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RD-57A-1
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Manufacturer Name: RD-57A-1. Designer: Lyulka. Developed in: 1995-98. Propellants: Lox/LH2. Thrust(vac): 395.000 kN (88,799 lbf). Isp: 460 sec. Mass Engine: 550 kg (1,210 lb). Diameter: 1.85 m (6.06 ft). Length: 3.15 m (10.33 ft). Chambers: 1. Area Ratio: 143.00. Oxidizer to Fuel Ratio: 5.80. Thrust to Weight Ratio: 73.23. Country: Russia. Status: Developed 1995-98. New version of RD-57M for SSTO-demonstrator proposed by Aerojet. Optimized nozzle contour for performance increase, new chamber material for weight reduction. First launch was planned for 3rd quarter 1998 in 1994, but not performed until 1999.
Bibliography and Further Reading - Andreeyev, Chepkin, Fanciullo, AIAA Joint Prop. Conf., June 1994, "The Development of the D-57 Advanced Staged Combustion Engine for Upper stages", AIAA-94, AIAA Joint Prop. Conf., June 1994 via Dietrich Haeseler.
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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