Encyclopedia Astronautica
RD-0105



wrd0105.jpg
RD-0105
Credit: KBKhA
Kosberg Lox/Kerosene rocket engine. 49.4 kN. Luna 8K72, Vostok 8K72 upper stage. Out of production. Isp=316s. Developed jointly with OKB-1 in nine months on the basis of OKB-1'ssteering chamber from the RD-107 engine. First flight 1958.

Application: R-7 8K72 Luna stage 3 (block E-Luna).

Engine: 125 kg (275 lb). Chamber Pressure: 45.00 bar. Thrust to Weight Ratio: 40.

AKA: RO-5; RD-428; RD-0105; 8D714.
Status: Out of production.
Unfuelled mass: 125 kg (275 lb).
Diameter: 2.56 m (8.39 ft).
Thrust: 49.40 kN (11,106 lbf).
Specific impulse: 316 s.
Burn time: 440 s.
First Launch: 1957-59.
Number: 13 .

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • Luna 8K72 Russian orbital launch vehicle. R-7 ICBM with single-engine upper stage used for early Soviet unmanned lunar shots. More...
  • Vostok 8K72 Russian orbital launch vehicle. 8K72 Luna launch vehicle, third stage modified with larger forward cylindrical section to accomodate Vostok-sized spacecraft. Used only for launch of first few prototype Vostoks. 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...

Bibliography
  • Varfolomyev, Timothy, "Soviet Rocketry that Conquered Space - Part 2", Spaceflight, 1996, Volume 38, page 48.
  • Haeseler, Dietrich, Visit to the museum of Chemical Automatics Design Bureau, Voronezh 1992 via Dietrich Haeseler.
  • Siddiqi, Asif A, Soviet Space Web Page, 1999 via Dietrich Haeseler. Web Address when accessed: here.

Associated Stages
  • Luna 8K72-2 Lox/Kerosene propellant rocket stage. Loaded/empty mass 8,100/1,120 kg. Thrust 49.00 kN. Vacuum specific impulse 316 seconds. More...
  • Vostok 8K72-2 Lox/Kerosene propellant rocket stage. Loaded/empty mass 7,775/1,440 kg. Thrust 49.42 kN. Vacuum specific impulse 316 seconds. More...

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