The invention relates to a composite distributed electric duct propulsion aircraft. The aircraft comprises a fuselage; a wing attached to the fuselage; the distributed electric ducted fans are mounted above the wing surfaces of the wings; and the tail electric ducted fan is installed at the tail of the fuselage, and the power of the tail electric ducted fan is larger than that of a single ducted fan in the distributed electric ducted fans. According to the electric duct propulsion aircraft, the tail propulsion electric duct and the wing electric duct are matched with each other to complement each other, and the high-speed and low-speed aerodynamic performance of the electric duct propulsion aircraft, especially the aerodynamic performance under 70-100 kilometers per hour, is fully optimized.

    本发明涉及一种复合分布式电涵道推进飞机,包括:机身;机翼,机翼附连到机身;分布式电涵道风扇,分布式电涵道风扇安装在机翼的翼面上方;以及尾部电涵道风扇,尾部电涵道风扇安装到机身的尾部,其中,尾部电涵道风扇的功率大于分布式电涵道风扇中的单个涵道风扇的功率。通过尾推电涵道与翼上电涵道的互相配合、取长补短,充分优化电涵道推进飞机的高、低速气动性能,特别是在70‑100千米每小时下的气动性能。


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    Title :

    Composite distributed electric duct propulsion aircraft


    Additional title:

    复合分布式电涵道推进飞机


    Contributors:
    CHEN ZHIYU (author) / XIE RUIXUAN (author) / ZHOU XIYUE (author) / ZHAO XIAOHUI (author) / SONG HOUJIN (author) / NIE SHIYU (author)

    Publication date :

    2024-08-27


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

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



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