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RD-57A-1
Part of RD-54 Family
Lyulka LOx/LH2 rocket engine. 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.

Status: Developed 1995-98. Date: 1995-98. Thrust: 395.00 kN (88,799 lbf). Unfuelled mass: 550 kg (1,210 lb). Specific impulse: 460 s. Height: 3.15 m (10.33 ft). Diameter: 1.85 m (6.06 ft).

First launch was planned for 3rd quarter 1998 in 1994, but not performed until 1999.

Engine: 550 kg (1,210 lb). Area Ratio: 143. Thrust to Weight Ratio: 73.23. Oxidizer to Fuel Ratio: 5.8.



Country: Russia. Propellants: Lox/LH2. Agency: Lyulka bureau.

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