Chrysler Studies, 1966: S-IB with 2 Titan UA1205 with standard length S-IB stage, S-IVB stage, or 2 Titan UA1207 strap-ons with 20-foot stretche S-IB stage, S-IVB stage. S-IB ignition at sea level at same time as strap-ons.

LEO Payload: 36,590 kg. to: 169 km Orbit. at: 28.0 degrees. Liftoff Thrust: 2,051,270 kgf. Total Mass: 1,307,320 kg. Core Diameter: 6.6 m. Total Length: 58.0 m. Flyaway Unit Cost $: 48.72 million. in 1985 unit dollars.

• Stage Number: 0. 2 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 IB-11 Gross Mass: 505,953 kg. Empty Mass: 48,545 kg. Thrust (vac): 840,426 kgf. Isp: 296 sec. Burn time: 153 sec. Isp(sl): 262 sec. Diameter: 6.5 m. Span: 6.5 m. Length: 30.5 m. Propellants: Lox/Kerosene No Engines: 8. H-1b

• Stage Number: 2. 1 x Saturn IVB (S-IB) Gross Mass: 118,800 kg. Empty Mass: 12,900 kg. Thrust (vac): 105,200 kgf. Isp: 421 sec. Burn time: 475 sec. Isp(sl): 200 sec. Diameter: 6.6 m. Span: 6.6 m. Length: 17.8 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
• 232 - Tharratt, C E, Spaceflight, "Improving the Uprated Saturn 1", 1967, page 207.
• 234 - Normyle, William J, Aviation Week and Space Technology, "Changing Concepts Key to Desing of Future Saturn Family", 1966-03-27, page 106.