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RD-0120TD
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Manufacturer Name: RD-0120TD. Designer: Kosberg. Application: experimental tri-propellant. Propellants: Lox/Kerosene/LH2. Thrust(vac): 1,317.000 kN (296,073 lbf). Throttled thrust(vac): 775.000 kN (174,226 lbf). Isp: 419 sec. Isp (sea level): 295 sec. Diameter: 2.42 m (7.93 ft). Length: 4.55 m (14.92 ft). Chambers: 1. Area Ratio: 85.70. Oxidizer to Fuel Ratio: 4.13. Country: Russia. Status: Developed 1990's. Experimental tri-propellant (dual-fuel) variant using the RD-0120 engine. Realized by supply of high-pressure kerosene from test bench or adapted existing kerosene pump for tests. Specific impulse 419 / 452 sec.
Bibliography and Further Reading - Gontcharov, Orlov, Rachuk, Rudis, Shostak, McIllwain, Starke, Hulka, ONERA, "Tripropellant Liquid Rocket Engine Technology Using a Fuel-Rich Closed Power Cycle", June 1995 via Dietrich Haeseler.
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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