Encyclopedia Astronautica
Saturn MLV-V-2



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Saturn V-MLV-2
Credit: © Mark Wade
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.

LEO Payload: 137,250 kg (302,580 lb) to a 185 km orbit at 28.00 degrees. Payload: 53,550 kg (118,050 lb) to a translunar trajectory.

Stage Data - Saturn MLV-V-2

  • Stage 1. 1 x Saturn MS-IC-1. Gross Mass: 2,694,703 kg (5,940,803 lb). Empty Mass: 169,719 kg (374,166 lb). Thrust (vac): 45,948.754 kN (10,329,691 lbf). Isp: 310 sec. Burn time: 158 sec. Isp(sl): 270 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 48.15 m (157.97 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1A. Status: Study NASA 1966. Comments: Basic Saturn IC stretched 240 inches with F-1A engines uprated 20% in thrust and 6 second improvement in specific impulse.
  • Stage 2. 1 x Saturn MS-II-1. Gross Mass: 521,447 kg (1,149,593 lb). Empty Mass: 49,877 kg (109,959 lb). Thrust (vac): 5,165.790 kN (1,161,316 lbf). Isp: 425 sec. Burn time: 361 sec. Isp(sl): 306 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 25.88 m (84.90 ft). Propellants: Lox/LH2. No Engines: 5. Engine: J-2. Status: Study NASA 1966. Comments: Basic Saturn II with 41 inch stretch of hydrogen tank.
  • Stage 3. 1 x Saturn MS-IVB-2. Gross Mass: 176,600 kg (389,300 lb). Empty Mass: 17,800 kg (39,200 lb). Thrust (vac): 1,401.300 kN (315,025 lbf). Isp: 447 sec. Burn time: 489 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 23.12 m (75.85 ft). Propellants: Lox/LH2. No Engines: 1. Engine: HG-3. Status: Study 1965. Comments: Douglas Studies, 1965: S-IVB with 315 k high pressure 3000 psia engine, 350,000 pounds propellant.

Status: Study 1965.
Gross mass: 3,557,450 kg (7,842,830 lb).
Payload: 137,250 kg (302,580 lb).
Height: 117.00 m (383.00 ft).
Diameter: 10.06 m (33.00 ft).
Thrust: 40,019.90 kN (8,996,831 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • F-1A Rocketdyne Lox/Kerosene rocket engine. 9189.6 kN. Study 1968. Designed for booster applications. Gas generator, pump-fed. Isp=310s. More...
  • HG-3 Rocketdyne lox/lh2 rocket engine. 1400.7 kN. Study 1967. Isp=451s. High-performance high-pressure chamber engine developed from J-2. Considered for upgrades to Saturn V launch vehicle upper stages. Technology led to Space Shuttle Main Engines. More...

See also
  • 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...
  • 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...

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

Associated Stages
  • 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...
  • Saturn MS-IVB-2 Lox/LH2 propellant rocket stage. Loaded/empty mass 176,600/17,800 kg. Thrust 1,401.30 kN. Vacuum specific impulse 447 seconds. Douglas Studies, 1965: S-IVB with 315 k high pressure 3000 psia engine, 350,000 pounds propellant More...
  • 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. More...

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