 | Saturn IB-INT-11
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 only 4 H-1 motors, with 4 Titan UA1205 with standard length S-IB stage, S-IVB stage, or 4 Titan UA1207 strap-ons with 20-foot stretche S-IB stage, S-IVB stage. S-IB ignition at sea level at same time as strap-ons. Manufacturer: Von Braun. LEO Payload: 34,000 kg (74,000 lb). to: 169 km Orbit. at: 28.00 degrees. Liftoff Thrust: 24,820.900 kN (5,579,960 lbf). Total Mass: 1,509,230 kg (3,327,280 lb). Core Diameter: 6.61 m (21.68 ft). Total Length: 51.00 m (167.00 ft). Flyaway Unit Cost $: 71.920 million. in: 1985 unit dollars.
Stage Data - Saturn INT-12 - Stage Number: 0. 4 x Stage: Titan UA1205 . Gross Mass: 226,233 kg (498,758 lb). Empty Mass: 33,798 kg (74,511 lb). Thrust (vac): 5,849.411 kN (1,315,000 lbf). Isp: 263 sec. Burn time: 115 sec. Isp(sl): 238 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 25.91 m (85.00 ft). Propellants: Solid. No Engines: 1. Engine: UA1205. Status: Out of production.
- Stage Number: 1. 1 x Stage: Saturn S-1B-4 H-1. Gross Mass: 444,700 kg (980,300 lb). Empty Mass: 37,600 kg (82,800 lb). Thrust (vac): 4,120.700 kN (926,370 lbf). Isp: 296 sec. Burn time: 282 sec. Isp(sl): 262 sec. Diameter: 6.52 m (21.39 ft). Span: 6.52 m (21.39 ft). Length: 24.48 m (80.31 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: H-1b. Status: Study 1966. Chrysler Studies, 1966: S-1B with 4 H-1's for use with Titan UA1205 strap-ons
- 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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