Encyclopedia Astronautica

Yuzhnoye N2O4/UDMH rocket engine. 8.580 kN. R-36M2 vehicle bus. Based on RD-864. Two thrust levels. The four thrusters swing out of the stage housing before use. Chamber pressure 41 / 17 bar. Diameter 3,0 / 4,02 m. Isp=313s. First flight 1986.

Application: R-36M2 / RS-20V (SS-18 Mod 4) vehicle bus.

Throttled thrust(vac): 2.470 kN (555 lbf). Engine: 196 kg (432 lb). Chamber Pressure: 41.00 bar. Thrust to Weight Ratio: 4.46. Oxidizer to Fuel Ratio: 1.8.

Unfuelled mass: 196 kg (432 lb).
Height: 1.42 m (4.65 ft).
Diameter: 3.00 m (9.80 ft).
Thrust: 8.58 kN (1,929 lbf).
Specific impulse: 313 s.
Burn time: 700 s.
First Launch: 1983-85.
Number: 42 .

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Associated Countries
See also
Associated Launch Vehicles
  • Dnepr Ukrainian orbital launch vehicle based on decommissioned R-36M2 intercontinental ballistic missiles. More...

Associated Manufacturers and Agencies
  • Yuzhnoye Ukrainian manufacturer of rockets, spacecraft, and rocket engines. Yangel Design Bureau, Dnepropetrovsk, Ukraine. More...

Associated Propellants
  • 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...

  • Shnyakin, V N, Shidkostnye Raketye Dvigateli - Opisanie i Osnovnye Tekhnicheskie Dannye, GKB Yuzhnoe "Yangel", Dnepropetrovsk 1996 via Dietrich Haeseler.

Associated Stages
  • R-36M2-3 N2O4/UDMH propellant rocket stage. Loaded/empty mass 4,266/2,356 kg. Thrust 18.60 kN. Vacuum specific impulse 317 seconds. Main engine could be throttled to 800 kgf. More...

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