NASA study, 1966. No-height-limitation stretched Saturn with Titan UA1207 motors for thrust augmentation.

LEO Payload: 200,000 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 67,000 kg. to a: Translunar trajectory. Liftoff Thrust: 6,056,370 kgf. Total Mass: 5,172,820 kg. Core Diameter: 10.1 m. Total Length: 124.0 m. Flyaway Unit Cost $: 97.44 million. in 1985 unit dollars.

• Stage Number: 0. 4 x Titan UA1207 Gross Mass: 319,330 kg. Empty Mass: 51,230 kg. Thrust (vac): 725,732 kgf. Isp: 272 sec. Burn time: 120 sec. Isp(sl): 245 sec. Diameter: 3.1 m. Span: 3.1 m. Length: 34.1 m. Propellants: Solid No Engines: 1. UA1207

• Stage Number: 1. 1 x Saturn MS-IC-4(S)B Gross Mass: 2,875,500 kg. Empty Mass: 154,000 kg. Thrust (vac): 3,948,100 kgf. Isp: 304 sec. Burn time: 206 sec. Isp(sl): 265 sec. Diameter: 10.1 m. Span: 19.0 m. Length: 50.6 m. Propellants: Lox/Kerosene No Engines: 5. F-1

• Stage Number: 2. 1 x Saturn MS-II-1A Gross Mass: 600,800 kg. Empty Mass: 60,000 kg. Thrust (vac): 650,675 kgf. Isp: 421 sec. Burn time: 345 sec. Isp(sl): 200 sec. Diameter: 10.1 m. Span: 10.1 m. Length: 29.6 m. Propellants: Lox/LH2 No Engines: 7. 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