Encyclopedia Astronautica
MR-UR-100 St 1

N2O4/UDMH rocket stage. 1236.00 kN (277,864 lbf) thrust. Mass 59,000 kg (130,073 lb).

Status: Retired 1988.
Gross mass: 59,000 kg (130,000 lb).
Unfuelled mass: 5,000 kg (11,000 lb).
Height: 14.30 m (46.90 ft).
Diameter: 2.25 m (7.38 ft).
Thrust: 1,236.00 kN (277,863 lbf).
Number: 87 .

More... - Chronology...

Associated Countries
Associated Engines
  • RD-268 Glushko N2O4/UDMH rocket engine. 1236 kN. MR-UR-100 / RS-16 (SS-17) stage 1. Out of Production. First flight 1976. Modification of RD-263 engine. Isp=319s. First flight 1990. More...

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...
  • MR-UR-100U 15A16 Ukrainian intercontinental ballistic missile. Improved version of the MR-UR-100U loaded into the super-hardened 15P715U universal silo, with a modernised guidance system with better reliability and accuracy. 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...

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