Encyclopedia Astronautica
CZ-4A-2


N2O4/UDMH propellant rocket stage. Loaded/empty mass 39,550/4,000 kg. Thrust 831.01 kN. Vacuum specific impulse 295 seconds.

Cost $ : 3.000 million.

AKA: L-35.
Status: Active.
Gross mass: 39,550 kg (87,190 lb).
Unfuelled mass: 4,000 kg (8,800 lb).
Height: 10.41 m (34.15 ft).
Diameter: 3.35 m (10.99 ft).
Span: 3.35 m (10.99 ft).
Thrust: 831.01 kN (186,817 lbf).
Specific impulse: 295 s.
Specific impulse sea level: 260 s.
Burn time: 135 s.
Number: 13 .

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-4A Chinese orbital launch vehicle. The CZ-4 was developed and manufactured by the Shanghai Academy of Spaceflight Technology. Its first stage was essentially the same as that of the CZ-3 and the second stage was identical to that of the CZ-3. The CZ-4's third stage, however, was a development, featuring a thin wall common intertank bulkhead tankage and two-engine cluster with both engines gimbling about two perpendicular axes. The third stage engine cluster connected to the tank aft bulkhead through the engine bay. The CZ-4 had two payload fairing configurations: Type-A and Type-B. The CZ-4 was designed for launching satellites into polar and sun-synchronous orbits. More...
  • CZ-2D Chinese orbital launch vehicle. The Long March 2D was a two-stage launch vehicle with storable propellants, suitable for launching a variety of low earth orbit satellites. Developed and manufactured by the Shanghai Academy of Spaceflight Technology, the CZ-2D had a typical payload capability of 3,500kg in a 200 km circular orbit. Its first stage was identical to that of the CZ-4. The second stage was essentially the same as that of the CZ-4, except for an improved vehicle equipment bay. 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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