Saturn IB-INT-11 - Credit: © Mark Wade. 2,028 bytes. 76 x 424 pixels.

Chrysler Studies, 1966: S-IB with only 4 H-1 motors, with 4 Titan UA1205 with standard length S-IB stage, S-IVB stage, or 4 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: 34,000 kg. to: 169 km Orbit. at: 28.0 degrees. Liftoff Thrust: 2,531,030 kgf. Total Mass: 1,509,230 kg. Core Diameter: 6.6 m. Total Length: 51.0 m. Flyaway Unit Cost $: 71.92 million. in 1985 unit dollars.

• Stage Number: 0. 4 x Titan UA1205 Gross Mass: 226,233 kg. Empty Mass: 33,798 kg. Thrust (vac): 596,474 kgf. Isp: 263 sec. Burn time: 115 sec. Isp(sl): 238 sec. Diameter: 3.1 m. Span: 3.1 m. Length: 25.9 m. Propellants: Solid No Engines: 1. UA1205

• Stage Number: 1. 1 x Saturn S-1B-4 H-1 Gross Mass: 444,700 kg. Empty Mass: 37,600 kg. Thrust (vac): 420,200 kgf. Isp: 296 sec. Burn time: 282 sec. Isp(sl): 262 sec. Diameter: 6.5 m. Span: 6.5 m. Length: 24.5 m. Propellants: Lox/Kerosene No Engines: 4. 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.