Saturn C-3B

American orbital launch vehicle. Final configuration 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).