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Saturn INT-12

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Saturn IB-INT-11 Credit: © Mark Wade

Status: Study 1966. Payload: 34,000 kg (74,000 lb). Thrust: 24,820.90 kN (5,579,960 lbf). Gross mass: 1,509,230 kg (3,327,280 lb). Height: 51.00 m (167.00 ft). Diameter: 6.61 m (21.68 ft). Apogee: 169 km (105 mi).

LEO Payload: 34,000 kg (74,000 lb) to a 169 km orbit at 28.00 degrees. Flyaway Unit Cost 1985$: 71.920 million.

Stage Data - Saturn INT-12

• Stage 0. 4 x 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 1. 1 x 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. Comments: Chrysler Studies, 1966: S-1B with 4 H-1's for use with Titan UA1205 strap-ons.

• 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).