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Saturn INT-15
Part of Saturn I Family
Saturn 1B/120-5 seg
Saturn 1B/120-5 seg
Saturn 1B with 120 inch 5 segment strap on
Credit: © Mark Wade
American orbital launch vehicle. Chrysler Studies, 1966: S-IB with 8 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.

Status: Study 1966. Payload: 26,000 kg (57,000 lb). Thrust: 12,477.80 kN (2,805,121 lbf). Gross mass: 824,100 kg (1,816,800 lb). Height: 54.00 m (177.00 ft). Diameter: 6.61 m (21.68 ft). Apogee: 169 km (105 mi).

LEO Payload: 26,000 kg (57,000 lb) to a 169 km orbit at 28.00 degrees.

Stage Data - Saturn INT-15

  • Stage 0. 8 x 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: Out of Production. Comments: 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 1. 1 x Saturn IB-15. Gross Mass: 478,103 kg (1,054,036 lb). Empty Mass: 45,873 kg (101,132 lb). Thrust (vac): 8,241.763 kN (1,852,822 lbf). Isp: 296 sec. Burn time: 144 sec. Isp(sl): 262 sec. Diameter: 6.52 m (21.39 ft). Span: 6.52 m (21.39 ft). Length: 27.43 m (89.99 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: H-1b. Status: Study 1966. Comments: 10 foot stretch of Saturn IB. Not found useful in any configuration except with Minuteman first-stage strap-ons to augment thrust.
  • Stage 2. 1 x 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. Status: Out of Production. Comments: Saturn IB version of S-IVB stage. Due to lower 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).

Family: orbital launch vehicle. People: von Braun. Country: USA. Engines: H-1b. Stages: Saturn IB-15, Saturn IVB (S-IB), M55/TX-55/Tu-122.



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