Saturn IB-A - Credit: © Mark Wade. 1,718 bytes. 72 x 383 pixels.

Douglas Studies, 1965: S-IB with 225 k lbf H-1's; S-IVB stretched with 350,000 lbs propellants; Centaur third stage.

LEO Payload: 18,600 kg. to: 185 km Orbit. at: 28.0 degrees. Liftoff Thrust: 816,450 kgf. Total Mass: 605,980 kg. Core Diameter: 6.6 m. Total Length: 62.0 m. Flyaway Unit Cost $: 20.30 million. in 1985 unit dollars.

• Stage Number: 1. 1 x Saturn S-IB-A Gross Mass: 448,600 kg. Empty Mass: 41,600 kg. Thrust (vac): 922,400 kgf. Isp: 296 sec. Burn time: 128 sec. Isp(sl): 262 sec. Diameter: 6.5 m. Span: 6.5 m. Length: 24.5 m. Propellants: Lox/Kerosene No Engines: 8. H-1c

• Stage Number: 2. 1 x Saturn IVB-A Gross Mass: 118,800 kg. Empty Mass: 12,900 kg. Thrust (vac): 97,500 kgf. Isp: 421 sec. Burn time: 450 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: 3. 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