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RD-54
Lyulka LOx/LH2 rocket engine. N1 concept stage III. Developed 1960-75.

AKA: 11D54; D-54. Status: Developed 1960-75. Date: 1960-75. Thrust: 392.00 kN (88,125 lbf). Specific impulse: 440 s. Burn time: 360 s.

Subtopics

RD-57 Lyulka LOx/LH2 rocket engine. N1 Block S (N-1M). Study 1965. One to have been used in N1 Block S. In fixed chamber version, 3 to 6 to have been used in N1 Block V-III. Engine system includes roll control thruster with 1.29 kN thrust.

RD-57M Lyulka LOx/LH2 rocket engine. Vulkan Blok V. Development ended 1976. Version with extendible nozzle. Length 4.06 / 2.61 m. Specific impulse 461 / 448 sec. Area ratio 170 / 87.6.

RD-57A-1 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.

Country: Russia. Launch Vehicles: N1, N1 1969. Propellants: Lox/LH2. Stages: N1 Block V. Agency: Lyulka bureau. Bibliography: 177, 307, 320, 95.

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