NII Mash N2O4/UDMH rocket engine. 400 mN. In Production. Experimental low-thrust thruster. Chamber from niobium alloy. Chamber pressure 41 / 17 bar. Specific impulse 313 / 302,3 sec. Isp=290s.
Engine: 0.10 kg (0.22 lb). Chamber Pressure: 41.00 bar. Thrust to Weight Ratio: .4.
Status: In Production.
More... - Chronology...
Unfuelled mass: 0.10 kg (0.22 lb).
Thrust: 0.40 N (0.08 lbf).
Specific impulse: 290 s.
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N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...
Haeseler, Dietrich, Datasheets from NII Mashinostroeniye, Nishnaya Salda, 1992 via Dietrich Haeseler.
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