A pressure-fed, full-blowdown, bipropellant liquid apogee propulsion module was selected for the ETS-6, a 2000 kg mass Japanese engineering test satellite. This paper describes preliminary development efforts of the 2000 N thrust class liquid apogee engine. As an attempt to meet a very high performance requirements, we employed hydrazine/nitrogen tetroxide (NTO) propellant system with a nozzle area ratio as high as 300:1. It was shown that a high performance film cooled engine was feasible with delivered vacuum specific impulse of 324 plus/minus 1 s at a chamber pressure of 8.5 kg/cm2, abs. Large area ratio specific impulse can be predicted by a simple method with the energy release efficiency determined from sea level tests with a small area ratio nozzle. Popping occurred at higher pressures may be correlated by fuel orifice Reynolds number for a particular injector design, i.e., double concentric ring arrangement of unlike doublet elements with film cooling orifices in the outermost ring. Problem areas regarding further development are described briefly.
Hydrazine/NTO liquid apogee engine for the ETS-6
Hydrazin-Stickstofftetroxid-Fluessigtreibstofftriebwerk fuer den ETS-6 im Apogaeum
AIAA-Papers ; Jul ; 1-9
1987
9 Seiten, 11 Bilder, 3 Tabellen, 12 Quellen
Conference paper
English
Hydrazine/NTO liquid apogee engine for the ETS-VI
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