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RD-0210
Credit - KBKhA
Engine Model: RD-0210. Manufacturer Name: RD-0210. Government Designation: 8D411K. Other Designations: RD-465, 8D49. Designer: Kosberg. Developed in: 1962-65. Application: Proton stage 2. Propellants: N2O4/UDMH. Thrust(vac): 582.100 kN (130,861 lbf). Isp: 327 sec. Burn time: 230 sec. Mass Engine: 566 kg (1,247 lb). Diameter: 1.47 m (4.82 ft). Length: 2.33 m (7.64 ft). Chambers: 1. Chamber Pressure: 147.00 bar. Area Ratio: 81.30. Thrust to Weight Ratio: 104.87. Country: Russia. First Flight: 1965. Last Flight: 2006. Flown: 1,240.

Cluster of four similar engines used in second stage of Proton - one providing tank pressurization (8D412K/RD-0211) and three (8D411K/RD-0210). Staged combustion cycle (Oxidizer pre-burner gas routed to main chamber after driving turbine).

Engine Model: RD-0210-HC. Manufacturer Name: RD-0210-HC. Designer: Kosberg. Propellants: Lox/Kerosene. Thrust(vac): 592.000 kN (133,086 lbf). Isp: 342 sec. Mass Engine: 570 kg (1,250 lb). Chambers: 1. Chamber Pressure: 147.00 bar. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 105.90. Country: Russia. Status: Design concept 1990's.

Proposed variant of RD-0210 engine using LOX-kerosene instead of N2O4/UDMH as propellants.

RD-0210 used on Rocket Stages
Bibliography:

  • Burya article, Lavochkin web site.
  • Haeseler, Dietrich, Visit to the museum of Chemical Automatics Design Bureau, Voronezh 1992 via Dietrich Haeseler.
  • Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
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