Development status of the hypersonic turbojet engine for Mach 5 flight in JAXA

H. Kobayashi, H. Taguchi, T. Kojima, K. Harada, K. Okai, M. Hongoh, T. Arai, Tetsuya Satou

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    Abstract

    Development of the hypersonic turbojet engine with air-precooling system has been conducted in JAXA since 2004. This engine can protect its turbo-machinery from aerodynamic heat during hypersonic flight owing to liquid hydrogen coolant supplied in the air precooler. The latest model of the hypersonic turbojet engine assembled in 2007 has 0.225 by 0.225 meters square cross section, a total length of 2.67m. We have a phased plan for making Mach 5 flight test of the hypersonic turbojet engine by 2015. Our first target velocity of flight experiment is Mach 2. In 2009 we successfully conducted pre-flight verification tests in an altitude testing facility of Akiruno Research Center. In September 2010 the first Mach 2 flight was conducted in Taiki Aerospace Research Field. The Mach 2 flight experimental vehicle carried the engine and propellant system supplying gaseous hydrogen as a fuel and liquid nitrogen as a coolant of the precooler. The engine was ignited at Mach 2 and operated for 20 seconds in supersonic flight environment. The flight experiment was successfully excluding parachute deployment failure. In order to conduct the next Mach 5 flight we must verify the air precooling system with liquid hydrogen in ground test facilities. Direct connected wind tunnel test of the engine is to be conducted in 2011 in Noshiro Testing Center, where free jet wind tunnel test at Mach 5 condition in Kakuda Space Center is scheduled in 2013.

    Original languageEnglish
    Title of host publication62nd International Astronautical Congress 2011, IAC 2011
    Pages6655-6659
    Number of pages5
    Volume8
    Publication statusPublished - 2011
    Event62nd International Astronautical Congress 2011, IAC 2011 - Cape Town
    Duration: 2011 Oct 32011 Oct 7

    Other

    Other62nd International Astronautical Congress 2011, IAC 2011
    CityCape Town
    Period11/10/311/10/7

    Fingerprint

    Turbojet engines
    Hypersonic aerodynamics
    Mach number
    Engines
    Coolants
    Hydrogen
    Wind tunnels
    Air
    Parachutes
    Liquids
    Testing
    Liquid nitrogen
    Propellants
    Test facilities
    Machinery
    Aerodynamics
    Experiments

    ASJC Scopus subject areas

    • Aerospace Engineering

    Cite this

    Kobayashi, H., Taguchi, H., Kojima, T., Harada, K., Okai, K., Hongoh, M., ... Satou, T. (2011). Development status of the hypersonic turbojet engine for Mach 5 flight in JAXA. In 62nd International Astronautical Congress 2011, IAC 2011 (Vol. 8, pp. 6655-6659)

    Development status of the hypersonic turbojet engine for Mach 5 flight in JAXA. / Kobayashi, H.; Taguchi, H.; Kojima, T.; Harada, K.; Okai, K.; Hongoh, M.; Arai, T.; Satou, Tetsuya.

    62nd International Astronautical Congress 2011, IAC 2011. Vol. 8 2011. p. 6655-6659.

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    Kobayashi, H, Taguchi, H, Kojima, T, Harada, K, Okai, K, Hongoh, M, Arai, T & Satou, T 2011, Development status of the hypersonic turbojet engine for Mach 5 flight in JAXA. in 62nd International Astronautical Congress 2011, IAC 2011. vol. 8, pp. 6655-6659, 62nd International Astronautical Congress 2011, IAC 2011, Cape Town, 11/10/3.
    Kobayashi H, Taguchi H, Kojima T, Harada K, Okai K, Hongoh M et al. Development status of the hypersonic turbojet engine for Mach 5 flight in JAXA. In 62nd International Astronautical Congress 2011, IAC 2011. Vol. 8. 2011. p. 6655-6659
    Kobayashi, H. ; Taguchi, H. ; Kojima, T. ; Harada, K. ; Okai, K. ; Hongoh, M. ; Arai, T. ; Satou, Tetsuya. / Development status of the hypersonic turbojet engine for Mach 5 flight in JAXA. 62nd International Astronautical Congress 2011, IAC 2011. Vol. 8 2011. pp. 6655-6659
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