Encyclopedia Astronautica

N2O4/UDMH propellant rocket stage. Loaded/empty mass 151,000/9,000 kg. Thrust 3,000.00 kN. Vacuum specific impulse 289 seconds.

Cost $ : 4.000 million. No Engines: 4.

AKA: L-140.
Status: Active.
Gross mass: 151,000 kg (332,000 lb).
Unfuelled mass: 9,000 kg (19,800 lb).
Height: 20.22 m (66.33 ft).
Diameter: 3.35 m (10.99 ft).
Span: 6.00 m (19.60 ft).
Thrust: 3,000.00 kN (674,400 lbf).
Specific impulse: 289 s.
Specific impulse sea level: 259 s.
Burn time: 132 s.
Number: 13 .

More... - Chronology...

Associated Countries
Associated Engines
  • YF-20A Beijing Wan Yuan N2O4/UDMH rocket engine. 750.2 kN. Out of production. Isp=289s. Boosted CZ-2A, CZ-2C, CZ-2E(A), CZ-3, FB-1. First flight 1972. More...

Associated Launch Vehicles
  • CZ-3 Chinese orbital launch vehicle. The Long March 3 was a three-stage launch vehicle designed for delivery of satellites of 1,500 kg mass into geosynchronous transfer orbit. The first and second stages were based on the CZ-2C, and designed and manufactured by the Shanghai Academy of Spaceflight Technology. The majority of the technology and flight hardware used in the CZ-3 had been qualified and proven on the CZ-2C. The third stage, manufactured by CALT, was equipped with an LOX/LH2 cryogenic engine. Long March 3 was also capable of placing spacecraft into an elliptical or circular low earth orbit and sun synchronous 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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