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.

LEO Payload: 435,300 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 185,900 kg. to a: Translunar trajectory. Liftoff Thrust: 9,587,310 kgf. Total Mass: 7,386,760 kg. Core Diameter: 10.1 m. Total Length: 180.0 m.

• Stage Number: 0. 4 x Saturn MS-LRB-23(L) Gross Mass: 874,100 kg. Empty Mass: 18,100 kg. Thrust (vac): 1,579,200 kgf. Isp: 304 sec. Burn time: 162 sec. Isp(sl): 265 sec. Diameter: 6.6 m. Span: 6.6 m. Length: 47.9 m. Propellants: Lox/Kerosene No Engines: 2. F-1

• Stage Number: 1. 1 x Saturn MS-IC-1 Gross Mass: 2,694,703 kg. Empty Mass: 169,719 kg. Thrust (vac): 4,685,469 kgf. Isp: 310 sec. Burn time: 158 sec. Isp(sl): 270 sec. Diameter: 10.1 m. Span: 19.0 m. Length: 48.1 m. Propellants: Lox/Kerosene No Engines: 5. F-1A

• Stage Number: 2. 1 x Saturn MS-II-4(S)B Gross Mass: 494,100 kg. Empty Mass: 42,300 kg. Thrust (vac): 527,100 kgf. Isp: 421 sec. Burn time: 355 sec. Isp(sl): 200 sec. Diameter: 10.1 m. Span: 10.1 m. Length: 24.8 m. Propellants: Lox/LH2 No Engines: 5. J-2

• Stage Number: 3. 1 x Saturn MS-IVB-1A Gross Mass: 179,200 kg. Empty Mass: 20,400 kg. Thrust (vac): 105,200 kgf. Isp: 421 sec. Burn time: 625 sec. Isp(sl): 200 sec. Diameter: 6.6 m. Span: 6.6 m. Length: 22.8 m. Propellants: Lox/LH2 No Engines: 1. J-2

• 228 - Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Availabe chapters may be ordered directly from Scott Lowther at web site indicated. HTML when accessed: http://www.webcreations.com/ptm