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Family: Saturn I. Country: USA. Status: Study 1965.
Douglas Studies, 1965: Standard Saturn IB with Titan UA1205 5-segment strap-on motors.
SpecificationsLEO Payload: 33,000 kg. to: 185 km Orbit. at: 28.0 degrees. Liftoff Thrust: 2,902,990 kgf. Total Mass: 1,511,980 kg. Core Diameter: 6.6 m. Total Length: 51.0 m. Flyaway Unit Cost $: 115.42 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 IB Gross Mass: 448,648 kg. Empty Mass: 41,594 kg. Thrust (vac): 840,426 kgf. Isp: 296 sec. Burn time: 155 sec. Isp(sl): 262 sec. Diameter: 6.5 m. Span: 6.5 m. Length: 24.5 m. Propellants: Lox/Kerosene No Engines: 8. H-1b
- 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 .