Encyclopedia Astronautica

N2O4/UDMH propellant rocket stage. Loaded mass 20,000 kg. Thrust 682.00 kN.

Status: Retired 1996.
Gross mass: 20,000 kg (44,000 lb).
Height: 7.70 m (25.20 ft).
Diameter: 1.90 m (6.20 ft).
Thrust: 682.00 kN (153,319 lbf).
Burn time: 74 s.
Number: 30 .

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Associated Countries
Associated Engines
Associated Launch Vehicles
  • Vysota Russian intercontinental ballistic suborbital launch vehicle. Two stage vehicle based on R-29D SLBM. Suborbital; 30-55 min zero G. Payload volume 0.7 cu. m. Payload 115 kg to 5200 km or 1150 kg to 200 km. Liftoff mass 33 tonnes. More...

Associated Manufacturers and Agencies
  • Makeyev Russian manufacturer of rockets, spacecraft, and rocket engines. Makeyev Design Bureau, Kolomna, Russia. 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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