 | Saturn IB-INT-5A
Credit - © Mark Wade
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Orbital launch vehicle. Year: 1965. Family: Saturn I. Country: USA. Status: Study 1965. UA Study, 1965: Full length 260 inch solid motor with S-IVB upper stage. Manufacturer: Von Braun. LEO Payload: 43,034 kg (94,873 lb). to: 185 km Orbit. at: 28.00 degrees. Liftoff Thrust: 32,027.100 kN (7,199,979 lbf). Total Mass: 1,818,800 kg (4,009,700 lb). Core Diameter: 6.61 m (21.68 ft). Total Length: 58.00 m (190.00 ft). Flyaway Unit Cost $: 111.650 million. in: 1985 unit dollars.
Stage Data - Saturn INT-05A - Stage Number: 1. 1 x Stage: 260 inch solid FL. Gross Mass: 1,648,355 kg (3,634,000 lb). Empty Mass: 156,126 kg (344,198 lb). Thrust (vac): 35,391.395 kN (7,956,302 lbf). Isp: 263 sec. Burn time: 114 sec. Isp(sl): 238 sec. Diameter: 6.60 m (21.60 ft). Span: 6.60 m (21.60 ft). Length: 30.48 m (99.99 ft). Propellants: Solid. No Engines: 1. Engine: AJ-260X. Status: Study 1967. 260 inch solid booster - full length. These would have been the flight configuration motors, replacing the Saturn V first stage or being used as booster motors in various Uprated Saturn and Nova configurations.
- Stage Number: 2. 1 x Stage: Saturn IVB (S-IB). Gross Mass: 118,800 kg (261,900 lb). Empty Mass: 12,900 kg (28,400 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 475 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 17.80 m (58.30 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Saturn IB version of S-IVB stage. Due to lower payload payload, 300 kg saving in structure compared to Saturn V version. Due to deletion of restart requirement, 700 kg saving in propulsion system (primarily reduction in helium for restart).
Bibliography and Further Reading - Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Availabe chapters may be ordered directly from Scott Lowther at web site indicated. Accessed at: http://www.webcreations.com/ptm.
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