Encyclopedia Astronautica

Chinese N2O4/UDMH rocket engine. 107.9 kN. Development ended 1988. Isp=287s. Used on CZ-1C launch vehicle.

Thrust (sl): 97.000 kN (21,806 lbf). Thrust (sl): 9,889 kgf.

Status: Development ended 1988.
Diameter: 1.80 m (5.90 ft).
Thrust: 107.90 kN (24,257 lbf).
Specific impulse: 287 s.
Specific impulse sea level: 258 s.
Burn time: 164 s.

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Associated Countries
See also
Associated Launch Vehicles
  • CZ-1C Chinese orbital launch vehicle. Proposed launch vehicle derived from the CZ-1, with a new upper stage. Never flown. 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...

Associated Stages
  • CZ-1C-3 N2O4/UDMH propellant rocket stage. Loaded/empty mass 6,400/1,000 kg. Thrust 107.00 kN. Vacuum specific impulse 287 seconds. More...

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