|
Orbital launch vehicle. Year: 1967. Family: Saturn V. Country: USA. Status: Study 1967. 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. Manufacturer: Von Braun. LEO Payload: 166,600 kg (367,200 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 72,800 kg (160,400 lb). to a: Translunar trajectory. Liftoff Thrust: 40,033.800 kN (8,999,956 lbf). Total Mass: 3,741,120 kg (8,247,750 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 121.00 m (396.00 ft).
Stage Data - Saturn V-3B - Stage Number: 1. 1 x Stage: 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 1967. 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 Number: 2. 1 x Stage: 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 1967. S-II with 15.5 foot stretch, 1.29 million pounds propellant, 7 x 400,000 lb thrust toroidal engines.
- Stage Number: 3. 1 x Stage: 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 1967. S-IVB with 16.5 foot stretch, 350,000 pounds propellant, 1 400,000 pound thrust toroidal engine.
Bibliography and Further Reading - Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Availabe chapters may be ordered directly from Scott Lowther at web site indicated. Accessed at: http://www.webcreations.com/ptm.
|