The invention provides an ultra-high speed aircraft thermal protection and drag reduction method and system. The method includes that a cold source is arranged inside the cavity of an ultra-high speed aircraft, a plurality of micropores are arranged in the wall surface of the cavity, and the cold source is ejected out of the micropores in a high-pressure air state under the action of driving force to form an air film on the outer surface of the cavity. The air film can perform thermal protection on the ultra-high speed aircraft, viscous drag of the aircraft with external air can be effectively reduced, thermal barrier is favorably alleviated or eliminated, security of the ultra-high speed aircraft is improved, service life is prolonged, and a good application prospect is achieved. A cold source driving unit comprising an air pump, a cold source storer and a buffer is adopted in the system, the air pump supplies compressed air to the cold source storer during the operation state, the cold source enters the buffer to be vaporized under the action of air pressure, and the air is ejected from the micropores to form the air film under the action of pressure.


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    Titel :

    Ultra-high speed aircraft thermal protection and drag reduction method and system


    Beteiligte:
    ZHANG WENWU (Autor:in) / XIANG SHUHONG (Autor:in) / GUO CHUNHAI (Autor:in) / TONG JINGYU (Autor:in) / ZHANG TIANRUN (Autor:in) / YANG YANG (Autor:in) / SONG TAO (Autor:in)

    Erscheinungsdatum :

    13.05.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS / F42B EXPLOSIVE CHARGES, e.g. FOR BLASTING , Explosive Ladungen, z.B. für Sprengungen



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