The invention discloses a hypersonic flow drag reduction structure, and relates to the technical field of hypersonic aircrafts. The hypersonic flow drag reduction structure comprises two or more independent small rib units arranged on the surface of an aircraft, and the small rib units are configured to be evenly arranged in the spanwise direction of the aircraft; wherein each small rib unit comprises a plurality of bionic microstructures arranged in the flow direction, and each bionic microstructure is obtained by constructing bionic grooves which are arranged in a V shape in space. According to the hypersonic flow resistance reduction structure, additional resistance is almost not introduced under the hypersonic flow condition, meanwhile, the wall surface friction resistance of the aircraft is reduced through flow control, and the hypersonic flow resistance reduction structure has a large engineering application prospect on hypersonic aircrafts.

    本发明公开了一种高超声速流动减阻结构,涉及高超声速飞行器技术领域包括设置在飞行器表面的两个或两个以上独立的小肋单元,且各小肋单元均被配置为沿飞行器的展向方向均匀排列;其中,各小肋单元均包括多个沿流向方向排列的仿生微结构,各仿生微结构均由在空间上呈V形布局的仿生沟槽构建得到。本发明提供一种高超声速流动减阻结构,在高超声速流动条件下几乎不引入附加阻力的同时,通过对流动控制实现飞行器壁面摩阻的降低,在高超声速飞行器上具有较大的工程应用前景。


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    Title :

    Hypersonic flow drag reduction structure


    Additional title:

    高超声速流动减阻结构


    Contributors:
    JIA YAO (author) / WANG GANG (author) / ZHU KE (author) / YANG YANGUANG (author) / WEN BO (author) / XIE FENG (author) / YANG BO (author) / WANG SHAOYI (author) / LIAO ZIQI (author)

    Publication date :

    2024-09-20


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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