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|Saturn 1B/120-7 seg - Saturn 1B with 120 inch 7 segment strapon|
Credit: © Mark Wade. 5,188 bytes. 135 x 760 pixels.
Family: Saturn II. Country: USA. Status: Study 1966.
North American study, 1966. Saturn variant with a modified S-II first stage with seven high-performance HG-3 engines; S-IVB second stage. Poor performance and cost-effectiveness and not studied further.
LEO Payload: 42,000 kg. to: 185 km Orbit. at: 28.0 degrees. Liftoff Thrust: 605,305 kgf. Total Mass: 504,400 kg. Core Diameter: 10.1 m. Total Length: 51.0 m.
- Stage Number: 1. 1 x Saturn II-INT-17 Gross Mass: 495,000 kg. Empty Mass: 48,000 kg. Thrust (vac): 990,500 kgf. Isp: 450 sec. Burn time: 200 sec. Isp(sl): 275 sec. Diameter: 10.1 m. Span: 10.1 m. Length: 24.8 m. Propellants: Lox/LH2 No Engines: 7. HG-3-SL
- 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
- 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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