S-1C details Credit: © Mark Wade. 40,371 bytes. 510 x 391 pixels.

MSFC study, 1968. S-ID stage-and-a-half first stage and Saturn IVB second stage. Centaur available as third stage for deep space missions. 30% performance improvement over Saturn V-A/Saturn INT-20 with standard Saturn IC first stage.

LEO Payload: 118,000 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 39,000 kg. to a: Mars flyby trajectory. Liftoff Thrust: 3,440,310 kgf. Total Mass: 3,054,750 kg. Core Diameter: 10.1 m. Total Length: 113.0 m. Flyaway Unit Cost $: 701.80 million. in 1985 unit dollars.

• Stage Number: 1. 1 x Saturn IC Gross Mass: 2,286,217 kg. Empty Mass: 135,218 kg. Thrust (vac): 3,946,624 kgf. Isp: 304 sec. Burn time: 161 sec. Isp(sl): 265 sec. Diameter: 10.1 m. Span: 19.0 m. Length: 42.1 m. Propellants: Lox/Kerosene No Engines: 5. F-1

• Stage Number: 2. 1 x Saturn II Gross Mass: 490,778 kg. Empty Mass: 39,048 kg. Thrust (vac): 526,764 kgf. Isp: 421 sec. Burn time: 390 sec. Isp(sl): 200 sec. Diameter: 10.1 m. Span: 10.1 m. Length: 24.8 m. Propellants: Lox/LH2 No Engines: 5. J-2

• Stage Number: 3. 1 x Saturn IVB (S-V) Gross Mass: 119,900 kg. Empty Mass: 13,300 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

• Stage Number: 4. 1 x Centaur D/E Gross Mass: 16,258 kg. Empty Mass: 2,631 kg. Thrust (vac): 13,381 kgf. Isp: 444 sec. Burn time: 470 sec. Isp(sl): 0 sec. Diameter: 3.1 m. Span: 3.1 m. Length: 9.6 m. Propellants: Lox/LH2 No Engines: 2. RL-10A-3

• 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