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Engine Model: 11D49. Government Designation: 11D49. Other Designations: S5.23. Designer: Isayev. Developed in: 1960-64. Application: Kosmos-3M stage 2. Propellants: Nitric acid/UDMH. Thrust(vac): 157.500 kN (35,407 lbf). Isp: 303 sec. Burn time: 4,305 sec. Mass Engine: 185 kg (407 lb). Diameter: 1.92 m (6.29 ft). Length: 1.78 m (5.83 ft). Chambers: 1 + 4. Chamber Pressure: 98.10 bar. Area Ratio: 103.40. Oxidizer to Fuel Ratio: 2.65. Thrust to Weight Ratio: 86.81. Country: Russia. First Flight: 1964. Last Flight: 2005. Flown: 788.

Engine has one main and four steering nozzles. Thrust 157.5 + 4 x 25 kN. Precessor was 11D47 in R-14 (derivative ?) stage 2.

11D49 used on Rocket Stages
Bibliography:

  • Glushko, V P, Albom Konstruktsiy ZhRD, Vol. 1 1968, Vol. 3 & 4 1969 via Dietrich Haeseler.
  • Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
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