Encyclopedia Astronautica
Saturn MLV-V-1A


American orbital launch vehicle. MSFC study, 1965. Saturn IC stretched 240 inches with 5.6 million pounds propellant and 6 F-1 engines; S-II stretched 156 inches with 1.2 million pounds propellant and 7 J-2 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2 engine.

LEO Payload: 145,000 kg (319,000 lb) to a 185 km orbit at 28.00 degrees. Payload: 54,400 kg (119,900 lb) to a translunar trajectory.

Stage Data - Saturn MLV-V-1A

  • Stage 1. 1 x Saturn MS-IC-1A. Gross Mass: 2,694,700 kg (5,940,700 lb). Empty Mass: 160,600 kg (354,000 lb). Thrust (vac): 46,443.300 kN (10,440,869 lbf). Isp: 304 sec. Burn time: 160 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.01 m (62.36 ft). Length: 48.16 m (158.00 ft). Propellants: Lox/Kerosene. No Engines: 6. Engine: F-1. Status: Study 1966. Comments: Basic Saturn IC stretched 240 inches with 6 F-1 engines.
  • Stage 2. 1 x Saturn MS-II-1A. Gross Mass: 600,800 kg (1,324,500 lb). Empty Mass: 60,000 kg (132,000 lb). Thrust (vac): 6,380.941 kN (1,434,493 lbf). Isp: 421 sec. Burn time: 345 sec. Isp(sl): 200 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 29.59 m (97.08 ft). Propellants: Lox/LH2. No Engines: 7. Engine: J-2. Status: Study NASA 1966. Comments: Basic Saturn II with 187 inch stretch of propellant tanks, 1.2 million pound propellant capacity, and 7 J-2 engines.
  • Stage 3. 1 x Saturn MS-IVB-1A. Gross Mass: 179,200 kg (395,000 lb). Empty Mass: 20,400 kg (44,900 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 625 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 22.82 m (74.86 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Study Boeing 1967. Comments: S-IVB with 16.5 foot stretch, 350,000 pounds propellant, standard J-2 engine.

Status: Study 1965.
Gross mass: 3,648,700 kg (8,044,000 lb).
Payload: 145,000 kg (319,000 lb).
Height: 121.00 m (396.00 ft).
Diameter: 10.06 m (33.00 ft).
Thrust: 40,485.10 kN (9,101,413 lbf).
Apogee: 185 km (114 mi).

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...

See also
  • Saturn V 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. Despite the study of innumerable variants, production was ended after only 12 were built and America spent the next fifty years in a pointless slow-motion withdrawal from manned space exploration. More...
  • Saturn The Saturn launch vehicle was the penultimate expression of the Peenemuende Rocket Team's designs for manned exploration of the moon and Mars. Numerous designs and variants were studied, but in the end only three models - the Saturn I, IB, and V - were built in the 1960's, and then only used to support NASA's Apollo moon landing program. More...

Associated Manufacturers and Agencies
  • Von Braun American manufacturer of rockets and spacecraft. Von Braun, USA. More...

Associated Stages
  • Saturn MS-II-1A Lox/LH2 propellant rocket stage. Loaded/empty mass 600,800/60,000 kg. Thrust 6,380.94 kN. Vacuum specific impulse 421 seconds. Basic Saturn II with 187 inch stretch of propellant tanks, 1.2 million pound propellant capacity, and 7 J-2 engines. More...
  • Saturn MS-IVB-1A Lox/LH2 propellant rocket stage. Loaded/empty mass 179,200/20,400 kg. Thrust 1,031.60 kN. Vacuum specific impulse 421 seconds. S-IVB with 16.5 foot stretch, 350,000 pounds propellant, standard J-2 engine. More...
  • Saturn MS-IC-1A Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,694,700/160,600 kg. Thrust 46,443.30 kN. Vacuum specific impulse 304 seconds. Basic Saturn IC stretched 240 inches with 6 F-1 engines. More...

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