Encyclopedia Astronautica
Saturn C-4



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Saturn C-4
Credit: © Mark Wade
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Saturn A-1 to C-5
Credit: © Mark Wade
American orbital launch vehicle. The launch vehicle actually planned for the Lunar Orbit Rendezvous approach to lunar landing. The Saturn C-5 was selected instead to have reserve capacity.

LEO Payload: 99,000 kg (218,000 lb) to a 185 km orbit at 28.00 degrees. Payload: 32,000 kg (70,000 lb) to a translunar trajectory in 1985 dollars. Flyaway Unit Cost $: 58.290 million.

Stage Data - Saturn C-4

  • Stage 1. 1 x Saturn S-IB-4. Gross Mass: 1,813,729 kg (3,998,587 lb). Empty Mass: 108,823 kg (239,913 lb). Thrust (vac): 30,962.526 kN (6,960,653 lbf). Isp: 304 sec. Burn time: 155 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 11.28 m (37.00 ft). Length: 28.96 m (95.01 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: F-1. Status: Study 1960.
  • Stage 2. 1 x Saturn S-II-4. Gross Mass: 294,731 kg (649,770 lb). Empty Mass: 24,938 kg (54,978 lb). Thrust (vac): 3,557.313 kN (799,716 lbf). Isp: 420 sec. Burn time: 296 sec. Isp(sl): 300 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 16.76 m (54.98 ft). Propellants: Lox/LH2. No Engines: 4. Engine: J-2. Status: Study 1960.
  • Stage 3. 1 x Saturn IVB. Gross Mass: 119,920 kg (264,370 lb). Empty Mass: 13,311 kg (29,345 lb). Thrust (vac): 1,031.983 kN (231,999 lbf). Isp: 425 sec. Burn time: 475 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 17.80 m (58.30 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Out of Production.

Status: Study 1960.
Gross mass: 2,347,180 kg (5,174,640 lb).
Payload: 99,000 kg (218,000 lb).
Height: 76.00 m (249.00 ft).
Diameter: 10.06 m (33.00 ft).
Thrust: 26,990.40 kN (6,067,683 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...
  • 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...

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 IVB Lox/LH2 propellant rocket stage. Loaded/empty mass 119,920/13,311 kg. Thrust 1,031.98 kN. Vacuum specific impulse 425 seconds. Configuration as flown on Saturn V. More...
  • Saturn S-IB-4 Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,813,729/108,823 kg. Thrust 30,962.53 kN. Vacuum specific impulse 304 seconds. More...
  • Saturn S-II-4 Lox/LH2 propellant rocket stage. Loaded/empty mass 294,731/24,938 kg. Thrust 3,557.31 kN. Vacuum specific impulse 420 seconds. Version for Saturn C-4. More...

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