Encyclopedia Astronautica
Saturn INT-05A



satint5a.gif
Saturn IB-INT-5A
Credit: © Mark Wade
satint5b.gif
Saturn IB-INT-5B
Credit: © Mark Wade
American orbital launch vehicle. UA Study, 1965: Full length 260 inch solid motor with S-IVB upper stage.

LEO Payload: 43,034 kg (94,873 lb) to a 185 km orbit at 28.00 degrees in 1985 dollars. Flyaway Unit Cost $: 111.650 million.

Stage Data - Saturn INT-05A

  • Stage 1. 1 x 260 inch solid FL. Gross Mass: 1,648,355 kg (3,634,000 lb). Empty Mass: 156,126 kg (344,198 lb). Thrust (vac): 35,391.395 kN (7,956,302 lbf). Isp: 263 sec. Burn time: 114 sec. Isp(sl): 238 sec. Diameter: 6.60 m (21.60 ft). Span: 6.60 m (21.60 ft). Length: 30.48 m (99.99 ft). Propellants: Solid. No Engines: 1. Engine: AJ-260X. Status: Study 1968. Comments: 260 inch solid booster - full length. These would have been the flight configuration motors, replacing the Saturn V first stage or being used as booster motors in various Uprated Saturn and Nova configurations.
  • 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 1965.
Gross mass: 1,818,800 kg (4,009,700 lb).
Payload: 43,034 kg (94,873 lb).
Height: 58.00 m (190.00 ft).
Diameter: 6.61 m (21.68 ft).
Thrust: 32,027.10 kN (7,199,979 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • AJ-260-1/3 Aerojet solid rocket engine. 10,105 kN. Design concept 1960's. Isp=275s. Used on Saturn INT-05B launch vehicle. More...
  • AJ-260X Aerojet solid rocket engine. 35,390.7 kN. Study 1967. Full length version of 260 inch motor tested in 1960's. Proposed for use in various Saturn and Nova configurations. Isp=263s. 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
  • 260 inch solid FL Solid propellant rocket stage. Loaded/empty mass 1,648,355/156,126 kg. Thrust 35,391.40 kN. Vacuum specific impulse 263 seconds. 260 inch solid booster - full length. These would have been the flight configuration motors, replacing the Saturn V first stage or being used as booster motors in various Uprated Saturn and Nova configurations. 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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