Encyclopedia Astronautica
Saturn MS-II-1


Lox/LH2 propellant rocket stage. Loaded/empty mass 521,447/49,877 kg. Thrust 5,165.79 kN. Vacuum specific impulse 425 seconds. Basic Saturn II with 41 inch stretch of hydrogen tank.

No Engines: 5.

Status: Study 1965.
Gross mass: 521,447 kg (1,149,593 lb).
Unfuelled mass: 49,877 kg (109,959 lb).
Height: 25.88 m (84.90 ft).
Diameter: 10.06 m (33.00 ft).
Span: 10.06 m (33.00 ft).
Thrust: 5,165.79 kN (1,161,316 lbf).
Specific impulse: 425 s.
Specific impulse sea level: 306 s.
Burn time: 361 s.

More... - Chronology...


Associated Countries
Associated Engines
  • J-2 Rocketdyne lox/lh2 rocket engine. 1033.1 kN. Study 1961. Isp=421s. Used in Saturn IVB stage in Saturn IB and Saturn V, and Saturn II stage in Saturn V. Gas generator, pump-fed. First flight 1966. More...

Associated Launch Vehicles
  • 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-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...

Associated Propellants
  • Lox/LH2 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. Liquid hydrogen was identified by all the leading rocket visionaries as the theoretically ideal rocket fuel. It had big drawbacks, however - it was highly cryogenic, and it had a very low density, making for large tanks. The United States mastered hydrogen technology for the highly classified Lockheed CL-400 Suntan reconnaissance aircraft in the mid-1950's. The technology was transferred to the Centaur rocket stage program, and by the mid-1960's the United States was flying the Centaur and Saturn upper stages using the fuel. It was adopted for the core of the space shuttle, and Centaur stages still fly today. More...

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