The invention belongs to the technical field of aircraft propulsion system design, and particularly relates to an aircraft-integrated propulsion system, which comprises an engine embedded in an aircraft body and internally provided with a starting motor; an air inlet of the engine is formed in the back of the body; a main nozzle exhaust port of the engine is formed in the rear end of the body; an outer duct exhaust port of the engine is divided into two halves, and outlets of the two halves are formed in the rear end of the aircraft body and are symmetrical about the axis of the aircraft; the propulsion system integrated with the aircraft further comprises two groups of ducted fans which are respectively arranged in outlets of exhaust ports of the two half outer ducts and are driven by a starting motor.

    本申请属于飞机推进系统设计技术领域,具体涉及一种与飞机融合的推进系统,包括:发动机,内埋于机体内,内置起动电机;发动机的进气口成型在机体背部;发动机的主喷管排气口成型在机体后端;发动机的外涵道排气口部位分为两半,两半的出口成型在机体后端,关于飞机轴线对称;与飞机融合的推进系统,还包括:两组涵道风扇,分别设置在两半外涵道排气口部位的出口中,以起动电机进行驱动。


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    Titel :

    Propulsion system integrated with aircraft


    Weitere Titelangaben:

    一种与飞机融合的推进系统


    Beteiligte:
    GONG SHENG (Autor:in) / YUAN CHANGLONG (Autor:in) / SU GUIYING (Autor:in) / LI WEI (Autor:in) / HE JIAQIAN (Autor:in) / DUAN YUFA (Autor:in)

    Erscheinungsdatum :

    2023-07-11


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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