Korean Lox/Kerosene rocket engine. In development. Launch thrust 122.5 kN. Pressure-fed indigenous design. First flight 2002.
Thrust (sl): 122.500 kN (27,539 lbf). Thrust (sl): 12,500 kgf.
Status: In development.
More... - Chronology...
Thrust: 122.50 kN (27,539 lbf).
Burn time: 53 s.
Number: 1 .
Korea South South Korea became familiar with large-scale rocketry through maintenance and modification activities on American-supplied Honest John and Nike Hercules tactical missiles. By the 1990's Korea had developed an independent capability to manufacture solid propellant rocket motors of up to one tonne mass. In 1990 KARI was funded to build the first indigenous sounding rockets, flown as the KSR-I and KSR-II. In December 1997 KARI was allowed to proceed with development of liquid oxygen/kerosene rocket motor for an orbital launcher, but this was abandoned when the South Korean government decided it wanted to be among the top ten spacefaring nations by 2015. The existing program was too limited in growth potential to allow that. Therefore it was decided to leapfrog the technology by contracting with Russian companies. First launch of the KSLV-I launch vehicle from the new space centre took place in 2010. 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...
KSR-3 Lox/Kerosene propellant rocket stage. Loaded/empty mass 5,000/700 kg. Thrust 122.50 kN. Vacuum specific impulse 280 seconds. All values except thrust estimated. More...
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