Draft:Saturn INT-05
{{infobox rocket |function = Launch vehicle for Apollo |manufacturer = |country-origin = United States |height = 190 feet (58 m) (w/o payload) |diameter = 21.68 feet (6.61 m) |mass = 4,009,700 pounds (1,818,800 kg) gross (to LEO) |stages = |capacities =
Payload to LEOMass94,873 pounds (43,034 kg)
|family = Saturn |status = Study, not developed |sites = Kennedy Space Center |payloads = |stagedata =
First stage – AJ-260XHeight99.99 feet (30.48 m)Diameter21.6 feet (6.6 m)Empty mass334,198 pounds (151,590 kg)Gross mass3,634,000 pounds (1,648,000 kg)Powered by1 AJ-260XMaximum thrust[convert: invalid number]Specific impulse289 secsBurn time114 secondsPropellantSolid Second stage – S-IVBHeight58.3 feet (17.8 m)Diameter21.68 feet (6.61 m)Empty mass28,400 pounds (12,900 kg)Gross mass261,900 pounds (118,800 kg)Powered by1 J-2Maximum thrust[convert: invalid number]Specific impulse200 secBurn time475 secondsPropellantLH2 / LOX
The Saturn INT-05 was a concept rocket studied by NASA. It took the form of a Saturn I-b with the S-Ib stage replaced by a 260 inch (6.6 meter) solid rocket motor.
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