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Family: Saturn V. Country: USA. Status: Study 1967.
Saturn variant consisting of S-IC first stage and S-IVB second stage. Consideration was given to deleting one or more of the F-1 engines in the first stage.
|Liftoff Mass - kg||S-IC - No.
F-1 Motors||Payload - kg - 4.68 G limit||Payload - kg - 6.0 G limit|
LEO Payload: 60,000 kg. to: 185 km Orbit. at: 28.0 degrees. Liftoff Thrust: 3,440,310 kgf. Total Mass: 2,478,120 kg. Core Diameter: 10.1 m. Total Length: 72.0 m. Flyaway Unit Cost $: 391.50 million. in 1985 unit dollars.
- Stage Number: 1. 1 x Saturn IC Gross Mass: 2,286,217 kg. Empty Mass: 135,218 kg. Thrust (vac): 3,946,624 kgf. Isp: 304 sec. Burn time: 161 sec. Isp(sl): 265 sec. Diameter: 10.1 m. Span: 19.0 m. Length: 42.1 m. Propellants: Lox/Kerosene No Engines: 5. 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
- 233 - Alexander, George, Aviation Week and Space Technology, "Manned Flight Planning Gap Delays Saturn Development", 1966-08-08, page 60.
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Last update 12 March 2001.
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© Mark Wade, 2001 .