Lox/Kerosene propellant rocket stage. Loaded/empty mass 355,000/35,000 kg. Thrust 7,906.10 kN. Vacuum specific impulse 337 seconds. Essentially identical to Zenit stage 1.
Cost $ : 40.000 million.
Status: Retired 1988.
More... - Chronology...
Gross mass: 355,000 kg (782,000 lb).
Unfuelled mass: 35,000 kg (77,000 lb).
Height: 37.70 m (123.60 ft).
Diameter: 3.90 m (12.70 ft).
Span: 4.20 m (13.70 ft).
Thrust: 7,906.10 kN (1,777,362 lbf).
Specific impulse: 337 s.
Specific impulse sea level: 309 s.
Burn time: 145 s.
Number: 12 .
RD-170 Glushko Lox/Kerosene rocket engine. 7903 kN. Energia strap-on. Developed 1973-1985. Isp=337s. First flight 1987. Used one-plane gimablling versus the two-plane gimablling required on the RD-171 of the Zenit launch vehicle. Designed for 10 reuses. More...
Associated Launch Vehicles
Energia The Energia-Buran Reusable Space System (MKS) began development in 1976 as a Soviet booster that would exceed the capabilities of the US shuttle system. Following extended development, Energia made two successful flights in 1987-1988. But the Soviet Union was crumbling, and the ambitious plans to build an orbiting defense shield, to renew the ozone layer, dispose of nuclear waste, illuminate polar cities, colonize the moon and Mars, were not to be. Funding dried up and the Energia-Buran program completely disappeared from the government's budget after 1993. More...
Energia/Buran Design version of Energia, with the reusable Buran manned spaceplane mounted to the side of the core. More...
Energia M Launch vehicle originally designed in the 1980's to fullfill the third generation 20-30 tonnes to orbit launcher requirement. It was an adaptation of the Energia launch vehicle, using two strap-on booster units instead of four, and a reduced-diameter core using a single RD-0120 engine instead of four. In the 1990's a structural test article was built and it was proposed that several Energia-M's be launched for commercial customers using surplus Energia components. No buyers came forward for the untested design. More...
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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