Encyclopedia Astronautica
Saturn C-3B



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Saturn C-33B 3 Stage
Saturn C-33B 3 Stage version Nov 1961
Credit: © Mark Wade
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Saturn C-3B final
Saturn C-3B final configuration Nov 1961
Credit: © Mark Wade
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Saturn A-1 to C-5
Credit: © Mark Wade
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Saturn C-3B 2 Stage
Saturn C-3B 2 Stage version Nov 1961
Credit: © Mark Wade
American orbital launch vehicle. Final configurtion of the Saturn C-3 at the time of selection of the Saturn C-5 configuration for the Apollo program in December 1961.

LEO Payload: 78,000 kg (171,000 lb) to a 185 km orbit at 28.00 degrees. Payload: 25,000 kg (55,000 lb) to a translunar trajectory.

Stage Data - Saturn C-3B

  • Stage 1. 1 x Saturn IC C-3B. Gross Mass: 1,160,787 kg (2,559,097 lb). Empty Mass: 72,549 kg (159,943 lb). Thrust (vac): 22,954.798 kN (5,160,444 lbf). Isp: 304 sec. Burn time: 140 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 34.41 m (112.89 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1. Status: Study 1961. Comments: Final first stage design of Saturn C-3 (November 1961).
  • 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-3B. Gross Mass: 52,144 kg (114,957 lb). Empty Mass: 6,801 kg (14,993 lb). Thrust (vac): 889.325 kN (199,928 lbf). Isp: 420 sec. Burn time: 207 sec. Isp(sl): 200 sec. Diameter: 5.59 m (18.33 ft). Span: 5.59 m (18.33 ft). Length: 15.40 m (50.50 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Study 1961. Comments: Final common third stage design for Saturn C-3B (November 1961).

Status: Study 1961.
Gross mass: 1,690,590 kg (3,727,110 lb).
Payload: 78,000 kg (171,000 lb).
Height: 85.00 m (278.00 ft).
Diameter: 10.06 m (33.00 ft).
Thrust: 20,010.00 kN (4,498,420 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 C-3 The launch vehicle concept considered for a time as the leading contender for the Earth Orbit Rendezvous approach to an American lunar landing. 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 IC C-3B Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,160,787/72,549 kg. Thrust 22,954.80 kN. Vacuum specific impulse 304 seconds. Final first stage design of Saturn C-3 (November 1961). More...
  • Saturn II C-5A Lox/LH2 propellant rocket stage. Loaded/empty mass 384,057/31,740 kg. Thrust 4,446.65 kN. Vacuum specific impulse 420 seconds. Final common second stage design for Saturn C-3, C-4 and C-5 (November 1961). Developed into Saturn V second stage. More...
  • Saturn IVB C-3B Lox/LH2 propellant rocket stage. Loaded/empty mass 52,144/6,801 kg. Thrust 889.33 kN. Vacuum specific impulse 420 seconds. Final common third stage design for Saturn C-3B (November 1961). More...

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