Encyclopedia Astronautica
Saturn INT-18



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Saturn 2SL/120" SRB
Saturn 2SL 120 inch strapons
Credit: © Mark Wade
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Saturn 2-120-5
Credit: © Mark Wade
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Saturn MLV 2-120-7
Credit: © Mark Wade
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Saturn 2-120-4
Credit: © Mark Wade
North American study, 1966. Saturn variant with Titan UA1205 or 1207 motors as boosters, Saturn II stage as core, and Saturn IVB upper stage. Various combinations of numbers of strap-ons, propellant loading of the two core stages, and sea-level versus altitude ignition were studied.

Liftoff Mass - kgStrapon Motor TypeNumber of StraponsS-II Propellant - kgS-IVB Propellant - kgPayload - kg
1,132,000Titan UA12044215,40080,30021,300
1,132,000Titan UA12044215,40078,50023,100
1,030,400Titan UA12072254,00080,70027,400
1,132,400Titan UA12072349,20079,80035,400
1,083,000Titan UA12052431,60077,40040,500
1,570,500Titan UA12054440,40074,40051,700
1,895,200Titan UA12074446,70075,70066,400
1,476,200Titan UA12054446,700No S-IVB39,000
1,779,600Titan UA12074446,700No S-IVB44,000

LEO Payload: 66,590 kg (146,800 lb) to a 185 km orbit at 28.00 degrees in 1985 dollars. Flyaway Unit Cost $: 387.440 million.

Stage Data - Saturn INT-18

  • Stage 0. 4 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 II. Gross Mass: 490,778 kg (1,081,980 lb). Empty Mass: 39,048 kg (86,086 lb). Thrust (vac): 5,165.790 kN (1,161,316 lbf). Isp: 421 sec. Burn time: 390 sec. Isp(sl): 200 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 24.84 m (81.49 ft). Propellants: Lox/LH2. No Engines: 5. Engine: J-2. 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: 1,966,810 kg (4,336,070 lb).
Payload: 66,590 kg (146,800 lb).
Height: 51.00 m (167.00 ft).
Diameter: 10.06 m (33.00 ft).
Thrust: 25,642.10 kN (5,764,573 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • 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 V America's booster for the Apollo manned lunar landing. The design was frozen before a landing mode was selected; the Saturn V could be used for either Earth-Orbit-Rendezvous or Lunar-Orbit-Rendezvous methods. The vehicle ended up with the same payload capability as the 'too large' Nova. The basic diameter was dictated by the ceiling height at the Michoud factory selected for first stage manufacture. Despite the study of innumerable variants, production was ended after only 12 were built and America spent the next fifty years in a pointless slow-motion withdrawal from manned space exploration. More...

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

Associated Stages
  • Saturn II Lox/LH2 propellant rocket stage. Loaded/empty mass 490,778/39,048 kg. Thrust 5,165.79 kN. Vacuum specific impulse 421 seconds. Configuration as flown. 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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