Encyclopedia Astronautica
Saturn INT-15



sat115.gif
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.

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 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: 824,100 kg (1,816,800 lb).
Payload: 26,000 kg (57,000 lb).
Height: 54.00 m (177.00 ft).
Diameter: 6.61 m (21.68 ft).
Thrust: 12,477.80 kN (2,805,121 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...
  • M55/TX-55/Tu-122 Thiokol solid rocket engine. 792 kN. In production. Isp=262s. Proposed as strap-on booster for Saturn IB-C, Saturn INT-14, Saturn INT-15, Saturn INT-19 variants. First flight 2000. 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
  • Minuteman-1 Solid propellant rocket stage. Loaded/empty mass 23,077/2,292 kg. Thrust 791.30 kN. Vacuum specific impulse 262 seconds. 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. More...
  • Saturn IB-15 Lox/Kerosene propellant rocket stage. Loaded/empty mass 478,103/45,873 kg. Thrust 8,241.76 kN. Vacuum specific impulse 296 seconds. 10 foot stretch of Saturn IB. Not found useful in any configuration except with Minuteman first-stage strap-ons to augment thrust. 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...

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