Encyclopedia Astronautica
UR-500MK-2


Lox/Kerosene propellant rocket stage. Loaded/empty mass 161,000/11,000 kg. Thrust 1,860.00 kN. Vacuum specific impulse 346 seconds. Empty mass estimated based on overall vehicle mass fraction. Length estimated based on total mass.

Status: Design 1975.
Gross mass: 161,000 kg (354,000 lb).
Unfuelled mass: 11,000 kg (24,000 lb).
Height: 20.00 m (65.00 ft).
Diameter: 4.15 m (13.61 ft).
Span: 4.15 m (13.61 ft).
Thrust: 1,860.00 kN (418,140 lbf).
Specific impulse: 346 s.
Specific impulse sea level: 246 s.
Burn time: 270 s.
Number: 1 .

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Associated Countries
Associated Engines
  • NK-43 Kuznetsov Lox/Kerosene rocket engine. 1755 kN. N-1F, Kistler stage 2. Design 1975. Isp=346s. Modified version of original engine with multiple ignition capability. Never flown and mothballed after the cancellation of the N1. Resurrected for Kistler. More...

Associated Launch Vehicles
  • UR-500MK Russian orbital launch vehicle. In 1975 Chelomei proposed this version of the Proton powered by lox/kerosene NK-33 engines developed for the cancelled N1 moon booster. This would give the Soviet Union an equivalent to the all-new Zenit-2 booster being developed by Glushko, but at a fraction of the time and expense through the use of existing components. The proposal had no chance politically, and was never seriously considered. More...

Associated Propellants
  • Lox/Kerosene 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. In January 1953 Rocketdyne commenced the REAP program to develop a number of improvements to the engines being developed for the Navaho and Atlas missiles. Among these was development of a special grade of kerosene suitable for rocket engines. Prior to that any number of rocket propellants derived from petroleum had been used. Goddard had begun with gasoline, and there were experimental engines powered by kerosene, diesel oil, paint thinner, or jet fuel kerosene JP-4 or JP-5. The wide variance in physical properties among fuels of the same class led to the identification of narrow-range petroleum fractions, embodied in 1954 in the standard US kerosene rocket fuel RP-1, covered by Military Specification MIL-R-25576. In Russia, similar specifications were developed for kerosene under the specifications T-1 and RG-1. The Russians also developed a compound of unknown formulation in the 1980's known as 'Sintin', or synthetic kerosene. More...

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