Credit: © Mark Wade
Credit: © Mark Wade
Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,286,217/135,218 kg. Thrust 38,703.16 kN. Vacuum specific impulse 304 seconds. Configuration as flown.
Cost $ : 391.500 million. No Engines: 5.
Gross mass: 2,286,217 kg (5,040,245 lb).
More... - Chronology...
Unfuelled mass: 135,218 kg (298,104 lb).
Height: 42.06 m (137.99 ft).
Diameter: 10.06 m (33.00 ft).
Span: 19.00 m (62.00 ft).
Thrust: 38,703.16 kN (8,700,816 lbf).
Specific impulse: 304 s.
Specific impulse sea level: 265 s.
Burn time: 161 s.
Number: 24 .
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 American orbital launch vehicle. America's booster for the Apollo manned lunar landing. The design was frozen before a landing mode was selected; the Saturn V could be used for either Earth-Orbit-Rendezvous or Lunar-Orbit-Rendezvous methods. The vehicle ended up with the same payload capability as the 'too large' Nova. The basic diameter was dictated by the ceiling height at the Michoud factory selected for first stage manufacture. More...
Saturn V 2 American orbital launch vehicle. Two stage version of Saturn V, consisting of 1 x Saturn S-IC + 1 x Saturn S-II, used to launch Skylab. More...
Saturn MLV-V-4(S) American orbital launch vehicle. MSFC study, 1965. Saturn V core, strengthened but not stretched, with 4 Titan UA1205 strap-on solid rocket boosters. More...
Saturn INT-20 American orbital launch vehicle. Saturn variant consisting of S-IC first stage and S-IVB second stage. Consideration was given to deleting one or more of the F-1 engines in the first stage. More...
Saturn INT-21 American orbital launch vehicle. Saturn variant consisting of S-IC first stage and S-II second stage. This essentially flew once to launch Skylab in 1972, although the IU was located atop the Skylab space station (converted S-IVB stage) rather than atop the S-II as in the INT-21 design. More...
Saturn V-A American orbital launch vehicle. MSFC study, 1968. Essentially identical to Saturn INT-20; standard Saturn IC stage together with Saturn IVB second stage, with Centaur third stage for deep space missions. More...
Saturn V-Centaur American orbital launch vehicle. MSFC study, 1968. S-ID stage-and-a-half first stage and Saturn IVB second stage. Centaur available as third stage for deep space missions. 30% performance improvement over Saturn V-A/Saturn INT-20 with standard Saturn IC first stage. More...
Saturn Shuttle American orbital launch vehicle. A winged recoverable Saturn IC stage was considered instead of solid rocket boosters after the final shuttle design was selected. 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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