NII Mash N2O4/UDMH rocket engine. 6 kN. experimental 612.25 kgf / 0.071 tf / 0.031tf. Developed. Experimental thruster, 3 thrust levels by 4 valves: 6000 N, 0.7 N, 0.3 N. Specific impulse 326 - 286 sec. Isp=286s.
Application: experimental 612.25 kgf / 0.071 tf / 0.031tf.
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Thrust: 6.00 kN (1,349 lbf).
Specific impulse: 286 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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