Saturn V-MLV-1 - Credit: © Mark Wade. 6,031 bytes. 173 x 853 pixels.

MSFC study, 1965. Improved Saturn V configuration studied under contract NAS8-11359. Saturn IC stretched 240 inches with 5.6 million pounds propellant and 5 F-1A engines; S-II stretched 41 inches with 1.0 million pounds propellant and 5 J-2 engines; S-IVB strengthened but with standard 230,000 lbs propellant, 1 J-2 engine.

LEO Payload: 137,250 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 49,600 kg. to a: Translunar trajectory. Liftoff Thrust: 4,080,890 kgf. Total Mass: 3,501,350 kg. Core Diameter: 10.1 m. Total Length: 111.0 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-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.

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Saturn MLV 1.37 Credit: © Mark Wade. 5,187 bytes. 135 x 760 pixels.

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