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Saturn INT-16
Part of Saturn I Family
Saturn IB-INT-16
Saturn IB-INT-16
Credit: © Mark Wade
American orbital launch vehicle. UA Studies, 1966: S-IVB upper stage with from 2 to 5 Titan UA1205, 1206, or 1207 motors as first stage, clustered around from 1 to 3 of the same motors as a second stage. S-IVB upper stage.

Status: Study 1966. Payload: 28,000 kg (61,000 lb). Thrust: 26,466.90 kN (5,949,996 lbf). Gross mass: 1,283,570 kg (2,829,780 lb). Height: 52.00 m (170.00 ft). Diameter: 6.61 m (21.68 ft). Apogee: 185 km (114 mi).

LEO Payload: 28,000 kg (61,000 lb) to a 185 km orbit at 28.00 degrees. Flyaway Unit Cost 1985$: 89.900 million.

Stage Data - Saturn INT-16

  • Stage 1. 5 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 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. Stages: Saturn IVB (S-IB), UA1205.



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