Encyclopedia Astronautica
Saturn V-ELV


American orbital launch vehicle. NASA study, 1966. No-height-limitation stretched Saturn with Titan UA1207 motors for thrust augmentation.

LEO Payload: 200,000 kg (440,000 lb) to a 185 km orbit at 28.00 degrees. Payload: 67,000 kg (147,000 lb) to a translunar trajectory in 1985 dollars. Flyaway Unit Cost $: 97.440 million.

Stage Data - Saturn V-ELV

  • Stage 0. 4 x Titan UA1207. Gross Mass: 319,330 kg (704,000 lb). Empty Mass: 51,230 kg (112,940 lb). Thrust (vac): 7,116.999 kN (1,599,965 lbf). Isp: 272 sec. Burn time: 120 sec. Isp(sl): 245 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 34.14 m (112.00 ft). Propellants: Solid. No Engines: 1. Engine: UA1207. Status: In Production.
  • Stage 1. 1 x Saturn MS-IC-4(S)B. Gross Mass: 2,875,500 kg (6,339,300 lb). Empty Mass: 154,000 kg (339,000 lb). Thrust (vac): 38,717.600 kN (8,704,063 lbf). Isp: 304 sec. Burn time: 206 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 50.58 m (165.94 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1. Status: Study Boeing 1967. Comments: S-IC with 336 inch stretch, 6,000,0000 lbs propellant, structural strength increased from 56% to 65% depending on station, resulting in 13.9% increase in empty weight.
  • 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 1966.
Gross mass: 5,172,820 kg (11,404,110 lb).
Payload: 200,000 kg (440,000 lb).
Height: 124.00 m (406.00 ft).
Diameter: 10.06 m (33.00 ft).
Thrust: 59,392.70 kN (13,352,010 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • UA1207 CSD solid rocket engine. 7116.9 kN. Isp=272s. First flight 1989. 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-4(S)B Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,875,500/154,000 kg. Thrust 38,717.60 kN. Vacuum specific impulse 304 seconds. S-IC with 336 inch stretch, 6,000,0000 lbs propellant, structural strength increased from 56% to 65% depending on station, resulting in 13.9% increase in empty weight. More...
  • Titan UA1207 Solid propellant rocket stage. Loaded/empty mass 319,330/51,230 kg. Thrust 7,117.00 kN. Vacuum specific impulse 272 seconds. More...

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