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Saturn C-4
Part of Saturn V Family
Saturn C-4
Saturn C-4
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.

Status: Study 1960. Payload: 99,000 kg (218,000 lb). Thrust: 26,990.40 kN (6,067,683 lbf). Gross mass: 2,347,180 kg (5,174,640 lb). Height: 76.00 m (249.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).

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. Flyaway Unit Cost 1985$: 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.

Family: orbital launch vehicle. People: von Braun. Country: USA. Engines: F-1, J-2. Stages: Saturn IVB, Saturn S-IB-4, Saturn S-II-4. More at: 8588.


Photo Gallery

Saturn A-1 to C-5Saturn A-1 to C-5
Credit: © Mark Wade



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