 | Saturn IB-INT-14
Credit - © Mark Wade
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Orbital launch vehicle. Year: 1966. Family: Saturn I. Country: USA. Status: Study 1966. Chrysler Studies, 1966: S-IB with 4 Minuteman motors as strap-ons, with no, 10, or 20-foot stretch S-IB stages, S-IVB stage. S-IB ignition at sea level at same time as strap-ons. Manufacturer: Von Braun. LEO Payload: 23,180 kg (51,100 lb). to: 169 km Orbit. at: 28.00 degrees. Liftoff Thrust: 9,886.400 kN (2,222,551 lbf). Total Mass: 750,570 kg (1,654,720 lb). Core Diameter: 6.61 m (21.68 ft). Total Length: 58.00 m (190.00 ft).
Stage Data - Saturn INT-14 - Stage Number: 0. 4 x Stage: Minuteman-1. Gross Mass: 23,077 kg (50,876 lb). Empty Mass: 2,292 kg (5,052 lb). Thrust (vac): 791.300 kN (177,891 lbf). Isp: 262 sec. Burn time: 60 sec. Isp(sl): 237 sec. Diameter: 1.67 m (5.47 ft). Span: 1.67 m (5.47 ft). Length: 7.49 m (24.57 ft). Propellants: Solid. No Engines: 1. Engine: M55/TX-55/Tu-122. Status: In production. First stage of Minuteman I. Proposed as zero stage for various Saturn variants in 1960's. Surplus motors used in ABM SDI tests in 1980's and 1990's.
- Stage Number: 1. 1 x Stage: Saturn IB-11. Gross Mass: 505,953 kg (1,115,435 lb). Empty Mass: 48,545 kg (107,023 lb). Thrust (vac): 8,241.763 kN (1,852,822 lbf). Isp: 296 sec. Burn time: 153 sec. Isp(sl): 262 sec. Diameter: 6.52 m (21.39 ft). Span: 6.52 m (21.39 ft). Length: 30.48 m (99.99 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: H-1b. Status: Study 1966. 20 foot stretch of Saturn IB for use with UA1207 7 segment solid rocket strap-on units.
- 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.
- Tharratt, C E, Spaceflight, "Improving the Uprated Saturn 1", 1967, page 207.
- 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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