Saturn V-3B (original) (raw)

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Saturn V-3B

Part of Saturn V

American orbital launch vehicle. Boeing study, 1967. Variation on MSFC 1965 study Saturn MLV-V-3 but with toroidal engines. Saturn IC stretched 240 inches with 5.6 million pounds propellant (but only 4.99 million pounds usable without solid rocket boosters) and 5 F-1A engines; S-II stretched 186 inches with 1.29 million lbs propellant and 5 J-2T-400 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2T-400 engine.

Status: Study 1967. Payload: 166,600 kg (367,200 lb). Thrust: 40,033.80 kN (8,999,956 lbf). Gross mass: 3,741,120 kg (8,247,750 lb). Height: 121.00 m (396.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).

LEO Payload: 166,600 kg (367,200 lb) to a 185 km orbit at 28.00 degrees. Payload: 72,800 kg (160,400 lb) to a translunar trajectory.

Stage Data - Saturn V-3B

Stage 1. 1 x Saturn MS-IC-3B. Gross Mass: 2,718,800 kg (5,993,900 lb). Empty Mass: 178,700 kg (393,900 lb). Thrust (vac): 45,925.500 kN (10,324,463 lbf). Isp: 304 sec. Burn time: 162 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 48.15 m (157.97 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1A. Status: Study Boeing 1967. Comments: S-IC with 20 foot stretch, 1.8 million lb thrust F-1's, 5.6 million pounds propellant capacity (fuel offloaded to 4.99 million for LEO or 4.80 million lbs for LOR mission).
Stage 2. 1 x Saturn MS-II-3B. Gross Mass: 643,200 kg (1,418,000 lb). Empty Mass: 53,500 kg (117,900 lb). Thrust (vac): 12,455.400 kN (2,800,085 lbf). Isp: 447 sec. Burn time: 204 sec. Isp(sl): 200 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 29.56 m (96.98 ft). Propellants: Lox/LH2. No Engines: 5. Engine: Toroidal 400k. Status: Study Boeing 1967. Comments: S-II with 15.5 foot stretch, 1.29 million pounds propellant, 7 x 400,000 lb thrust toroidal engines.
Stage 3. 1 x Saturn MS-IVB-3B. Gross Mass: 179,200 kg (395,000 lb). Empty Mass: 20,400 kg (44,900 lb). Thrust (vac): 1,778.900 kN (399,913 lbf). Isp: 447 sec. Burn time: 385 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 22.82 m (74.86 ft). Propellants: Lox/LH2. No Engines: 1. Engine: Toroidal 400k. Status: Study Boeing 1967. Comments: S-IVB with 16.5 foot stretch, 350,000 pounds propellant, 1 400,000 pound thrust toroidal engine.

Family: orbital launch vehicle. People: von Braun. Country: USA. Engines: F-1A, Toroidal 400k. Stages: Saturn MS-IC-3B, Saturn MS-II-3B, Saturn MS-IVB-3B.

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