Encyclopedia Astronautica

N2O4/UDMH propellant rocket stage. Loaded/empty mass 39,000/4,000 kg. Thrust 761.90 kN. Vacuum specific impulse 295 seconds.

Cost $ : 2.000 million.

AKA: L-35.
Status: Active.
Gross mass: 39,000 kg (85,000 lb).
Unfuelled mass: 4,000 kg (8,800 lb).
Height: 7.50 m (24.60 ft).
Diameter: 3.35 m (10.99 ft).
Span: 3.35 m (10.99 ft).
Thrust: 761.90 kN (171,282 lbf).
Specific impulse: 295 s.
Specific impulse sea level: 270 s.
Burn time: 130 s.
Number: 26 .

More... - Chronology...

Associated Countries
Associated Engines
  • YF-22A/23A Beijing Wan Yuan N2O4/UDMH rocket engine. 762 kN. Out of production. Cluster of YF-22A and 4 x YF-23 verniers. Isp=295s. Boosted CZ-2C, CZ-3. First flight 1975. More...

Associated Launch Vehicles
  • CZ-2C Chinese orbital launch vehicle. The CZ-2C was the definitive low earth orbit launch vehicle derived from DF-5 ICBM. It became the basis for an entire family of subsequent Long March vehicles. Many adaptive modifications were made to the configuration of the CZ-2A to handle a variety of new satellites and upper stages. The CZ-2C had improved technical performance and payload capacity compared to the CZ-2A, with later versions having a payload capability of 2,800 kg into a 200 km circular orbit. 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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