Saturn V 120" SRB - Saturn V 120 inch strapons Credit: © Mark Wade. 5,874 bytes. 161 x 996 pixels.

MSFC study, 1965. 4 Titan UA1205 solid rocket boosters; Saturn IC stretched 337 inches with 6.0 million pounds propellant and 5 F-1 engines; S-II with 970,000 pounds propellant and 5 J-2 engines; S-IVB strengthened but with standard 230,000 lbs propellant, 1 J-2 engine.

LEO Payload: 160,880 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 57,500 kg. to a: Translunar trajectory. Liftoff Thrust: 5,600,700 kgf. Total Mass: 4,615,440 kg. Core Diameter: 10.1 m. Total Length: 113.0 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 MS-IC-4(S)B Gross Mass: 2,875,500 kg. Empty Mass: 154,000 kg. Thrust (vac): 3,948,100 kgf. Isp: 304 sec. Burn time: 206 sec. Isp(sl): 265 sec. Diameter: 10.1 m. Span: 19.0 m. Length: 50.6 m. Propellants: Lox/Kerosene No Engines: 5. F-1

• Stage Number: 2. 1 x Saturn MS-II-1 Gross Mass: 521,447 kg. Empty Mass: 49,877 kg. Thrust (vac): 526,764 kgf. Isp: 425 sec. Burn time: 361 sec. Isp(sl): 306 sec. Diameter: 10.1 m. Span: 10.1 m. Length: 25.9 m. Propellants: Lox/LH2 No Engines: 5. J-2

• Stage Number: 3. 1 x Saturn MS-IVB-1 Gross Mass: 120,500 kg. Empty Mass: 13,900 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: 18.1 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
• 230 - Saturn V Improvement Study, Final report, NASA Contract NAS8-11359.