The invention is applicable to the technical field of aircraft anti-icing and deicing, and provides an anti-icing device which is characterized in that an anti-icing system is arranged at a pneumatic leading edge, micropores are partially or completely formed in a skin of a downstream wing of the anti-icing system, and a micropore skin is formed; at least one airtight cabin is arranged below the microporous skin; the aircraft further comprises a suction device, an air suction pipeline of the suction device extends into the airtight cabin, and an exhaust pipeline of the suction device is connected with an exhaust port in a wing. Micropores in the micropore skin can effectively'suck 'a turbulent boundary layer, can maintain most laminar boundary layers of the wing, can reduce the resistance of the aircraft and improve the separation control capability of a pneumatic surface, so that the fuel economy of the aircraft is improved, and the requirements of artificial laminar control and overflow water control are met at the same time by adopting one set of system; the deicing device does not need additional air supply, is simple in structure, can be modularly implemented, and can be conveniently applied to light aircrafts and unmanned aerial vehicle systems.

    本发明适用于飞机防除冰技术领域,提供了一种防冰装置,在气动前缘设置防冰系统,在防冰系统下游机翼的蒙皮上部分或全部设置微孔,形成微孔蒙皮;在所述微孔蒙皮的下方设置至少一个气密舱;还包括抽吸装置,所述抽吸装置的吸气管道伸入所述气密舱内,所述抽吸装置的排气管道连接机翼上的排气口。微孔蒙皮中的微孔可以有效“吸入”湍流边界层,还能够维持机翼大部分的层流边界层,可降低飞机阻力、提高气动面分离控制能力,从而提高飞机的燃油经济性,本发明采用一套系统同时达到人工层流控制和溢流水控制的需求;本发明的除冰装置不需要额外供气,结构简单,可以模块化实施,便于应用于轻型飞机和无人机系统。


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    Title :

    Anti-icing device


    Additional title:

    一种防冰装置


    Contributors:
    HU ZHANWEI (author) / DING LIANG (author) / YI XIAN (author) / ZHAO XIANLI (author)

    Publication date :

    2021-06-18


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

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




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