Isayev N2O4/UDMH rocket engine. 18.8 kN. Luna Ye-8. Out of Production. Spacecraft maneuvering engine for ascent stage of Luna moon sample return missions. Isp=313s. First flight 1969.
Application: Luna Ye-8.
Engine: 42 kg (92 lb). Chamber Pressure: 92.20 bar. Thrust to Weight Ratio: 45.88. Oxidizer to Fuel Ratio: 1.84. Coefficient of Thrust sea level: 0.
AKA: S5.61; KRD-61.
More... - Chronology...
Status: Out of Production.
Unfuelled mass: 42 kg (92 lb).
Height: 0.71 m (2.34 ft).
Diameter: 0.55 m (1.79 ft).
Thrust: 18.80 kN (4,226 lbf).
Specific impulse: 313 s.
Burn time: 53 s.
First Launch: 1968-70.
Associated Manufacturers and Agencies
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...
Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.
Glushko, V P (ed), Kosmonavtika Entsiklopedi, Moscow 1985 via Dietrich Haeseler.
Kudryavtsev, V M, et.al., Osnovy Teorii i Rascheta, Moscow, Vysshaya Shkola, 1993 via Dietrich Haeseler.
Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
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