Encyclopedia Astronautica

Credit: Yuzhnoye
Yuzhnoye N2O4/UDMH rocket engine. 142.630 kN. MR-UR-100 / RS-16 (SS-17) stage 2. Out of Production. Based on RD-857. Thrust vector control by secondary gas injection into nozzle. Roll control via special small jet nozzles. Isp=331s.

Application: MR-UR-100 / RS-16 (SS-17) stage 2.

Engine: 192 kg (423 lb). Chamber Pressure: 132.40 bar. Thrust to Weight Ratio: 75.75. Oxidizer to Fuel Ratio: 2.55.

AKA: 15D169.
Status: Out of Production.
Unfuelled mass: 192 kg (423 lb).
Height: 1.68 m (5.50 ft).
Diameter: 0.93 m (3.04 ft).
Thrust: 142.63 kN (32,064 lbf).
Specific impulse: 331 s.
Burn time: 195 s.
First Launch: 1969-72.

More... - Chronology...

Associated Countries
See also
Associated Launch Vehicles
  • MR-UR-100 Ukrainian intercontinental ballistic missile. The Yangel MR-UR-100 was designed as a replacement for Chelomei's UR-100 at the end of its 10 year storage life. Although it could be installed in the same silos, it was 50% heavier. The competing design of Chelomei, the UR-100N, was also put into production when the Soviet hierarchy deadlocked and could not pick one design over the other. 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.

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