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Orbital launch vehicle. Year: 1961. Family: Saturn C. Country: USA. Status: Study 1961. Final configurtion of the Saturn C-4 at the time of selection of the Saturn C-5 configuration for the Apollo program in December 1961. Only Saturn configuration with common bulkhead propellant tanks in first stage, resulting in shorter vehicle than less powerful Saturn C-3. Manufacturer: Von Braun. LEO Payload: 95,000 kg (209,000 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 31,000 kg (68,000 lb). to a: Translunar trajectory. Liftoff Thrust: 26,679.900 kN (5,997,880 lbf). Total Mass: 2,051,290 kg (4,522,320 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 89.00 m (291.00 ft).
Stage Data - Saturn C-4B - Stage Number: 1. 1 x Stage: Saturn IC C-4B. Gross Mass: 1,450,984 kg (3,198,872 lb). Empty Mass: 90,686 kg (199,928 lb). Thrust (vac): 30,606.397 kN (6,880,592 lbf). Isp: 304 sec. Burn time: 130 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 33.46 m (109.77 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1. Status: Study 1961. Final first stage design of Saturn C-3 (November 1961). Unique S-IC design in that fuel and propellant tank shared common bulkhead; stage was actually shorter than C-3B S-IC.
- Stage Number: 2. 1 x Stage: 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. Final common second stage design for Saturn C-3, C-4 and C-5 (November 1961). Developed into Saturn V second stage.
- Stage Number: 3. 1 x Stage: 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. 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.
Bibliography and Further Reading - Hostetter, Dave, "Personal communication", Drawings of final Saturn configuration from archives, Alabama Space and Rocket Center..
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