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Orbital launch vehicle. Year: 1967. Family: Saturn V. Country: USA. Status: Study 1967. Boeing study, 1967. 4 260 inch liquid propellant boosters (each with 2 F-1A).; Saturn IC stretched 336 inches with 6.0 million pounds propellant and 5 F-1A engines; S-II stretched 156 inches with 1.2 million pounds propellant and 5 HG-3 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 HG-3 engine. Not studied in detail since vehicle height of 600 feet with payload exceeded study limit of 410 feet. Manufacturer: Von Braun. LEO Payload: 435,300 kg (959,600 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 185,900 kg (409,800 lb). to a: Translunar trajectory. Liftoff Thrust: 94,019.400 kN (21,136,402 lbf). Total Mass: 7,386,760 kg (16,285,010 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 180.00 m (590.00 ft).
Stage Data - Saturn V-24(L) - Stage Number: 0. 4 x Stage: Saturn MS-LRB-23(L). Gross Mass: 874,100 kg (1,927,000 lb). Empty Mass: 18,100 kg (39,900 lb). Thrust (vac): 15,486.600 kN (3,481,526 lbf). Isp: 304 sec. Burn time: 162 sec. Isp(sl): 265 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 47.85 m (156.98 ft). Propellants: Lox/Kerosene. No Engines: 2. Engine: F-1. Status: Study 1967. Liquid rocket booster strap-ons using 2 F-1's.
- Stage Number: 1. 1 x Stage: Saturn MS-IC-1. Gross Mass: 2,694,703 kg (5,940,803 lb). Empty Mass: 169,719 kg (374,166 lb). Thrust (vac): 45,948.754 kN (10,329,691 lbf). Isp: 310 sec. Burn time: 158 sec. Isp(sl): 270 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. Basic Saturn IC stretched 240 inches with F-1A engines uprated 20% in thrust and 6 second improvement in specific impulse.
- Stage Number: 2. 1 x Stage: Saturn MS-II-4(S)B. Gross Mass: 494,100 kg (1,089,300 lb). Empty Mass: 42,300 kg (93,200 lb). Thrust (vac): 5,169.000 kN (1,162,037 lbf). Isp: 421 sec. Burn time: 355 sec. Isp(sl): 200 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 24.84 m (81.49 ft). Propellants: Lox/LH2. No Engines: 5. Engine: J-2. Status: Study 1968. Standard S-II but with structural strength increased from 86% to 502% depending on station, resulting in 8.6% increase in empty weight.
- Stage Number: 3. 1 x Stage: Saturn MS-IVB-1A. Gross Mass: 179,200 kg (395,000 lb). Empty Mass: 20,400 kg (44,900 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 625 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: J-2. Status: Study 1966. S-IVB with 16.5 foot stretch, 350,000 pounds propellant, standard J-2 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.
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