Encyclopedia Astronautica

N2O4/UDMH propellant rocket stage. Loaded/empty mass 33,600/4,000 kg. Thrust 831.01 kN. Vacuum specific impulse 297 seconds.

Cost $ : 3.000 million.

AKA: L-35.
Status: Active.
Gross mass: 33,600 kg (74,000 lb).
Unfuelled mass: 4,000 kg (8,800 lb).
Height: 11.53 m (37.82 ft).
Diameter: 3.35 m (10.99 ft).
Span: 3.35 m (10.99 ft).
Thrust: 831.01 kN (186,817 lbf).
Specific impulse: 297 s.
Specific impulse sea level: 260 s.
Burn time: 110 s.
Number: 16 .

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Associated Countries
Associated Engines
  • YF-25/23 Beijing Wan Yuan N2O4/UDMH rocket engine. 831 kN. In production. Cluster of YF-25 and 4 x YF-23 verniers. Isp=295s. First stage engine for CZ-2D, CZ-2E, CZ-2E(A), CZ-3A, CZ-3B, CZ-3C, CZ-4A. First flight 1988. More...

Associated Launch Vehicles
  • CZ-3A Chinese three-stage orbital launch vehicle. The Long March 3A, by incorporating the mature technologies of the CZ-3 and adding a more powerful cryogenic third stage and more capable control system, had a greater geosynchronous transfer orbit capability, greater flexibility for attitude control, and better adaptability to a variety of launch missions. 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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