Encyclopedia Astronautica

Lox/LH2 propellant rocket stage. Loaded/empty mass 10,500/2,000 kg. Thrust 44.10 kN. Vacuum specific impulse 425 seconds.

Cost $ : 4.000 million. No Engines: 4.

AKA: H-8.
Status: Active.
Gross mass: 10,500 kg (23,100 lb).
Unfuelled mass: 2,000 kg (4,400 lb).
Height: 7.48 m (24.54 ft).
Diameter: 2.25 m (7.38 ft).
Span: 2.25 m (7.38 ft).
Thrust: 44.10 kN (9,914 lbf).
Specific impulse: 425 s.
Burn time: 800 s.
Number: 13 .

More... - Chronology...

Associated Countries
Associated Engines
  • YF-73 Beijing Wan Yuan lox/lh2 rocket engine. 11 kN. In development. Gas-generator turbopump. Gimballed engine. Isp=425s. Used on CZ-3 launch vehicle. First flight 1984. More...

Associated Launch Vehicles
  • CZ-3 Chinese orbital launch vehicle. The Long March 3 was a three-stage launch vehicle designed for delivery of satellites of 1,500 kg mass into geosynchronous transfer orbit. The first and second stages were based on the CZ-2C, and designed and manufactured by the Shanghai Academy of Spaceflight Technology. The majority of the technology and flight hardware used in the CZ-3 had been qualified and proven on the CZ-2C. The third stage, manufactured by CALT, was equipped with an LOX/LH2 cryogenic engine. Long March 3 was also capable of placing spacecraft into an elliptical or circular low earth orbit and sun synchronous orbit. More...
  • CZ-NGLV-200 Chinese orbital launch vehicle. The Long March New Generation Launch Vehicle series small launcher would use the 2.25 m diameter module as the first stage and a single upper stage of the same diameter (probably the existing YF-73 stage of the CZ-3). Payload was given as 1.5 tonnes into low earth orbit. First launch was expected after 2008. Although the configuration was not shown at the Wuzhai Air Show in 2002 it re-emerged at the FAI in 2003. It seemed to be in competition with the all-solid-propellant KT-1, KT-2, and KT-2A series. 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...

Home - Browse - Contact
© / Conditions for Use