Encyclopedia Astronautica

N2O4/UDMH propellant rocket stage. Loaded/empty mass 153,000/10,000 kg. Thrust 3,295.00 kN. Vacuum specific impulse 291 seconds.

Cost $ : 4.000 million. No Engines: 4.

AKA: L-140.
Status: Active.
Gross mass: 153,000 kg (337,000 lb).
Unfuelled mass: 10,000 kg (22,000 lb).
Height: 20.52 m (67.32 ft).
Diameter: 3.35 m (10.99 ft).
Span: 6.00 m (19.60 ft).
Thrust: 3,295.00 kN (740,745 lbf).
Specific impulse: 291 s.
Specific impulse sea level: 261 s.
Burn time: 122 s.
Number: 40 .

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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-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...
  • CZ-2C/SD On April 28, 1993, the Chinese Great Wall Industrial Corporation and Motorola signed a launch services contract for multiple launch of Iridium communications satellites using CZ-2C/SD launch vehicles. The main differences between the CZ-2C and the CZ-2C/SD were: a modified fairing with a diameter of 3.35m; a newly developed Smart Dispenser; improved second stage fuel and oxidizer tanks; and second stage engines with higher expansion ratio nozzles. 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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