Encyclopedia Astronautica

Lox/Kerosene propellant rocket stage. Loaded/empty mass 60,000/7,000 kg. Thrust 588.00 kN. Vacuum specific impulse 340 seconds. Upper stage for the 3.35 m diameter core vehicle. Only information available are the types of propellants, total thrust, and number of engines. Therefore all values shown here except thrust are estimated. This launcher has a low priority since its payload capability overlaps existing Chinese launch vehicles, and it would not be developed until after 2010.

No Engines: 4.

Status: In development.
Gross mass: 60,000 kg (132,000 lb).
Unfuelled mass: 7,000 kg (15,400 lb).
Height: 13.00 m (42.00 ft).
Diameter: 3.35 m (10.99 ft).
Span: 3.35 m (10.99 ft).
Thrust: 588.00 kN (132,187 lbf).
Specific impulse: 340 s.
Burn time: 300 s.
Number: 1 .

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Associated Countries
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...

Associated Propellants
  • Lox/Kerosene 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. In January 1953 Rocketdyne commenced the REAP program to develop a number of improvements to the engines being developed for the Navaho and Atlas missiles. Among these was development of a special grade of kerosene suitable for rocket engines. Prior to that any number of rocket propellants derived from petroleum had been used. Goddard had begun with gasoline, and there were experimental engines powered by kerosene, diesel oil, paint thinner, or jet fuel kerosene JP-4 or JP-5. The wide variance in physical properties among fuels of the same class led to the identification of narrow-range petroleum fractions, embodied in 1954 in the standard US kerosene rocket fuel RP-1, covered by Military Specification MIL-R-25576. In Russia, similar specifications were developed for kerosene under the specifications T-1 and RG-1. The Russians also developed a compound of unknown formulation in the 1980's known as 'Sintin', or synthetic kerosene. More...

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