Encyclopedia Astronautica
CZ H-18


Lox/LH2 propellant rocket stage. Loaded/empty mass 21,000/2,800 kg. Thrust 156.00 kN. Vacuum specific impulse 440 seconds.

Cost $ : 16.000 million. No Engines: 2.

AKA: H-18.
Status: Development ended 1997.
Gross mass: 21,000 kg (46,000 lb).
Unfuelled mass: 2,800 kg (6,100 lb).
Height: 12.38 m (40.60 ft).
Diameter: 3.00 m (9.80 ft).
Span: 3.00 m (9.80 ft).
Thrust: 156.00 kN (35,070 lbf).
Specific impulse: 440 s.
Burn time: 470 s.
Number: 25 .

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Associated Countries
Associated Engines
  • YF-75 Beijing Wan Yuan lox/lh2 rocket engine. 78.5 kN. In development. Gas-generator turbopump. Gimballed engine. Isp=440s. First flight 1994. More...

Associated Launch Vehicles
  • CZ-3A Chinese three-stage orbital launch vehicle. The Long March 3A, by incorporating the mature technologies of the CZ-3 and adding a more powerful cryogenic third stage and more capable control system, had a greater geosynchronous transfer orbit capability, greater flexibility for attitude control, and better adaptability to a variety of launch missions. More...
  • 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-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
  • Lox/LH2 Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Liquid hydrogen was identified by all the leading rocket visionaries as the theoretically ideal rocket fuel. It had big drawbacks, however - it was highly cryogenic, and it had a very low density, making for large tanks. The United States mastered hydrogen technology for the highly classified Lockheed CL-400 Suntan reconnaissance aircraft in the mid-1950's. The technology was transferred to the Centaur rocket stage program, and by the mid-1960's the United States was flying the Centaur and Saturn upper stages using the fuel. It was adopted for the core of the space shuttle, and Centaur stages still fly today. More...

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