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.

LEO Payload: 166,600 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 72,800 kg. to a: Translunar trajectory. Liftoff Thrust: 4,082,310 kgf. Total Mass: 3,741,120 kg. Core Diameter: 10.1 m. Total Length: 121.0 m.

• Stage Number: 1. 1 x Saturn MS-IC-3B Gross Mass: 2,718,800 kg. Empty Mass: 178,700 kg. Thrust (vac): 4,683,100 kgf. Isp: 304 sec. Burn time: 162 sec. Isp(sl): 265 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-3B Gross Mass: 643,200 kg. Empty Mass: 53,500 kg. Thrust (vac): 1,270,100 kgf. Isp: 447 sec. Burn time: 204 sec. Isp(sl): 200 sec. Diameter: 10.1 m. Span: 10.1 m. Length: 29.6 m. Propellants: Lox/LH2 No Engines: 5. Toroidal 400k

• Stage Number: 3. 1 x Saturn MS-IVB-3B Gross Mass: 179,200 kg. Empty Mass: 20,400 kg. Thrust (vac): 181,400 kgf. Isp: 447 sec. Burn time: 385 sec. Isp(sl): 200 sec. Diameter: 6.6 m. Span: 6.6 m. Length: 22.8 m. Propellants: Lox/LH2 No Engines: 1. Toroidal 400k

• 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