Lox/LH2 propellant rocket stage. Loaded/empty mass 142,000/15,000 kg. Thrust 411.00 kN. Vacuum specific impulse 460 seconds. Upper stage design by KB Saturn for manned lunar expedition, large geosynchronous platform launch.
Status: Development ended 1976.
Gross mass: 142,000 kg (313,000 lb).
Unfuelled mass: 15,000 kg (33,000 lb).
Height: 16.50 m (54.10 ft).
Diameter: 6.70 m (21.90 ft).
Span: 6.70 m (21.90 ft).
Thrust: 411.00 kN (92,396 lbf).
Specific impulse: 460 s.
Burn time: 1,370 s.
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Associated Countries
Associated Engines
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RD-57M Lyulka lox/lh2 rocket engine. 397 kN. Vulkan Blok V. Development ended 1976. Isp=461s. Version with extendible nozzle. Length 4.06 / 2.61 m. Specific impulse 461 / 448 sec. Area ratio 170 / 87.6. More...
Associated Launch Vehicles
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Vulkan Super heavy-lift version of Energia with six strap-on boosters, and in-line upper stages and payloads. The concept was put on the back burner when Energia / Buran development begun. More...
Associated Propellants
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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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