Isayev N2O4/UDMH rocket engine. 3.430 kN. Luna 15-24 used this low thrust engine in system KTDU-417 for soft-landing on the moon. Out of Production. Isp=254s. Pressure-fed engine; could be throttled to 2.06 kN.
See entry KTDU-417.
Application: Luna 15-24 low thrust engine in system KTDU-417.
Chambers: 2. Throttled thrust(vac): 2.060 kN (463 lbf). Chamber Pressure: 8.90 bar. Oxidizer to Fuel Ratio: 2.4.
More... - Chronology...
Status: Out of Production.
Thrust: 3.43 kN (771 lbf).
Specific impulse: 254 s.
Burn time: 30 s.
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...
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