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Family: Saturn I. Country: USA. Status: Study 1966.
UA Studies, 1966: S-IVB upper stage with from 2 to 5 Titan UA1205, 1206, or 1207 motors as first stage, clustered around from 1 to 3 of the same motors as a second stage. S-IVB upper stage.
SpecificationsLEO Payload: 28,000 kg. to: 185 km Orbit. at: 28.0 degrees. Liftoff Thrust: 2,698,870 kgf. Total Mass: 1,283,570 kg. Core Diameter: 6.6 m. Total Length: 52.0 m. Flyaway Unit Cost $: 89.90 million. in 1985 unit dollars.
- Stage Number: 1. 5 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: 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
- 232 - Tharratt, C E, Spaceflight, "Improving the Uprated Saturn 1", 1967, page 207.
- 234 - Normyle, William J, Aviation Week and Space Technology, "Changing Concepts Key to Desing of Future Saturn Family", 1966-03-27, page 106.
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Last update 12 March 2001.
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© Mark Wade, 2001 .