RD-0245

RD-0245

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Engine Model: RD-0245. Manufacturer Name: RD-0245. Designer: Kosberg. Developed in: 1977-85. Application: R-29RM / RSM-54 (SS-N-23) stage 1 vernier. Propellants: N2O4/UDMH. Thrust(vac): 211.000 kN (47,434 lbf). Isp: 300 sec. Isp (sea level): 280 sec. Burn time: 79 sec. Chambers: 4. Chamber Pressure: 147.00 bar. Area Ratio: 14.00. Oxidizer to Fuel Ratio: 2.60. Country: Russia. Status: Out of Production. First Flight: 1985.

Four-chamber steering engine in system RD-0243 driven by turbine exhaust gas.

Engine Model: RD-0245-HC. Manufacturer Name: RD-0245-HC. Designer: Kosberg. Propellants: Lox/Kerosene. Thrust(vac): 214.000 kN (48,109 lbf). Isp: 320 sec. Mass Engine: 290 kg (630 lb). Chambers: 4. Chamber Pressure: 142.00 bar. Oxidizer to Fuel Ratio: 2.30. Thrust to Weight Ratio: 75.24. Country: Russia. Status: Design concept 1990's.

Proposed variant of RD-0245 engine using LOX-kerosene instead of N2O4/UDMH as propellants.

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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