Encyclopedia Astronautica
CZ-2C/SD-2


N2O4/UDMH propellant rocket stage. Loaded/empty mass 55,000/5,000 kg. Thrust 761.90 kN. Vacuum specific impulse 298 seconds. Stretched version of CZ-2C second stage. Empty mass estimated.

AKA: L-35.
Status: Development ended 1997.
Gross mass: 55,000 kg (121,000 lb).
Unfuelled mass: 5,000 kg (11,000 lb).
Height: 10.00 m (32.00 ft).
Diameter: 3.35 m (10.99 ft).
Span: 3.35 m (10.99 ft).
Thrust: 761.90 kN (171,282 lbf).
Specific impulse: 298 s.
Specific impulse sea level: 270 s.
Burn time: 190 s.
Number: 23 .

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-3B Chinese orbital launch vehicle. The Long March 3B was the most powerful Long March launch vehicle. It could inject a 5,000 kg payload into geosynchronous transfer orbit. The CZ-3B was developed on the basis of the CZ-3A, but had enlarged propellant tanks, larger fairing, and four boosters strapped onto the core stage. The CZ-3B boosters were identical to those of the CZ-3A. 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...
  • CZ-3C Chinese orbital launch vehicle. Launch vehicle combining CZ-3B core with two boosters from CZ-2E. The standard fairing was 9.56 m long, 4.0 m in diameter. On August 23, 2001, the CZ-3C launcher passed its critical design review. CZ-3C development had begun in 1995 but was suspended in 1996-2000 due to the 1996 CZ-3B failure. First launch was in 2008. 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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