Encyclopedia Astronautica
YF-50t



yf50t.jpg
YF-50t
New 50 tonne Lox/LH2 engine
Credit: © Mark Wade
CAALPT lox/lh2 rocket engine. 700 kN. In development. Isp=432s. New Lox/LH2 engine for next generation Chinese launch vehicles. It is an indigenous development based on Chinese experience with the YF-73 and YF-75 upper stage engines.

Gimballed in two axes, hydrogen bled from the engine is used to pressurise the oxygen tank, and helium isused to pressurise the hydrogen tank. Firing tests began in 2003 and were to be completed by early 2006. First launch expected in 2008.

Thrust (sl): 540.000 kN (121,390 lbf). Thrust (sl): 55,000 kgf. Oxidizer to Fuel Ratio: 5.45.

Status: In development.
Thrust: 700.00 kN (157,360 lbf).
Specific impulse: 432 s.
Specific impulse sea level: 333 s.
First Launch: 1999-2006.

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • CZ-NGLV-540 Chinese orbital launch vehicle. The 540 configuration for the Long March New Generation Launch Vehicle series would use the 5.0 m diameter core stage with four 2.25 m diameter stages as strap-ons. Payload was given as 10 tonnes to low earth orbit. A standard short 5.2 m diameter fairing tops the vehicle. More...
  • CZ-NGLV-522 Chinese orbital launch vehicle. The 522 configuration for the Long March New Generation Launch Vehicle series would use the 5.0 m diameter core stage with 2 x 2.25 m plus 2 x 3.35 m strap-on stages. Payload is estimated as 18-20 tonnes to low earth orbit. 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-504 The 504 configuration for the Long March New Generation Launch Vehicle series would use the 5.0 m diameter core stage with four 3.35 m diameter stages as strap-ons. Payload was given as 25 tonnes to low earth orbit. A standard large 5.2 m diameter fairing tops the vehicle. It would be used to launch the Chinese Space Laboratory in 2010. 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...

Associated Manufacturers and Agencies
  • CAALPT Chinese manufacturer of rocket engines. China Academy of Aerospace Liquid Propulsion Technology, Xian, China. 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...

Associated Stages
  • CZ-NGLV-500 Lox/LH2 propellant rocket stage. Loaded/empty mass 175,000/17,000 kg. Thrust 1,399.99 kN. Vacuum specific impulse 432 seconds. From top to bottom the 5-m Chinese new generation launch vehicle consists of a 117.3 cubic meter liquid oxygen tank, an intertank section, a 350.7 cubic meter liquid hydrogen tank, and an engine section with two gimballed LOX /LH2 engines of 660 kN vacuum thrust each. The hydrogen tank is pressurised using hydrogen bled from the engine and helium is used to pressurise the oxygen tank. More...

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