Encyclopedia Astronautica
CZ-2E-2


N2O4/UDMH propellant rocket stage. Loaded/empty mass 91,500/5,500 kg. Thrust 831.01 kN. Vacuum specific impulse 298 seconds.

Cost $ : 3.000 million.

AKA: L-90.
Status: Active.
Gross mass: 91,500 kg (201,700 lb).
Unfuelled mass: 5,500 kg (12,100 lb).
Height: 15.52 m (50.91 ft).
Diameter: 3.35 m (10.99 ft).
Span: 3.35 m (10.99 ft).
Thrust: 831.01 kN (186,817 lbf).
Specific impulse: 298 s.
Specific impulse sea level: 260 s.
Burn time: 295 s.
Number: 19 .

More... - Chronology...


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-2E Chinese orbital launch vehicle. The CZ-2E added four liquid rocket booster strap-ons to the basic CZ-2 core to achieve a low earth orbit payload capability approaching the Russian Proton, US Titan, or European Ariane rockets. The Long March 2E had a maximum payload capability of 9,500 kg to low earth orbit. More...
  • CZ-2F Chinese orbital launch vehicle. Man-rated version of CZ-2E, designed for launch of the Shenzhou spacecraft. Little difference externally. Modifications were related to improved redundancy of systems, strengthened upper stage to handle large 921-1 spacecraft fairing and launch escape tower. President Jiang Zemin gave the name 'Shenjian' ('Divine Arrow') to the CZ-2F after the successful launch of the Shenzhou-3 mission. More...
  • CZ-2E(A) Planned upgrade of CZ-2E with enlarged liquid boosters. Probably intended for launch of Chinese space station modules in the 21st century. Fairing was 5.20 m in diameter and 12.39 m long. 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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