Encyclopedia Astronautica

Lyulka lox/lh2 rocket engine. 395 kN. Developed 1995-98. Isp=460s. 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.

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

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

More... - Chronology...

Associated Countries
See also
Associated Manufacturers and Agencies
  • Lyulka Russian manufacturer of rocket engines. Lyulka Design Bureau, Russia. More...

Associated Propellants
  • Lox/LH2 Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Liquid hydrogen was identified by all the leading rocket visionaries as the theoretically ideal rocket fuel. It had big drawbacks, however - it was highly cryogenic, and it had a very low density, making for large tanks. The United States mastered hydrogen technology for the highly classified Lockheed CL-400 Suntan reconnaissance aircraft in the mid-1950's. The technology was transferred to the Centaur rocket stage program, and by the mid-1960's the United States was flying the Centaur and Saturn upper stages using the fuel. It was adopted for the core of the space shuttle, and Centaur stages still fly today. More...

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