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.
|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.|