This article is about the rocket. For the moon of Saturn, see Enceladus. For the Saturn V stage, see S-II.
Saturn II
Saturn II proposals: INT-17, INT-18, INT-19.
Function
Orbital launch vehicle
Manufacturer
North American (S-II) Douglas (S-IVB)
Country of origin
United States
Size
Height
167 feet (51 m)
Diameter
33 feet (10 m)
Mass
1,112,000 to 4,178,200 pounds (504,400 to 1,895,200 kg)
Stages
2
Capacity
Payload to LEO (100 nmi (185 km), 28° inclination)
Mass
47,000 to 146,400 pounds (21,300 to 66,400 kg)
Associated rockets
Family
Saturn
Derivative work
INT-17
INT-18
INT-19
Launch history
Status
Study 1966
Launch sites
Kennedy Space Center Launch Complex 39,
Total launches
0
Boosters (INT-18) – UA1207
No. boosters
2 or 4
Powered by
1
Maximum thrust
1,600,000 lbf (7,100 kN) SL
Total thrust
3,200,000 lbf (14,000 kN) or 6,400,000 lbf (28,000 kN) SL
Specific impulse
272 seconds SL
Burn time
120 seconds
Propellant
APCP
First stage (INT-17) – S-II–INT-17
Height
81.49 feet (24.84 m)
Diameter
33.0 feet (10.1 m)
Empty mass
105,000 pounds (48,000 kg)[note 1]
Gross mass
1,091,000 pounds (495,000 kg)[note 1]
Powered by
7 HG-3-SL
Maximum thrust
1,334,000 lbf (5,930 kN) SL
Specific impulse
275 seconds (2.70 km/s) SL
450 seconds (4.4 km/s) vac
Burn time
200 seconds
Propellant
LH2 / LOX
First stage (INT-18) – S-II
Height
81.49 feet (24.84 m)
Diameter
33.0 feet (10.1 m)
Empty mass
86,090 pounds (39,050 kg)[note 1]
Gross mass
1,082,000 pounds (491,000 kg)[note 1]
Powered by
5 Rocketdyne J-2
Maximum thrust
551,700 lbf (2,454 kN) SL
1,161,300 lbf (5,166 kN) vac
Specific impulse
200 seconds (2.0 km/s) SL
421 seconds (4.13 km/s) vac
Burn time
390 seconds
Propellant
LH2 / LOX
Second stage – S-IVB-200
Height
58.3 feet (17.8 m)
Diameter
21.68 feet (6.61 m)
Empty mass
28,400 pounds (12,900 kg)[note 2]
Gross mass
261,900 pounds (118,800 kg)[note 2]
Powered by
1 Rocketdyne J-2
Maximum thrust
231,900 lbf (1,032 kN) vac
Specific impulse
421 seconds (4.13 km/s) vac
Burn time
475 seconds
Propellant
LH2 / LOX
[edit on Wikidata]
The Saturn II was a series of American expendable launch vehicles, studied by North American Aviation under a NASA contract in 1966, derived from the Saturn V rocket used for the Apollo lunar program.[1] The intent of the study was to eliminate production of the Saturn IB, and create a lower-cost heavy launch vehicle based on Saturn V hardware. North American studied three versions with the S-IC first stage removed: the INT-17, a two-stage vehicle with a low Earth orbit payload capability of 47,000 pounds (21,000 kg); the INT-18, which added Titan UA1204 or UA1207 strap-on solid rocket boosters, with payloads ranging from 47,000 pounds (21,000 kg) to 146,400 pounds (66,400 kg); and the INT-19, using solid boosters derived from the Minuteman missile first stage.
For this study, the Boeing company also investigated configurations designated INT-20 and INT-21 which employed its S-IC first stage, and eliminated either North American's S-II second stage, or the Douglas S-IVB third stage. Budget constraints led to cancellation of the study and exclusive use of the Space Shuttle for orbital payloads.
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^Final Report - Studies of Improved Saturn V Vehicles and Intermediate Payload Vehicles (P-115)(PDF). Boeing Space Division. October 1966. Archived from the original (PDF) on 2006-06-14.
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