Encyclopedia Astronautica
Saturn MS-IC-4(S)B

Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,875,500/154,000 kg. Thrust 38,717.60 kN. Vacuum specific impulse 304 seconds. S-IC with 336 inch stretch, 6,000,0000 lbs propellant, structural strength increased from 56% to 65% depending on station, resulting in 13.9% increase in empty weight.

No Engines: 5.

Status: Study 1966.
Gross mass: 2,875,500 kg (6,339,300 lb).
Unfuelled mass: 154,000 kg (339,000 lb).
Height: 50.58 m (165.94 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: 206 s.

More... - Chronology...

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 MLV-V-4(S)-A American orbital launch vehicle. MSFC study, 1965. 4 Titan UA1205 solid rocket boosters; Saturn IC stretched 337 inches with 6.0 million pounds propellant and 5 F-1 engines; S-II with 970,000 pounds propellant and 5 J-2 engines; S-IVB strengthened but with standard 230,000 lbs propellant, 1 J-2 engine. More...
  • Saturn V-ELV American orbital launch vehicle. NASA study, 1966. No-height-limitation stretched Saturn with Titan UA1207 motors for thrust augmentation. 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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