RD-0234 home
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Engine Model: RD-0234. Manufacturer Name: RD-0234. Designer: Kosberg. Developed in: 1969-74. Application: UR-100N / RS-18 (SS-19) stage 1. Propellants: N2O4/UDMH. Thrust(vac): 520.000 kN (116,900 lbf). Isp: 310 sec. Isp (sea level): 285 sec. Burn time: 121 sec. Chambers: 1. Chamber Pressure: 205.00 bar. Country: Russia. Status: Out of Production. First Flight: 1974.

Staged combustion cycle. Modification of RD-0233 including tank pressurization system.

Engine Model: RD-0234-CH. Manufacturer Name: RD-0234-CH. Designer: Kosberg. Developed in: 1996-. Propellants: Lox/LCH4. Thrust(vac): 442.000 kN (99,365 lbf). Isp: 343 sec. Isp (sea level): 310 sec. Mass Engine: 390 kg (850 lb). Chambers: 1. Chamber Pressure: 176.00 bar. Oxidizer to Fuel Ratio: 3.40. Thrust to Weight Ratio: 115.38. Country: Russia. Status: Developed 1996-.

Proposed variant of RD-0234 engine using LOX-liquid methane instead of N2O4/UDMH as propellants.

Engine Model: RD-0234-HC. Manufacturer Name: RD-0234-HC. Designer: Kosberg. Developed in: 1996-. Propellants: Lox/Kerosene. Thrust(vac): 516.000 kN (116,001 lbf). Isp: 331 sec. Isp (sea level): 310 sec. Mass Engine: 390 kg (850 lb). Chambers: 1. Chamber Pressure: 196.00 bar. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 134.91. Country: Russia. Status: Developed 1996-.

Proposed variant of RD-0234 engine using LOX-kerosene instead of N2O4/UDMH as propellants.

Bibliography:

  • Pavutniskiy, Yu M; Mazarchenko, V A; Shilenkov, M V; Gerasimov, A B, Otechestvennye Rakety-Nos 1 and 2, St.Peterburg (State Marine-Technol. Univ.), 1996 via Dietrich Haeseler.
  • 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.
  • ROCKOT Users Guide, Issue 2, Rev. 0, Eurockot Launch Services, Bremen 1998. via Dietrich Haeseler.
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