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RD-0244
Credit - KBKhA
Engine Model: RD-0244. Manufacturer Name: RD-0244. Designer: Kosberg. Developed in: 1977-85. Application: R-29RM / RSM-54 (SS-N-23) stage 1. Propellants: N2O4/UDMH. Thrust(vac): 682.000 kN (153,319 lbf). Isp: 310 sec. Isp (sea level): 280 sec. Burn time: 74 sec. Chambers: 1. Chamber Pressure: 275.00 bar. Area Ratio: 2.00. Oxidizer to Fuel Ratio: 2.60. Country: Russia. Status: Out of Production. First Flight: 1985.

Main engine in system RD-0243. Staged combustion cycle. Submerged in propellant tank.

Engine Model: RD-0244-HC. Manufacturer Name: RD-0244-HC. Other Designations: RD-0244 KD. Designer: Kosberg. Propellants: Lox/Kerosene. Thrust(vac): 690.000 kN (155,110 lbf). Isp: 332 sec. Mass Engine: 540 kg (1,190 lb). Chambers: 1. Chamber Pressure: 230.00 bar. Oxidizer to Fuel Ratio: 2.70. Thrust to Weight Ratio: 130.29. Country: Russia. Status: Design concept 1990's.

Proposed variant of RD-0244 engine using LOX-kerosene instead of N2O4/UDMH as propellants.

RD-0244 used on Rocket Stages
Bibliography:

  • Vick, Charles, et al, KH-11 Photography of N1, Federation of American Scientists, 1995-present. Web Address when accessed: http://www.fas.org/.
  • Golubev, A A, KB KhimAvtomatiki - Straniy Istorii, Vol. 1, Voronezh 1995 via Dietrich Haeseler.
  • Haeseler, Dietrich, CADB-information leaflets, International Aerospace Show Berlin 1998 (ILA 98) via Dietrich Haeseler.
  • Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
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