A leading edge assembly for a hypersonic vehicle is provided. The leading edge assembly includes: an outer wall tapering toward the leading edge, the outer wall having a porous region at the leading edge; a coolant supply assembly in fluid communication with the porous region for selectively providing a coolant flow through the porous region of the outer wall; and an insulating layer disposed between a portion of the coolant supply assembly and the outer wall, where the insulating layer is configured to reduce heat transfer between the coolant supply assembly and the outer wall.

    提供了一种用于高超音速运载器的前缘组件。前缘组件包括:外壁,外壁向前缘逐渐变细,外壁具有前缘处的多孔区域;冷却剂供应组件,冷却剂供应组件与多孔区域流体连通,用于选择性地提供冷却剂流通过外壁的多孔区域;绝缘层,绝缘层设置在冷却剂供应组件的一部分和外壁之间,其中绝缘层被配置为减少冷却剂供应组件和外壁之间的热传递。


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    Titel :

    System for cooling leading edge of high-speed vehicle


    Weitere Titelangaben:

    用于冷却高速运载器的前缘的系统


    Beteiligte:

    Erscheinungsdatum :

    2023-09-08


    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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