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RD-0110 Engine
Credit - © Mark Wade
Engine Model: RD-0110. Manufacturer Name: RD-0110. Government Designation: 11D55. Other Designations: RD-461. Designer: Kosberg. Developed in: 1964-69. Application: Soyuz 11A511, Molniya-M 8K78M. Propellants: Lox/Kerosene. Thrust(vac): 297.900 kN (66,971 lbf). Isp: 326 sec. Burn time: 250 sec. Mass Engine: 408 kg (899 lb). Diameter: 2.24 m (7.34 ft). Length: 1.58 m (5.18 ft). Chambers: 4. Chamber Pressure: 68.20 bar. Area Ratio: 82.20. Oxidizer to Fuel Ratio: 2.20. Thrust to Weight Ratio: 74.46. Country: Russia. First Flight: 1964. Last Flight: 2006. Flown: 1,136.

Precursor RD-0107 used in 11A57 Voskhod stage 2. Modified to increase reliability.

Engine Model: RD-0110MD. Manufacturer Name: RD-0110MD. Designer: Kosberg. Developed in: 1994-. Propellants: Lox/LNG. Thrust(vac): 245.000 kN (55,078 lbf). Burn time: 20 sec. Chambers: 4. Chamber Pressure: 54.00 bar. Area Ratio: 82.20. Country: Russia. Status: Developed 1994-on.

Prototype engine for tests with propellants LOX/liquified natural gas. Tests performed from 30 April 1998 on, test duration 20s.

RD-0110 used on Rocket Stages
Bibliography:

  • Burya article, Lavochkin web site.
  • Varfolomyev, Timothy, Spaceflight, "Soviet Rocketry that Conquered Space - 8K71 launches", 1996, Volume 38, page 31.
  • Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.
  • Novosti Kosmonavtiki, "Podprobnosti o RN 'Rus'", 1996, Issue 6, page 20.
  • Haeseler, Dietrich, Visit to the museum of Chemical Automatics Design Bureau, Voronezh 1992 via Dietrich Haeseler.
  • Glushko, V P, Albom Konstruktsiy ZhRD, Vol. 1 1968, Vol. 3 & 4 1969 via Dietrich Haeseler.
  • Novosti kosmonavtiki, Issue 3, 1999.
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© Mark Wade, 1997 - 2008 except where otherwise noted.