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: 81,600 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 20,400 kg. to a: Translunar trajectory. Liftoff Thrust: 3,440,290 kgf. Total Mass: 2,504,020 kg. Core Diameter: 10.1 m. Total Length: 72.0 m.

• Stage Number: 0. 1 x Saturn S-ID Booster Gross Mass: 67,100 kg. Empty Mass: 67,100 kg. Thrust (vac): 3,157,300 kgf. Isp: 304 sec. Burn time: 154 sec. Isp(sl): 265 sec. Diameter: 10.1 m. Span: 19.0 m. Length: 42.1 m. Propellants: Lox/Kerosene No Engines: 4. F-1

• Stage Number: 1. 1 x Saturn S-ID Sustainer Gross Mass: 2,219,100 kg. Empty Mass: 68,100 kg. Thrust (vac): 789,300 kgf. Isp: 304 sec. Burn time: 315 sec. Isp(sl): 265 sec. Diameter: 10.1 m. Span: 19.0 m. Length: 42.1 m. Propellants: Lox/Kerosene No Engines: 1. F-1

• 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

• 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