Saturn C-3BN

American nuclear orbital launch vehicle. Version of Saturn C-3 considered with small nuclear thermal stage in place of S-IVB oxygen/hydrogen stage.

LEO Payload: 94,000 kg (207,000 lb) to a 185 km orbit at 28.00 degrees. Payload: 38,000 kg (83,000 lb) to a translunar trajectory.

Stage Data - Saturn C-3BN

• 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 S-N C-3BN. Gross Mass: 32,470 kg (71,580 lb). Empty Mass: 7,708 kg (16,993 lb). Thrust (vac): 266.799 kN (59,979 lbf). Isp: 800 sec. Burn time: 720 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 16.56 m (54.33 ft). Propellants: Nuclear/LH2. No Engines: 1. Engine: Nerva. Status: Study 1961. Comments: Nuclear upper stage considered in lieu of S-IVB in final Saturn C-3B study in November 1961.