Encyclopedia Astronautica

Glushko Lox/Kerosene rocket engine. 2079 kN. Isp=337s. Proposed for stage 1 of Angara. Single chamber from 4-chamber RD-170 would have been cheap and fast to develop. Only reached the draft project stage by 2003. Gimbaling +/- 8 degree in two planes.

Application: Angara stage 1.

Engine: 3,230 kg (7,120 lb). Chamber Pressure: 257.00 bar. Area Ratio: 37. Thrust to Weight Ratio: 64.56. Oxidizer to Fuel Ratio: 2.6.

AKA: RD-191M; RD-191.
Status: In development.
Unfuelled mass: 3,230 kg (7,120 lb).
Height: 4.05 m (13.28 ft).
Diameter: 2.00 m (6.50 ft).
Thrust: 2,079.00 kN (467,377 lbf).
Specific impulse: 337 s.
Specific impulse sea level: 311 s.
Burn time: 150 s.
First Launch: 1996-.
Number: 132 .

More... - Chronology...

Associated Countries
See also
Associated Launch Vehicles
  • Angara The Angara was a new all-Russian heavy launch vehicle designed to replace the Zenit (which was built by a Ukrainian company) and Proton (which had launch pads only on Kazakh territory). The booster was sized for rail transport of modular manufactured components to cosmodromes at Plesetsk and Svobodniy. The design featured a single modular core that could be clustered for large payloads or used as a first stage with a variety of existing upper stages. All plans for the Angara were dependent on financing and subject to constant change. More...

Associated Manufacturers and Agencies
  • Glushko Russian manufacturer of rocket engines and rockets. Glushko 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...

  • Salmon, Andrew, The Story Of Russian Rocket Engines - Energomash Museum, Commentary by the guide at the Energomash rocket engine museum in Khimki, April 1998 at YSC98..
  • Klepikov, Katorgin, Chvanov, "The New Generation of Rocket Engines, Operating by Ecologically Safe Propellant ...", IAF-Congress Turin, 1997, IAF-97-S.1.03 via Dietrich Haeseler.
  • Novosti kosmonavtiki, Issues. 21-22, 1998 via Dietrich Haeseler.

Associated Stages
  • Angara UM Lox/Kerosene propellant rocket stage. Loaded/empty mass 140,000/10,000 kg. Thrust 2,094.70 kN. Vacuum specific impulse 337.5 seconds. Can be throttled to 95%. Propellant ration 2.6:1, chamber pressure 257 bar. More...

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