有可形成文丘里效应的气流加速结构,进风端导入的气流经由气流加速结构被导流至驱动装置,用以通过加速后的气流对驱动装置进行风冷散热。本申请提供的方案,能通过加速后的气流对驱动装置进行充分的对流换热,该散热结构对驱动装置实现高效的风冷散热的同时可提高驱动装置的功率和扭矩。


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    Titel :

    Heat dissipation structure of driving device and aircraft


    Weitere Titelangaben:

    驱动装置的散热结构及飞行器


    Beteiligte:
    ZHAO DELI (Autor:in) / LIU YINTONG (Autor:in) / HOU CONG (Autor:in) / HE YI (Autor:in)

    Erscheinungsdatum :

    2022-03-18


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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