Lox/LH2 propellant rocket stage. Loaded/empty mass 26,000/3,100 kg. Thrust 156.00 kN. Vacuum specific impulse 448 seconds. The upper stage for the Chinese Next Generation Launch Vehicle is a modification of the CZ-3B upper stage. The stage uses a version of the Lox/LH2 YF-75 engine, simplified for improved reliability. The stage is of hammerhead form, with the upper LH2 tank with a diameter of 5 m, and the lower liquid oxygen tank with a diameter of 3.35 m. The total propellant is 22,900 kg with a burn time of over 600 seconds. Empty mass has not yet been released and is estimated.
No Engines: 2.
Status: In development.
More... - Chronology...
Gross mass: 26,000 kg (57,000 lb).
Unfuelled mass: 3,100 kg (6,800 lb).
Height: 12.00 m (39.00 ft).
Diameter: 3.35 m (10.99 ft).
Span: 5.00 m (16.40 ft).
Thrust: 156.00 kN (35,070 lbf).
Specific impulse: 448 s.
Burn time: 600 s.
Number: 1 .
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-NGLV-320 Chinese orbital launch vehicle. The Long March New Generation Launch Vehicle series medium launcher would use the 3.35 m diameter module and a new 3.35 m diameter second stage as the core vehicle. Either two or four 2.25 m diameter modules would be used as strap-ons. Payload to low earth orbit would be three tonnes with two strap-ons and 10 tonnes with four strap-ons. More...
CZ-NGLV-522/HO Chinese orbital launch vehicle. The 522/HO was the 'all up' baseline configuration for the Long March New Generation Launch Vehicle series. It would use the 5.0 m core stage, topped by the 5.0 m upper stage, together with 2 x 2.25 m plus 2 x 3.35 m strap-on stages. It was announced in 2003 that it would be first to fly, with a launch before the Beijing Olympics in 2008. It would be used for launch of large communications satellites. Payload is estimated as 10-12 tonnes to geosynchronous transfer orbit. More...
CZ-NGLV-540/HO Chinese orbital launch vehicle. The 540/HO configuration for the Long March New Generation Launch Vehicle series would use the 5.0 m core stage, topped by the 5.0 m upper stage, together with 4 x 2.25 m strap-on stages. First flight of this version was expected after 2010. Payload was given as 6 tonnes to geosynchronous transfer orbit. More...
CZ-NGLV-504/HO Chinese orbital launch vehicle. The 504/HO configuration for the Long March New Generation Launch Vehicle series would use the 5.0 m core stage, topped by the 5.0 m upper stage, together with 4 x 3.35 m strap-on stages. First flight of this version was expected after 2010. Payload was given as 14 tonnes to geosynchronous transfer orbit. More...
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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