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.
Ref. Lyulka 94 has higher mass at 911 kg and higher fixed nozzle area ratio at 100.
Application: Vulkan Blok V.
Throttled thrust(vac): 303.000 kN (68,117 lbf). Engine: 874 kg (1,926 lb). Chamber Pressure: 115.00 bar. Area Ratio: 170. Thrust to Weight Ratio: 46.31. Oxidizer to Fuel Ratio: 6.2.
More... - Chronology...
Status: Development ended 1976.
Unfuelled mass: 874 kg (1,926 lb).
Height: 4.06 m (13.32 ft).
Diameter: 2.00 m (6.50 ft).
Thrust: 397.00 kN (89,249 lbf).
Specific impulse: 461 s.
First Launch: 1960-74.
Associated Launch Vehicles
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 Manufacturers and Agencies
Lyulka Russian manufacturer of rocket engines. Lyulka Design Bureau, Russia. More...
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...
Vulkan Blok V 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. More...
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