To provide thermal protection and a drag reduction system for an ultra high-speed aircraft.SOLUTION: A cold source (200) and a cold source driving device (100) are arranged inside a body of an ultra high-speed aircraft. A plurality of micropores (300) is arranged on a wall surface (310) of the body. The cold source driving device (100) comprises an air pump (110), a cold source reservoir (210), and a buffer (150). The air pump (110) supplies compressed air to the cold source reservoir (210) during operation. The cold source (200) enters the buffer (150) and is vaporized by air pressure. High-pressure gas is ejected from the micropores (300) to form a gas film on the outer surface of the body. The gas film not only can perform thermal protection on the ultra high-speed aircraft, but also can effectively reduce viscous drag between the aircraft and external air, to contribute to alleviation or elimination of a thermal barrier phenomenon. Therefore, safety of the ultra high-speed aircraft is improved and service life can be prolonged.SELECTED DRAWING: Figure 1

    【課題】超高速航空機の熱防護と抵抗軽減システムに関する。【解決手段】超高速航空機の機体の内部には冷却源(200)と、冷却源駆動装置(100)とが設けられ、機体壁面(310)には複数の微細孔(300)が設けられ、冷却源駆動装置(100)は空気ポンプ(110)と冷却源格納器(210)と緩衝器(150)とを含み、動作時において、空気ポンプ(110)が冷却源格納器(210)に圧縮空気を供給し、冷却源(200)が空気圧力により緩衝器(150)に入り気化され、高圧の気体が微細孔(300)から噴射されて機体外面にガス膜を形成する。当該ガス膜は超高速航空機に対して熱防護を行うことができるとともに、航空機と外気との粘性抵抗を効果的に低減させることができ、熱の壁といった現象の軽減又は解消に寄与することができ、超高速航空機の安全性を向上し、耐用年数を延長することができる。【選択図】図1


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    Title :

    THERMAL PROTECTION AND DRAG REDUCTION SYSTEM FOR ULTRA HIGH-SPEED AIRCRAFT


    Additional title:

    超高速航空機の熱防護と抵抗軽減システム


    Contributors:
    ZHANG WENWU (author) / XIANG SHUHONG (author) / GUO CHUNHAI (author) / TONG JINGYU (author) / ZHANG TIANRUN (author) / YANG YANG (author) / SONG TAO (author)

    Publication date :

    2019-01-31


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64G Raumfahrt , COSMONAUTICS



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