Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 25,200/2,500 kg. Thrust 428.06 kN. Vacuum specific impulse 308 seconds. Orevo has sectioned hardware. Tsniimash has 1:10 structural simulation model. All figures accurate except empty mass estimated. Source: Placard, TsNIIMASH, Orevo.
More... - Chronology...
Status: Out of production.
Gross mass: 25,200 kg (55,500 lb).
Unfuelled mass: 2,500 kg (5,500 lb).
Diameter: 2.40 m (7.80 ft).
Span: 8.73 m (28.64 ft).
Thrust: 428.06 kN (96,232 lbf).
Specific impulse: 308 s.
Specific impulse sea level: 252 s.
Burn time: 160 s.
U102-000 Glushko Nitric acid/UDMH rocket engine. 468 kN. R-26 stage 2. Out of production. Isp=307s. More...
Associated Launch Vehicles
R-26 Ukrainian intercontinental ballistic missile. Two stage light ICBM developed 1960-1962, but cancelled so that Yangel could concentrate his efforts on the R-36. After project cancellation, a mock-up of this missile was shown in Moscow parades and misidentified for years by Western analysts as the 'SS-8'. More...
Nitric acid/UDMH Drawing on the German World War II Wasserfall rocket, nitric acid (HNO3) became the early storable oxidiser of choice for missiles and upper stages of the 1950's. To overcome various problems with its use, it was necessary to combine the nitric acid with N2O4 and passivation compounds. These formulae were considered extremely secret at the time. By the late 1950's it was apparent that N2O4 by itself was a better oxidiser. Therefore nitric acid was almost entirely replaced by pure N2O4 in storable liquid fuel rocket engines developed after 1960. 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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