Encyclopedia Astronautica
F-1A



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F-1A
Credit: Boeing / Rocketdyne
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Advanced Engines
Advanced Engines planned for uprated Saturn and Nova boosters
Credit: © Mark Wade
Rocketdyne Lox/Kerosene rocket engine. 9189.6 kN. Study 1968. Designed for booster applications. Gas generator, pump-fed. Isp=310s.

Thrust (sl): 8,003.800 kN (1,799,326 lbf). Thrust (sl): 816,178 kgf. Engine: 8,098 kg (17,853 lb). Chamber Pressure: 70.00 bar. Area Ratio: 16. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 115.71.

Status: Study 1968.
Unfuelled mass: 8,098 kg (17,853 lb).
Height: 5.48 m (17.97 ft).
Diameter: 3.61 m (11.84 ft).
Thrust: 9,189.60 kN (2,065,904 lbf).
Specific impulse: 310 s.
Specific impulse sea level: 270 s.
Burn time: 158 s.
First Launch: 1967.

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • Nova GD-B American heavy-lift orbital launch vehicle. General Dynamics Nova design using existing engines. Recoverable engine package; separation at 3,398 m/s at 76,200 m altitude; splashdown using retrorockets under 7 30 m diameter parachutes 1300 km downrange. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions. More...
  • Nova MM 1B American heavy-lift orbital launch vehicle. Nova design using existing engines; 14 F-1A in the first stage, 2 M-1 in the second. Operational date would have been December 1972 More...
  • Nova MM 1C American heavy-lift orbital launch vehicle. Nova design using existing engines; 18 F-1A in the first stage, 3 M-1 in the second. Operational date would have been February 1973 More...
  • Saturn MLV-V-1 American orbital launch vehicle. MSFC study, 1965. Improved Saturn V configuration studied under contract NAS8-11359. Saturn IC stretched 240 inches with 5.6 million pounds propellant and 5 F-1A engines; S-II stretched 41 inches with 1.0 million pounds propellant and 5 J-2 engines; S-IVB strengthened but with standard 230,000 lbs propellant, 1 J-2 engine. More...
  • Saturn MLV-V-2 American orbital launch vehicle. MSFC study, 1965. Saturn IC stretched 240 inches with 5.6 million pounds propellant and 5 F-1A engines; S-II stretched 41 inches with 1.0 million pounds propellant and 5 J-2 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 HG-3 engine. More...
  • Saturn MLV-V-3 American orbital launch vehicle. MSFC study, 1965. Ultimate core for improved Saturn V configurations studied under contract NAS8-11359. Saturn IC stretched 240 inches with 5.6 million pounds propellant and 5 F-1A engines; S-II stretched 156 inches with 1.2 million pounds propellant and 5 HG-3 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 HG-3 engine. More...
  • Saturn MLV-V-1/J-2T/200K American orbital launch vehicle. MSFC study, 1965. Improved Saturn V configuration studied under contract NAS8-11359. Variant of MLV-V-1 with toroidal J-2T-200K engines replacing standard J-2 engines in upper stages. More...
  • Saturn MLV-V-1/J-2T/250K American orbital launch vehicle. MSFC study, 1965. Improved Saturn V configuration studied under contract NAS8-11359. Variant of MLV-V-1 with toroidal J-2T-250K engines replacing standard J-2 engines in upper stages. More...
  • Saturn V-24(L) American orbital launch vehicle. Boeing study, 1967. 4 260 inch liquid propellant boosters (each with 2 F-1A).; Saturn IC stretched 336 inches with 6.0 million pounds propellant and 5 F-1A engines; S-II stretched 156 inches with 1.2 million pounds propellant and 5 HG-3 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 HG-3 engine. Not studied in detail since vehicle height of 600 feet with payload exceeded study limit of 410 feet. More...
  • Saturn V-3B American orbital launch vehicle. Boeing study, 1967. Variation on MSFC 1965 study Saturn MLV-V-3 but with toroidal engines. Saturn IC stretched 240 inches with 5.6 million pounds propellant (but only 4.99 million pounds usable without solid rocket boosters) and 5 F-1A engines; S-II stretched 186 inches with 1.29 million lbs propellant and 5 J-2T-400 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2T-400 engine. More...
  • Saturn MLV-V-4(S)-B American orbital launch vehicle. Boeing study, 1967. Configuration of improved Saturn 5 with Titan UA1207 120 inch solid rocket boosters. Saturn IC stretched 336 inches with 6.0 million pounds propellant and 5 F-1 engines; Saturn II and Saturn IVB stages strengthened but not stretched. Empty mass of stages increased by 13.9% (S-IC), 8.6% (S-II) and 11.8% (S-IVB). Studied again by Boeing in 1967 as Saturn V-4(S)B. More...
  • Saturn V-25(S)B American orbital launch vehicle. Boeing study, 1967. 4 156 inch solid propellant boosters; Saturn IC stretched 498 inches with 6.64 million pounds propellant and 5 F-1 engines; S-II standard length with 5 J-2 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2 engine. More...
  • Saturn V-4X(U) American orbital launch vehicle. Boeing study, 1968. Four core vehicles from Saturn V-25(S) study lashed together to obtain million-pound payload using existing hardware. First stage consisted of 4 Saturn IC's stretched 498 inches with 6.64 million pounds propellant and 5 F-1 engines; second stage 4 Saturn II standard length stages with 5 J-2 engines More...
  • Saturn V-25(S)U American orbital launch vehicle. Boeing study, 1968. 4 156 inch solid propellant boosters; Saturn IC stretched 498 inches with 6.64 million pounds propellant and 5 F-1 engines; S-II standard length with 5 J-2 engines. This vehicle would place Nerva nuclear third stage into low earth orbit, where five such stages would be assembled together with the spacecraft for a manned Mars expedition. More...

Associated Manufacturers and Agencies
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...

Associated Stages
  • Nova GD-B-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 9,070,000/635,000 kg. Thrust 142,451.00 kN. Vacuum specific impulse 310 seconds. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions. Recoverable engine package; separation at 3,398 m/s at 76,200 m altitude; splashdown using retrorockets under 7 30 m diameter parachutes 1300 km downrange. More...
  • Nova MM 1B-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 7,430,000/454,000 kg. Thrust 125,770.00 kN. Vacuum specific impulse 304 seconds. Operational date would have been December 1972 More...
  • Nova MM 1C-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 8,943,000/590,000 kg. Thrust 161,710.00 kN. Vacuum specific impulse 304 seconds. Operational date would have been February 1973 More...
  • Saturn MS-IC-3B Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,718,800/178,700 kg. Thrust 45,925.50 kN. Vacuum specific impulse 304 seconds. S-IC with 20 foot stretch, 1.8 million lb thrust F-1's, 5.6 million pounds propellant capacity (fuel offloaded to 4.99 million for LEO or 4.80 million lbs for LOR mission). More...
  • Saturn MS-IC-25(S) Lox/Kerosene propellant rocket stage. Loaded/empty mass 3,223,800/211,900 kg. Thrust 45,925.50 kN. Vacuum specific impulse 304 seconds. S-IC with 41.5 foot stretch, 6,640,0000 lbs propellant, uprated F-1 engines. More...
  • Saturn MS-IC-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,694,703/169,719 kg. Thrust 45,948.75 kN. Vacuum specific impulse 310 seconds. Basic Saturn IC stretched 240 inches with F-1A engines uprated 20% in thrust and 6 second improvement in specific impulse. More...

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