The invention is applicable to the technical field of aircrafts. The invention provides a distributed propulsion flying wing aircraft. The flying wing comprises a flying wing body and a distributed propelling system, the distributed propulsion system is arranged in the flying wing body and comprises a ducted fan system, a turbine engine system and a shaft power transmission system, and the shaft power transmission system transmits shaft power output by the turbine engine system to the ducted fan system. The distributed propelling system integrates a ducted fan system and a turbine engine system, the effect of a large-bypass-ratio engine is achieved, and the oil consumption rate of the flying-wing aircraft can be reduced by 25% or above.

    本发明适用于飞行器技术领域,提供了一种分布式推进飞翼飞行器,包括飞翼本体和分布式推进系统,所述分布式推进系统设置在所述飞翼本体的内部,所述分布式推进系统包括涵道风扇系统、涡轮发动机系统、轴功率传递系统,所述轴功率传递系统将所述涡轮发动机系统输出的轴功率传递给所述涵道风扇系统。本发明中的分布式推进系统集成了涵道风扇系统和涡轮发动机系统,达到了大涵道比发动机效果,使飞翼飞行器的耗油率可降低25%以上。


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    Titel :

    Distributed propulsion flying wing aircraft


    Weitere Titelangaben:

    一种分布式推进飞翼飞行器


    Beteiligte:
    DA XINGYA (Autor:in) / MA XIAOYONG (Autor:in) / TANG SHIYONG (Autor:in) / FAN JIANCHAO (Autor:in) / LI FANGJI (Autor:in) / ZHAO QING (Autor:in) / LI YANG (Autor:in)

    Erscheinungsdatum :

    2020-06-26


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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