Encyclopedia Astronautica
Saturn INT-16



satint16.gif
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.

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

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

More... - Chronology...


Associated Countries
Associated Engines
  • UA1205 CSD solid rocket engine. 5849.3 kN. Out of production. Isp=263s. Strap-on boosters for Titan 3C, 3D, 3E. Proposed for advanced Saturn IB versions. First flight 1965. More...

See also
  • Saturn I Von Braun launch vehicle known as 'Cluster's Last Stand' - 8 Redstone tanks around a Jupiter tank core,powered by eight Jupiter engines. Originally intended as the launch vehicle for Apollo manned circumlunar flights. However it was developed so early, no payloads were available for it. More...
  • Saturn The Saturn launch vehicle was the penultimate expression of the Peenemuende Rocket Team's designs for manned exploration of the moon and Mars. Numerous designs and variants were studied, but in the end only three models - the Saturn I, IB, and V - were built in the 1960's, and then only used to support NASA's Apollo moon landing program. More...

Associated Manufacturers and Agencies
  • Von Braun American manufacturer of rockets and spacecraft. Von Braun, USA. More...

Associated Stages
  • Saturn IVB (S-IB) Lox/LH2 propellant rocket stage. Loaded/empty mass 118,800/12,900 kg. Thrust 1,031.60 kN. Vacuum specific impulse 421 seconds. 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). More...
  • Titan UA1205 Solid propellant rocket stage. Loaded/empty mass 226,233/33,798 kg. Thrust 5,849.41 kN. Vacuum specific impulse 263 seconds. More...

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