RD-216 home
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Engine Model: RD-216. Manufacturer Name: RD-216. Government Designation: 11D614. Designer: Glushko. Developed in: 1958-60. Application: R-14, Kosmos 11K63 stage 1. Propellants: Nitric acid/UDMH. Thrust(vac): 1,728.000 kN (388,469 lbf). Thrust(sl): 1,469.200 kN (330,289 lbf). Isp: 291 sec. Isp (sea level): 248 sec. Burn time: 146 sec. Mass Engine: 1,350 kg (2,970 lb). Diameter: 2.26 m (7.41 ft). Length: 2.20 m (7.20 ft). Chambers: 4. Chamber Pressure: 73.60 bar. Area Ratio: 18.80. Oxidizer to Fuel Ratio: 2.50. Thrust to Weight Ratio: 131.40. Country: Russia. First Flight: 1964. Last Flight: 2005. Flown: 788.

RD-216 is a block of 2 RD-215's. The RD-216 had 2 combustion chambers and 2 turbines. Two sets of these were used in the first stage of the R-14 missile and Kosmos 11K63 series launch vehicles. Beginning with this engine Glushko cut the previous 3 to 5 year development time for new engines to 2 years. Diameter is per chamber.

Engine Model: RD-216M. Manufacturer Name: RD-216M. Designer: Glushko. Developed in: 1960s. Application: Kosmos-3M stage I. Propellants: Nitric acid/UDMH. Chambers: 4. Country: Russia. Status: Out of Production.

RD-216 used on Rocket Stages
Bibliography:

  • Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.
  • Salmon, Andrew, The Story Of Russian Rocket Engines - Energomash Museum, Commentary by the guide at the Energomash rocket engine museum in Khimki, April 1998 at YSC98..
  • Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition).
  • Haeseler, Dietrich, Information from NPO Energomash museum exhibit, Nov. 1992 via Dietrich Haeseler.
  • Glushko, V P, Albom Konstruktsiy ZhRD, Vol. 1 1968, Vol. 3 & 4 1969 via Dietrich Haeseler.
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