Encyclopedia Astronautica
Saturn IC C-4B

Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,450,984/90,686 kg. Thrust 30,606.40 kN. Vacuum specific impulse 304 seconds. Final first stage design of Saturn C-3 (November 1961). Unique S-IC design in that fuel and propellant tank shared common bulkhead; stage was actually shorter than C-3B S-IC.

No Engines: 5.

Status: Study 1961.
Gross mass: 1,450,984 kg (3,198,872 lb).
Unfuelled mass: 90,686 kg (199,928 lb).
Height: 33.46 m (109.77 ft).
Diameter: 10.06 m (33.00 ft).
Span: 19.00 m (62.00 ft).
Thrust: 30,606.40 kN (6,880,592 lbf).
Specific impulse: 304 s.
Specific impulse sea level: 265 s.
Burn time: 130 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 C-4B American orbital launch vehicle. Final configurtion of the Saturn C-4 at the time of selection of the Saturn C-5 configuration for the Apollo program in December 1961. Only Saturn configuration with common bulkhead propellant tanks in first stage, resulting in shorter vehicle than less powerful Saturn C-3. 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...

Home - Browse - Contact
© / Conditions for Use