Encyclopedia Astronautica
Saturn INT-13


American orbital launch vehicle. Chrysler Studies, 1966: S-IB with 2 Titan UA1205 with standard length S-IB stage, S-IVB stage, or 2 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.

LEO Payload: 36,590 kg (80,660 lb) to a 169 km orbit at 28.00 degrees in 1985 dollars. Flyaway Unit Cost $: 48.720 million.

Stage Data - Saturn INT-13

  • Stage 0. 2 x Titan UA1207. Gross Mass: 319,330 kg (704,000 lb). Empty Mass: 51,230 kg (112,940 lb). Thrust (vac): 7,116.999 kN (1,599,965 lbf). Isp: 272 sec. Burn time: 120 sec. Isp(sl): 245 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 34.14 m (112.00 ft). Propellants: Solid. No Engines: 1. Engine: UA1207. Status: In Production.
  • Stage 1. 1 x Saturn IB-11. Gross Mass: 505,953 kg (1,115,435 lb). Empty Mass: 48,545 kg (107,023 lb). Thrust (vac): 8,241.763 kN (1,852,822 lbf). Isp: 296 sec. Burn time: 153 sec. Isp(sl): 262 sec. Diameter: 6.52 m (21.39 ft). Span: 6.52 m (21.39 ft). Length: 30.48 m (99.99 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: H-1b. Status: Study 1966. Comments: 20 foot stretch of Saturn IB for use with UA1207 7 segment solid rocket strap-on units.
  • 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: 1,307,320 kg (2,882,140 lb).
Payload: 36,590 kg (80,660 lb).
Height: 58.00 m (190.00 ft).
Diameter: 6.61 m (21.68 ft).
Thrust: 20,116.10 kN (4,522,279 lbf).
Apogee: 169 km (105 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • H-1b Rocketdyne Lox/Kerosene rocket engine. 1030.2 kN. Isp=296s. First flight 1966. More...
  • UA1207 CSD solid rocket engine. 7116.9 kN. Isp=272s. First flight 1989. More...

See also
  • 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...
  • 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...

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

Associated Stages
  • Saturn IB-11 Lox/Kerosene propellant rocket stage. Loaded/empty mass 505,953/48,545 kg. Thrust 8,241.76 kN. Vacuum specific impulse 296 seconds. 20 foot stretch of Saturn IB for use with UA1207 7 segment solid rocket strap-on units. More...
  • 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 UA1207 Solid propellant rocket stage. Loaded/empty mass 319,330/51,230 kg. Thrust 7,117.00 kN. Vacuum specific impulse 272 seconds. More...

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