Saturn C-5

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Saturn C-5

Part of Saturn V

Saturn C-5 3 Stage
Saturn C-5 3 Stage version Nov 1961
Credit: © Mark Wade

American orbital launch vehicle. Final configuration of Saturn C-5 at the time of selection of this configuration for the Apollo program in December 1961. The actual Saturn V would be derived from this, but with an increased-diameter third stage (6.61 m vs 5.59 m in C-5) and increased propellant load in S-II second stage.

Status: Study 1961. Payload: 120,000 kg (260,000 lb). Thrust: 33,350.00 kN (7,497,370 lbf). Gross mass: 2,847,590 kg (6,277,860 lb). Height: 100.00 m (320.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).

LEO Payload: 120,000 kg (260,000 lb) to a 185 km orbit at 28.00 degrees. Payload: 41,000 kg (90,000 lb) to a translunar trajectory.

Stage Data - Saturn C-5

Stage 1. 1 x Saturn IC C-5A. Gross Mass: 2,217,285 kg (4,888,276 lb). Empty Mass: 131,495 kg (289,896 lb). Thrust (vac): 38,257.990 kN (8,600,738 lbf). Isp: 304 sec. Burn time: 160 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 42.87 m (140.64 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1. Status: Study 1961. Comments: Final first stage design of Saturn C-5 (November 1961) before selection as Apollo launch vehicle and development in Saturn V.

Stage 2. 1 x Saturn II C-5A. Gross Mass: 384,057 kg (846,700 lb). Empty Mass: 31,740 kg (69,970 lb). Thrust (vac): 4,446.648 kN (999,646 lbf). Isp: 420 sec. Burn time: 320 sec. Isp(sl): 200 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 21.39 m (70.17 ft). Propellants: Lox/LH2. No Engines: 5. Engine: J-2. Status: Study 1961. Comments: Final common second stage design for Saturn C-3, C-4 and C-5 (November 1961). Developed into Saturn V second stage.

Stage 3. 1 x Saturn IVB C-5A. Gross Mass: 102,249 kg (225,420 lb). Empty Mass: 11,563 kg (25,492 lb). Thrust (vac): 889.325 kN (199,928 lbf). Isp: 420 sec. Burn time: 415 sec. Isp(sl): 200 sec. Diameter: 5.59 m (18.33 ft). Span: 5.59 m (18.33 ft). Length: 19.00 m (62.00 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Study 1961. Comments: Final common third stage design for Saturn C-4 and C-5 (November 1961). Developed into Saturn V second stage. After development started, decision taken to boost performance by increasing diameter to 6.61 m and increasing propellant load.

Family: orbital launch vehicle. People: von Braun. Country: USA. Engines: F-1, J-2. Stages: Saturn IC C-5A, Saturn II C-5A, Saturn IVB C-5A.

Photo Gallery

1961 November 20 - . LV Family: Saturn V. Launch Vehicle: Saturn C-5.

Rosen Group recommends direct ascent for the lunar landing mission mode - . Nation: USA. Related Persons: Holmes, Brainard, Rosen, Milton. Program: Apollo. Milton W. Rosen, Director of Launch Vehicles and Propulsion, NASA Office of Manned Space Flight (OMSF), submitted to D. Brainerd Holmes, Director, OMSF, the report of the working group which had been set up on November 6.. Additional Details: here....

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