RD-0256 home
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Engine Model: RD-0256. Manufacturer Name: RD-0256. Designer: Kosberg. Developed in: 1983-89. Application: R-36M2 / RS-20V (SS-18 Mod-4) stage 2. Propellants: N2O4/UDMH. Chambers: 1. Country: Russia. Status: Out of Production. First Flight: 1987.

Main engine of system RD-0255. Staged combustion cycle.

Engine Model: RD-0256-HC. Manufacturer Name: RD-0256-HC. Designer: Kosberg. Developed in: 1996-. Propellants: Lox/Kerosene. Thrust(vac): 820.000 kN (184,340 lbf). Isp: 344 sec. Mass Engine: 770 kg (1,690 lb). Chambers: 1. Chamber Pressure: 172.00 bar. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 108.59. Country: Russia. Status: Design concept 1996-.

Proposed variant of RD-0256 engine using LOX-kerosene instead of N2O4/UDMH as propellants.

Engine Model: RD-0256-Methane. Manufacturer Name: RD-0256-Methan. Designer: Kosberg. Developed in: 1996-. Propellants: Lox/LCH4. Thrust(vac): 836.000 kN (187,940 lbf). Isp: 353 sec. Mass Engine: 770 kg (1,690 lb). Chambers: 1. Chamber Pressure: 176.00 bar. Oxidizer to Fuel Ratio: 3.40. Thrust to Weight Ratio: 110.71. Country: Russia. Status: Design concept 1996-.

Proposed variant of RD-0256 engine using LOX-liquid methane instead of N2O4/UDMH as propellants.

Bibliography:

  • Golubev, A A, KB KhimAvtomatiki - Straniy Istorii, Vol. 1, Voronezh 1995 via Dietrich Haeseler.
  • Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
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