Saturn MLV 5-3 - Credit: © Mark Wade. 6,374 bytes. 164 x 923 pixels.

Boeing study, 1967. Configuration of improved Saturn 5 with Titan UA1207 120 inch solid rocket boosters. Saturn IC stretched 336 inches with 6.0 million pounds propellant and 5 F-1 engines; Saturn II and Saturn IVB stages strengthened but not stretched. Empty mass of stages increased by 13.9% (S-IC), 8.6% (S-II) and 11.8% (S-IVB). Studied again by Boeing in 1967 as Saturn V-4(S)B.

LEO Payload: 171,990 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 63,160 kg. to a: Translunar trajectory. Liftoff Thrust: 7,068,380 kgf. Total Mass: 4,699,860 kg. Core Diameter: 10.1 m. Total Length: 89.0 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-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-1-J-2T-250K Gross Mass: 521,447 kg. Empty Mass: 49,877 kg. Thrust (vac): 566,790 kgf. Isp: 441 sec. Burn time: 348 sec. Isp(sl): 290 sec. Diameter: 10.1 m. Span: 10.1 m. Length: 25.9 m. Propellants: Lox/LH2 No Engines: 5. J-2T-250K

• 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
• 230 - Saturn V Improvement Study, Final report, NASA Contract NAS8-11359.