Boeing study, 1968. 4 156 inch solid propellant boosters; Saturn IC stretched 498 inches with 6.64 million pounds propellant and 5 F-1 engines; S-II standard length with 5 J-2 engines. This vehicle would place Nerva nuclear third stage into low earth orbit, where five such stages would be assembled together with the spacecraft for a manned Mars expedition.

LEO Payload: 248,663 kg. to: 486 km Orbit. at: 28.0 degrees. Payload: 160,000 kg. to a: Translunar trajectory. Liftoff Thrust: 7,376,460 kgf. Total Mass: 6,439,300 kg. Core Diameter: 10.1 m. Total Length: 153.0 m. Flyaway Unit Cost $: 174.00 million. in 1985 unit dollars.

• Stage Number: 0. 4 x UA 156 inch Gross Mass: 544,311 kg. Empty Mass: 37,195 kg. Thrust (vac): 910,044 kgf. Isp: 263 sec. Burn time: 157 sec. Isp(sl): 238 sec. Diameter: 4.0 m. Span: 4.0 m. Length: 34.0 m. Propellants: Solid No Engines: 1. UA-156

• Stage Number: 1. 1 x Saturn MS-IC-25(S) Gross Mass: 3,223,800 kg. Empty Mass: 211,900 kg. Thrust (vac): 4,683,100 kgf. Isp: 304 sec. Burn time: 192 sec. Isp(sl): 265 sec. Diameter: 10.1 m. Span: 19.0 m. Length: 54.7 m. Propellants: Lox/Kerosene No Engines: 5. F-1A

• Stage Number: 2. 1 x Saturn MS-II-4(S)B Gross Mass: 494,100 kg. Empty Mass: 42,300 kg. Thrust (vac): 527,100 kgf. Isp: 421 sec. Burn time: 355 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 S-N V-25(S)U Gross Mass: 245,760 kg. Empty Mass: 71,190 kg. Thrust (vac): 90,686 kgf. Isp: 825 sec. Burn time: 1,500 sec. Diameter: 10.1 m. Span: 10.1 m. Length: 48.2 m. Propellants: Nuclear/LH2 No Engines: 1. Nerva

• 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