Saurn MLV 5-3 - Saturn MLV 5-3 Credit: © Mark Wade. 6,460 bytes. 162 x 990 pixels.

MSFC study, 1965. Ultimate core for improved Saturn V configurations studied under contract NAS8-11359. Saturn IC stretched 240 inches with 5.6 million pounds propellant and 5 F-1A engines; S-II stretched 156 inches with 1.2 million pounds propellant and 5 HG-3 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 HG-3 engine.

LEO Payload: 160,400 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 65,800 kg. to a: Translunar trajectory. Liftoff Thrust: 4,080,890 kgf. Total Mass: 3,664,570 kg. Core Diameter: 10.1 m. Total Length: 121.0 m.

• Stage Number: 1. 1 x Saturn MS-IC-1 Gross Mass: 2,694,703 kg. Empty Mass: 169,719 kg. Thrust (vac): 4,685,469 kgf. Isp: 310 sec. Burn time: 158 sec. Isp(sl): 270 sec. Diameter: 10.1 m. Span: 19.0 m. Length: 48.1 m. Propellants: Lox/Kerosene No Engines: 5. F-1A

• Stage Number: 2. 1 x Saturn MS-II-2 Gross Mass: 600,788 kg. Empty Mass: 59,844 kg. Thrust (vac): 714,156 kgf. Isp: 451 sec. Burn time: 324 sec. Isp(sl): 280 sec. Diameter: 10.1 m. Span: 10.1 m. Length: 29.6 m. Propellants: Lox/LH2 No Engines: 5. HG-3

• Stage Number: 3. 1 x Saturn MS-IVB-2 Gross Mass: 176,600 kg. Empty Mass: 17,800 kg. Thrust (vac): 142,900 kgf. Isp: 447 sec. Burn time: 489 sec. Isp(sl): 200 sec. Diameter: 6.6 m. Span: 6.6 m. Length: 23.1 m. Propellants: Lox/LH2 No Engines: 1. HG-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
• 230 - Saturn V Improvement Study, Final report, NASA Contract NAS8-11359.