This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Other Designations: RD-226 ?. Designer: Glushko. Developed in: 1960-62. Application: R-26 stage 2. Used on stages: R-26 Stage 2. Used on launch vehicles: R-26. Propellants: Nitric acid/UDMH Thrust(vac): 47,723 kgf. Thrust(vac): 468.00 kN. Isp: 307 sec. Burn time: 160 sec. Diameter: 1.4 m. Length: 2.2 m. Chambers: 1. Chamber Pressure: 83.60 bar. Area Ratio: 48.40. Oxidizer to Fuel Ratio: 2.76. Country: Russia. Status: Out of Production. References: 193 , 194 , 320 . Comments: Orevo has sectioned hardware. This is only the thrust chamber, probably based on RD-224 chamber. Other components like turbopumps, etc. were obviously the same as RD-224. Mass chamber only 198 kg.
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Last update 12 March 2001.
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