The embodiment of the specification discloses an aircraft electric propulsion system, the system comprises a power generation subsystem, a power distribution subsystem and a propulsion subsystem, the power generation subsystem comprises a turboshaft engine and a generator; the turboshaft engine is arranged at the tail part of the aircraft and is used for driving the generator to generate electricity; wherein a fan of the turboshaft engine is used for sucking low-speed air of a fuselage boundary layer into the turboshaft engine; the power distribution subsystem is used for distributing power to the propulsion subsystem, and the propulsion subsystem drives an aircraft; wherein the electric power comprises electric power from a power generation subsystem.

    本说明书实施例公开了一种飞行器电力推进系统,所述系统包括发电分系统、配电分系统以及推进分系统,所述发电分系统包括涡轴发动机和发电机;所述涡轴发动机设置在飞行器尾部,用于驱动所述发电机发电;其中,所述涡轴发动机的风扇用于将机身边界层的低速空气吸入所述涡轴发动机;所述配电分系统用于将电力分配给所述推进分系统,由所述推进分系统驱动飞行器;其中,所述电力包括来自发电分系统的电力。


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    Titel :

    Aircraft electric propulsion system and wing distributed electric propeller propulsion aircraft


    Weitere Titelangaben:

    飞行器电力推进系统及机翼分布式电动螺旋桨推进飞行器


    Beteiligte:
    ZHANG XIAODONG (Autor:in)

    Erscheinungsdatum :

    06.05.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

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



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