Encyclopedia Astronautica
RLA-300


Glushko Lox/Kerosene rocket engine. 3187 kN. Design 1974. Proposed for the RLA series launch vehicles and the UR-700M Mars booster. Following rejection of RLA, design 'down-sized' to 200 tonnes thrust for Energia and Zenit.

In 1972 to 1974 Glushko proposed lox/kerosene engines for the RLA series launch vehicles and the UR-700M Mars booster with a lift-off thrust of 300 tonnes per chamber. The UR-700M version would use two chambers for a total thrust of 600 tonnes. Following rejection of the RLA and the adoption of the Energia design, this chamber design was 'down-sized' to 200 tonnes thrust for Energia and Vulkan.

Status: Design 1974.
Thrust: 3,187.00 kN (716,466 lbf).
First Launch: 1972-1975.

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • UR-700M Russian heavy-lift orbital launch vehicle. In 1969 the Soviet Union began project Aelita, studying the best method to beat the Americans in landing a man on Mars. Chelomei's team reached the conclusion that a Mars expedition would best be launched by an immense vehicle would allow their MK-700 Mars spacecraft to be orbited in two launches. The proposed UR-700M launch vehicle had a gross lift-off mass of 16,000 metric tons and could deliver 750 metric tons to orbit. By 1972 the Nixon administration had cancelled NASA's plans for manned Mars missions. Perhaps not coincidentally, a Soviet expert commission the same year concluded that the Mars project - and the UR-700M booster - were beyond the technical and economical capabilities of the Soviet Union and should be shelved indefinitely. More...

Associated Manufacturers and Agencies
  • Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. 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...

Bibliography
  • Yeteyev, Ivan, Operezhaya vremya, Ocherki, Moscow, 1999..

Associated Stages
  • RLA-2 Lox/Kerosene propellant rocket stage. Loaded/empty mass 150,000/10,000 kg. Thrust 2,940.00 kN. Vacuum specific impulse 349 seconds. Empty mass, specific impulses, length estimated by comparison to smaller Zenit successor design. More...
  • UR-700M-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 8,000,000/750,000 kg. Thrust 204,027.00 kN. Vacuum specific impulse 337 seconds. Total mass, length, estimated based on empty mass, total vehicle mass. Engine specific impulse estimated based on follow-on RD-170 engines. More...
  • UR-700M-2 Lox/Kerosene propellant rocket stage. Loaded/empty mass 5,250,000/500,000 kg. Thrust 102,013.60 kN. Vacuum specific impulse 337 seconds. Total mass, length, estimated based on empty mass, total vehicle mass. Engine specific impulse estimated based on follow-on RD-170 engines. More...

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