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RD-161P
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Manufacturer Name: RD-161P. Designer: Glushko. Developed in: 1993-. Application: Soyuz M stage 3 (block LM). Propellants: H2O2/Kerosene. Thrust(vac): 24.500 kN (5,508 lbf). Throttled thrust(vac): 14.700 kN (3,305 lbf). Isp: 319 sec. Burn time: 900 sec. Mass Engine: 105 kg (231 lb). Diameter: 1.24 m (4.06 ft). Length: 1.45 m (4.75 ft). Chambers: 1. Chamber Pressure: 117.70 bar. Area Ratio: 265.00. Oxidizer to Fuel Ratio: 5.90. Thrust to Weight Ratio: 23.79. Country: Russia. Status: Developed 1993-. Two thrust levels. Minimum 1500 kgf. Proposed for use on Soyuz M-3. Version for H2O2 fuel, concentration 96-98%.
Bibliography and Further Reading - Haeseler, Dietrich, NPO Energomash exhibit at Moscow Airshow MAKS 93, Moscow, 1993 via Dietrich Haeseler.
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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