Encyclopedia Astronautica
Saturn INT-19



sat2mm.gif
Saturn 2SL Minuteman
Saturn 2SL Minuteman strapons
Credit: © Mark Wade
sat2mm4.gif
Saturn 2 w MM SO
Credit: © Mark Wade
North American study, 1966. Saturn variant with 4 to 12 Minuteman motors as boosters, Saturn II stage as core, and Saturn IVB upper stage. Saturn II stage would be fitted with lower expansion ratio engines and would ignite at sea level. Various combinations of numbers of strap-ons, propellant loading of the two core stages were studied.

Liftoff Mass - kgMM Motors at LiftoffMM Motors 2nd RoundMM Motors 3rd RoundS-II Propellant - kgS-IVB Propellant - kgPayload - kg
328,300---188,20077,1005,500
463,50022-217,70080,30013,200
579,60042-277,60076,60020,100
579,60044-236,70073,00018,100
722,90062-367,80076,60027,200
722,90064-318,40078,00026,800
734,200642294,80081,20023,100
722,90066-273,90078,90025,400
866,70084-410,90080,70028,800
866,70084-410,90075,70033,700
866,70084-410,90075,20034,200

LEO Payload: 34,320 kg (75,660 lb) to a 185 km orbit at 28.00 degrees.

Stage Data - Saturn INT-19

  • Stage 0. 12 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 II-SL. Gross Mass: 490,952 kg (1,082,363 lb). Empty Mass: 44,240 kg (97,530 lb). Thrust (vac): 5,500.765 kN (1,236,621 lbf). Isp: 390 sec. Burn time: 310 sec. Isp(sl): 275 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-SL. Status: Study 1966. Comments: Saturn II modifed with reduced expansion ratio J-2 engines for use a first stage (sea level launch). Requires solid rocket motor augmentation to get off the ground.
  • 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: 770,000 kg (1,690,000 lb).
Payload: 34,320 kg (75,660 lb).
Height: 51.00 m (167.00 ft).
Diameter: 10.06 m (33.00 ft).
Thrust: 9,061.41 kN (2,037,086 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • J-2-SL Rocketdyne lox/lh2 rocket engine. 996.7 kN. Study 1966. Sea level version of J-2 with reduced expansion ratio proposed for Saturn II first stage use. Isp=390s. 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 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
  • 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 II-SL Lox/LH2 propellant rocket stage. Loaded/empty mass 490,952/44,240 kg. Thrust 5,500.77 kN. Vacuum specific impulse 390 seconds. Saturn II modifed with reduced expansion ratio J-2 engines for use a first stage (sea level launch). Requires solid rocket motor augmentation to get off the ground. 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...

Home - Browse - Contact
© / Conditions for Use