N2O4/UDMH propellant rocket stage. Loaded/empty mass 179,000/9,000 kg. Thrust 3,265.14 kN. Vacuum specific impulse 289 seconds.
Cost $ : 6.000 million. No Engines: 4.
More... - Chronology...
Status: Development ended 1997.
Gross mass: 179,000 kg (394,000 lb).
Unfuelled mass: 9,000 kg (19,800 lb).
Height: 23.08 m (75.72 ft).
Diameter: 3.35 m (10.99 ft).
Span: 7.00 m (22.90 ft).
Thrust: 3,265.14 kN (734,033 lbf).
Specific impulse: 289 s.
Specific impulse sea level: 259 s.
Burn time: 155 s.
Number: 25 .
YF-20B Beijing Wan Yuan N2O4/UDMH rocket engine. 816.3 kN. In production. Isp=289s. Boosted CZ-2C, CZ-2D, CZ-2E, CZ-2E(A), CZ-3A, CZ-3B, CZ-3C, CZ-4A. First flight 1988. More...
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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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