The invention relates to the technical field of thermal protection of the leading edge of a hypersonic aircraft, in particular to an active cooling structure for the leading edge of the hypersonic aircraft, which comprises a thermal protection plate, an inlet channel and an outlet channel, the upper end face and the lower end face of the thermal protection plate are provided with four inlet channels and four outlet channels for cooling working media to flow in and flow out respectively, a bionic fractal channel is arranged in the thermal protection plate, and the inlet channels and the outlet channels are communicated through the bionic fractal channel. By designing a new bionic fractal channel structure, the cooling working medium is concentrated in a front edge stationary point area of the hypersonic aircraft, reasonable distribution of the cooling working medium is achieved, on-way resistance loss of the cooling working medium is reduced, and therefore pump power is reduced.

    本发明涉及高超声速飞行器前缘热防护技术领域,尤其涉及一种高超声速飞行器前缘主动冷却结构,包括热防护板、入口通道和出口通道,所述热防护板呈与高超声速飞行器前端形状相匹配的半圆环形结构,所述热防护板的上端端面和下端端面分别设有四个用于冷却工质流入和流出的所述入口通道和出口通道,所述热防护板的内部设有仿生分形通道,所述入口通道和出口通道通过所述仿生分形通道连通。本发明通过设计仿生分形通道新结构,使冷却工质集中在高超声速飞行器前缘驻点区域,实现了对冷却工质的合理分配,降低了冷却工质的沿程阻力损失,从而降低泵功率。


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    Title :

    Active cooling structure for leading edge of hypersonic flight vehicle


    Additional title:

    一种高超声速飞行器前缘主动冷却结构


    Contributors:
    TANG YICUN (author) / YU TINGFANG (author) / GUO XING (author)

    Publication date :

    2024-03-22


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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