Encyclopedia Astronautica

N2O4/UDMH propellant rocket stage. Loaded/empty mass 14,850/2,650 kg. Thrust 294.00 kN. Vacuum specific impulse 287 seconds.

Cost $ : 1.000 million.

Status: Out of production.
Gross mass: 14,850 kg (32,730 lb).
Unfuelled mass: 2,650 kg (5,840 lb).
Height: 5.35 m (17.55 ft).
Diameter: 2.25 m (7.38 ft).
Span: 2.25 m (7.38 ft).
Thrust: 294.00 kN (66,093 lbf).
Specific impulse: 287 s.
Specific impulse sea level: 260 s.
Burn time: 120 s.
Number: 3 .

More... - Chronology...

Associated Countries
Associated Engines
  • YF-3 Beijing Wan Yuan N2O4/UDMH rocket engine. 294 kN. Out of production. Isp=287s. Used on CZ-1D launch vehicle. First flight 1995. More...

Associated Launch Vehicles
  • CZ-1D Chinese orbital launch vehicle. Proposed launch vehicle derived from the CZ-1, but with a new N2O4/UDMH second stage. Used for a suborbital re-entry vehicle test but never flown on an orbital mission. 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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