Encyclopedia Astronautica

Kosberg Lox/Kerosene rocket engine. 298.640 kN. Propoed in 1993 for Angara stage 2 verniers, Kvant-1 stage 1 vernier. Designed 1986-1990. Isp=331s. Variant of RD-0124 with shortened nozzle for sea-level operation.

Proposed for small launcher Kvant-1 by RKK Energia for stage 1 steering engine. Also proposed by RKK Energia in initial studies in 1993 for Angara upper stage.

Application: Angara stage 2 verniers. Kvant-1 stage 1 vernier.


Chambers: 4. Chamber Pressure: 173.50 bar. Oxidizer to Fuel Ratio: 2.6.

AKA: 14D23.
Status: Designed 1986-1990.
Thrust: 298.64 kN (67,137 lbf).
Specific impulse: 331 s.
Burn time: 300 s.

More... - Chronology...

Associated Countries
See also
Associated Launch Vehicles
  • Kvant-1 Russian orbital launch vehicle. From 1996-2001 RSC Energia carried out design studies on the Kvant-1 light launch vehicle with a low earth orbit payload capability of 1.8 to 3.0 metric tons. Market surveys seemed to indicate a need for a new launch vehicle of this class but development funding was not forthcoming. 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...

  • Semenov, Yuri P Editor, Raketno-kosmicheskaya korporatsiya 'Energia' imeni S P Koroleva, Moscow, Russia, 1996.
  • Haeseler, Dietrich, CADB-information leaflets, International Aerospace Show Berlin 1998 (ILA 98) via Dietrich Haeseler.

Associated Stages
  • 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...

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