Encyclopedia Astronautica
RD-0210-HC


Kosberg Lox/Kerosene rocket engine. 592 kN. Design concept 1990's. Proposed variant of RD-0210 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=342s.

Engine: 570 kg (1,250 lb). Chamber Pressure: 147.00 bar. Thrust to Weight Ratio: 105.9. Oxidizer to Fuel Ratio: 2.6.

Status: Design concept 1990's.
Unfuelled mass: 570 kg (1,250 lb).
Thrust: 592.00 kN (133,086 lbf).
Specific impulse: 342 s.

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Associated Countries
See also
Associated Manufacturers and Agencies
  • Kosberg Russian manufacturer of rocket engines. Kosberg Design Bureau, Russia. 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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