The pre-cooled turbojet engine is one of the most promising candidates for the propulsion system of hypersonic transport. A notable feature of this engine is to use an air pre-cooling device using liquid hydrogen fuel as a coolant in order to pretect the turbo-machinery from aerodynamic heating under hypersonic flight conditions. JAXA's recent model of the pre-cooled turbojet engine called 'S-Engine' has 0.225 by 0.225 meters square cross section, a total length of 2.67 m, and a mass of 134 kg. It produces a thrust of 122 kgf by firing liquid hydrogen fuel in afterburner, its compressor rotational speed is 80,000 rpm and its compressor pressure ratio is six. This engine is developed for the flight test at Mach 2 condition integrated with a balloon-launched missile-like vehicle. This paper describes pre-flight verification test results of the engine control system including liquid hydrogen supplying system.


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    Titel :

    Development of a Hypersonic Turbojet Engine Controller Designed for a Flight Experiment


    Beteiligte:
    H. Kobayashi (Autor:in) / H. Taguchi (Autor:in) / S. Sawai (Autor:in) / K. Fujita (Autor:in) / T. Kojima (Autor:in)

    Erscheinungsdatum :

    2009


    Format / Umfang :

    32 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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