Encyclopedia Astronautica

Credit: KBKhA
Kosberg Lox/Kerosene rocket engine. 294.3 kN. In development. Isp=359s. Engine to succeed RD-0110 in second stage of Soyuz. Used staged combustion; chamber pressure increased from 70 to 160 bar, specific impulse from 326 to 359 seconds First flight 2001.

Payload increase by 950 kg from current 6900 / 7200 kg from Plesetsk / Baikonur.

Application: Rus Soyuz 2 stage 3.


Chambers: 4. Engine: 480 kg (1,050 lb). Chamber Pressure: 162.00 bar. Propellant Formulation: Lox/RG-1. Thrust to Weight Ratio: 62.5. Oxidizer to Fuel Ratio: 2.6.

AKA: 14D23; RD-0124; 14D451M.
Status: In development.
Unfuelled mass: 480 kg (1,050 lb).
Height: 1.58 m (5.17 ft).
Diameter: 2.40 m (7.80 ft).
Thrust: 294.30 kN (66,161 lbf).
Specific impulse: 359 s.
Specific impulse sea level: 331 s.
Burn time: 300 s.
First Launch: 1993-.
Number: 19 .

More... - Chronology...

Associated Countries
See also
Associated Launch Vehicles
  • Soyuz M Rus project was to result in first major propulsion upgrade to R-7 family in forty years, using first stage engines derived from those developed for Zenit second stage to boost performance. It would have permitted launches from Plesetsk with same or greater payload than launch of standard Soyuz-U from Baikonur, permitting move of more launch operations back onto Russian territory. Instead the more modest Soyuz ST / Soyuz FG upgrades were made. More...
  • Soyuz ST Uprated Soyuz booster designed for commercial customers. Upgraded engines, modern digital avionics, reduced non-Russian content. Can be used with either Ikar or Fregat upper stages. The 'FG' was the military version. More...

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...

  • Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.
  • "Podprobnosti o RN 'Rus'", Novosti Kosmonavtiki, 1996, Issue 6, page 20.
  • Haeseler, Dietrich, CADB-information leaflets, International Aerospace Show Berlin 1998 (ILA 98) via Dietrich Haeseler.

Associated Stages
  • Angara A-2 Lox/Kerosene propellant rocket stage. Loaded/empty mass 25,200/2,355 kg. Thrust 294.00 kN. Vacuum specific impulse 359 seconds. Two thrust levels. Propellant ration 2.6:1, chamber pressure 162 bar. More...
  • Soyuz ST-2 Lox/Kerosene propellant rocket stage. Loaded/empty mass 25,200/2,355 kg. Thrust 294.00 kN. Vacuum specific impulse 359 seconds. More...

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