Encyclopedia Astronautica

N2O4/UDMH rocket stage. 142.00 kN (31,923 lbf) thrust. Mass 10,000 kg (22,046 lb).

Status: S.
Gross mass: 10,000 kg (22,000 lb).
Unfuelled mass: 1,000 kg (2,200 lb).
Height: 3.20 m (10.40 ft).
Diameter: 2.15 m (7.05 ft).
Thrust: 142.00 kN (31,922 lbf).
Burn time: 195 s.
Number: 87 .

More... - Chronology...

Associated Countries
Associated Engines
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 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...

Home - Browse - Contact
© / Conditions for Use