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Family: Saturn I. Country: USA. Status: Study 1965.
UA Study, 1965: Full length 260 inch solid motor with S-IVB upper stage.
SpecificationsLEO Payload: 43,034 kg. to: 185 km Orbit. at: 28.0 degrees. Liftoff Thrust: 3,265,860 kgf. Total Mass: 1,818,800 kg. Core Diameter: 6.6 m. Total Length: 58.0 m. Flyaway Unit Cost $: 111.65 million. in 1985 unit dollars.
- Stage Number: 1. 1 x 260 inch solid FL Gross Mass: 1,648,355 kg. Empty Mass: 156,126 kg. Thrust (vac): 3,608,918 kgf. Isp: 263 sec. Burn time: 114 sec. Isp(sl): 238 sec. Diameter: 6.6 m. Span: 6.6 m. Length: 30.5 m. Propellants: Solid No Engines: 1. AJ-260X
- Stage Number: 2. 1 x Saturn IVB (S-IB) Gross Mass: 118,800 kg. Empty Mass: 12,900 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: 17.8 m. Propellants: Lox/LH2 No Engines: 1. J-2
Bibliography:- 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
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Last update 12 March 2001.
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© Mark Wade, 2001 .
