The invention relates to a hypersonic aircraft head cone based on a composite cooling mode, which is characterized by comprising a head cone body which is made of a high temperature resistance alloy or ceramic material and is of a multi-micropore structure, wherein the inside of the head cone body is divided into a front chamber and a rear chamber by a separation sheet; the rear of the head cone body is fixedly connected with a center coolant pipeline and at least one periphery coolant pipeline; the at least one periphery coolant pipeline is communicated with the rear chamber; the center coolant pipeline penetrates through the rear chamber and stretches into the front chamber; a center spray orifice is formed in the center of the head of the head cone body, and is located in an extension line of the center coolant pipeline; and a plurality of side spray orifices which are uniformly distributed and are communicated with the rear chamber are formed in the side wall of the head cone body.


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    Titel :

    Hypersonic aircraft head cone based on composite cooling mode


    Beteiligte:
    JIANG PEIXUE (Autor:in) / HUANG GAN (Autor:in) / ZHU YINHAI (Autor:in)

    Erscheinungsdatum :

    2015-08-26


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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