Encyclopedia Astronautica

Glushko Lox/Kerosene rocket engine. 873 kN. Soyuz M stage 1, 2. Proposed for X-34. Isp=336s. Sea-level variant of RD-120. As of 1996 RD-120 prototype with 1.8 m diameter had been built, development time estimated for three years.

Thrust and Isp range due to throat diameter and chamber pressure. Gimbaling +/- 6 degree in two planes. Chamber pressure 163 - 172 bar.

Application: Soyuz M stage 1, 2. Proposed for X-34..


Throttled thrust(vac): 794.000 kN (178,498 lbf). Thrust (sl): 866.900 kN (194,887 lbf). Thrust (sl): 88,396 kgf. Engine: 1,433 kg (3,159 lb). Chamber Pressure: 172.00 bar. Thrust to Weight Ratio: 62.1. Oxidizer to Fuel Ratio: 2.6.

AKA: RD-123; RD-120K.
Status: Design 1994.
Unfuelled mass: 1,433 kg (3,159 lb).
Height: 2.80 m (9.10 ft).
Diameter: 1.50 m (4.90 ft).
Thrust: 873.00 kN (196,258 lbf).
Specific impulse: 336 s.
Specific impulse sea level: 298 s.
Burn time: 305 s.

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...

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...

Associated Stages
  • Kvant Lox/Kerosene propellant rocket stage. Loaded/empty mass 210,000/15,000 kg. Thrust 3,216.00 kN. Vacuum specific impulse 336 seconds. 4 11D121 verniers. Empty mass estimated. More...
  • Kvant-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 74,000/7,000 kg. Thrust 1,102.20 kN. Vacuum specific impulse 335 seconds. 4 RD-0124-14D23 verniers. Empty mass estimated. More...
  • Soyuz M-0 Lox/Kerosene propellant rocket stage. Loaded/empty mass 42,200/3,000 kg. Thrust 872.00 kN. Vacuum specific impulse 336 seconds. More...
  • Soyuz M-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 100,500/6,000 kg. Thrust 872.00 kN. Vacuum specific impulse 336 seconds. Proposed improved version. Not developed. More...

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