A pressure-fed, full-blowdown, nitrogen tetroxide (NTO)/hydrazine (N2H4) bipropellant liquid apogee propulsion system was selected for engineering test satellite--VI (ETS-VI), a 2000-kg Japanese engineering test satellite. This 2000-kg mass geostationary satellite is scheduled to be launched by an H-II rocket in 1994. The apogee engine required a high reliability and a relatively high performance for a pressure fed system. In the preliminary development phase of the apogee engine, a peak vacuum specific Ispv of 325 s was set as the initial development target. This performance requirement of the apogee engine is greater than that of the bipropellant engine using NTO/monomethyl hydrazine (MMH). To meet such high performance requirements, the authors employed a NTO/N2H4 propellant system instead of NTO/MMH propellant and used a very large area ratio nozzle (nozzle area ratio is 200 to 300). To enhanced the reliability of the apogee propulsion system, the authors selected a pressure-fed, full-blowdown system. Fundamental studies including hard-start, pop and thermal problems were also conducted during the development series of apogee engine started in 1983.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Development Test of a Liquid Apogee Engine for the ETS-VI


    Publication date :

    1994


    Size :

    27 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English






    Hydrazine/NTO liquid apogee engine for the ETS-VI

    IIHARA, S. / MIYAJIMA, HIROSHI / NAGASHIMA, RYUICHI | AIAA | 1987


    Hydrazine/NTO liquid apogee engine for the ETS-6

    Iihara, S. / Miyajima, H. / Nagashima, R. | Tema Archive | 1987