Encyclopedia Astronautica
Saturn MS-IC/260


Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,721,600/181,400 kg. Thrust 38,717.60 kN. Vacuum specific impulse 304 seconds. Standard length S-IC but with feed of propellant from fuel and propellant tanks housed above strap-on solid rocket motors

No Engines: 5.

Status: Study 1967.
Gross mass: 2,721,600 kg (6,000,100 lb).
Unfuelled mass: 181,400 kg (399,900 lb).
Height: 42.05 m (137.95 ft).
Diameter: 10.06 m (33.00 ft).
Span: 19.00 m (62.00 ft).
Thrust: 38,717.60 kN (8,704,063 lbf).
Specific impulse: 304 s.
Specific impulse sea level: 265 s.
Burn time: 192 s.

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Associated Countries
Associated Engines
  • F-1 Rocketdyne Lox/Kerosene rocket engine. 7740.5 kN. Isp=304s. Largest liquid rocket engine ever developed and flown. Severe combustion stability problems were solved during development and it never failed in flight. First flight 1967. More...

Associated Launch Vehicles
  • Saturn V/4-260 American orbital launch vehicle. Boeing study, 1967-1968. Use of full length 260 inch solid rocket boosters with stretched Saturn IC stages presented problems, since the top of the motors came about half way up the liquid oxygen tank of the stage, making transmission of loads from the motors to the core vehicle complex and adding a great deal of weight to the S-IC. Boeing's solution was to retain the standard length Saturn IC, with the 260 inch motors ending half way up the S-IC/S-II interstage, but to provide additional propellant for the S-IC by putting propellant tanks above the 260 inch boosters. These would be drained first and jettisoned with the boosters. This added to the plumbing complexity but solved the loads problem. 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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