N2O4/UDMH propellant rocket stage. Loaded/empty mass 450,400/31,000 kg. Thrust 10,532.00 kN. Vacuum specific impulse 317 seconds.
Cost $ : 18.000 million. No Engines: 6.
More... - Chronology...
Gross mass: 450,400 kg (992,900 lb).
Unfuelled mass: 31,000 kg (68,000 lb).
Height: 21.00 m (68.00 ft).
Diameter: 7.40 m (24.20 ft).
Span: 7.40 m (24.20 ft).
Thrust: 10,532.00 kN (2,367,687 lbf).
Specific impulse: 317 s.
Specific impulse sea level: 285 s.
Burn time: 108 s.
Number: 26 .
RD-253-14D14 Glushko N2O4/UDMH rocket engine. 1746 kN. Proton KM-1. In production. Developed in 1990s. Isp=317s. First flight 1999. More...
Associated Launch Vehicles
Proton/Briz K/M Earlier 8K82K model Proton, but Briz M storable propellant upper stage replaced the Block D cyrogenic stage. More...
Proton/Briz M Improved Proton orbital launch vehicle. Improvements in lower stages to reduce structural mass, increase thrust, and fully utilize propellants (reducing release of toxic chemicals in stage impact areas). Briz M storable propellant upper stage replaces Block D cyrogenic stage. More...
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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