About: Saturn II

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The Saturn II was a series of American expendable launch vehicles, studied by North American Aviation under NASA contract in 1966, derived from the Saturn V rocket used for the Apollo lunar program. 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.

Attributes	Values
rdf:type	Thing mean of transportation Rocket rocket yago:Artifact100021939 yago:Conveyance103100490 yago:Instrumentality103575240 yago:Object100002684 yago:PhysicalEntity100001930 television show yago:Rocket104099429 yago:Vehicle104524313 yago:Whole100003553
rdfs:label	Saturn II (en)
rdfs:comment	The Saturn II was a series of American expendable launch vehicles, studied by North American Aviation under NASA contract in 1966, derived from the Saturn V rocket used for the Apollo lunar program. 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. (en)
foaf:name	Saturn II (en)
name	Saturn II (en)
foaf:depiction
dcterms:subject	Saturn (rocket family)
Wikipage page ID	6597242 (xsd:integer)
Wikipage revision ID	1106908849 (xsd:integer)
Link from a Wikipage to another Wikipage	Rocketdyne J-2 Saturn IB Saturn INT-20 Saturn INT-21 Saturn V Boeing Apollo Applications Program LH2 S-IB S-IC S-II S-IVB Chrysler NASA Apollo program Launch vehicle Liquid oxygen Ammonium perchlorate composite propellant North American Aviation Titan (rocket family) HG-3 (rocket engine) Atlas (rocket family) UA120 Solid Rocket Booster Saturn (rocket family) Kennedy Space Center Kennedy Space Center Launch Complex 39 LGM-30 Minuteman Douglas Aircraft Company Marshall Space Flight Center Martin Marietta Space Shuttle Solid rocket booster Saturn (rocket family) Expansion ratio Expendable launch system Impulse (physics) Low Earth orbit Titan (rocket)
Link from a Wikipage to an external page	https://web.archive.org/web/20020524194507/http:/www.astronautix.com/stages/saturnii.htm https://web.archive.org/web/20020829020423/http:/astronautix.com/lvs/satint19.htm https://web.archive.org/web/20020829022406/http:/astronautix.com/lvs/satint17.htm https://web.archive.org/web/20060614175128/http:/astronautix.com/data/satvint.pdf https://web.archive.org/web/20110924082505/http:/www.astronautix.com/lvs/satint18.htm
sameAs	Saturn II Saturn II Saturn II
sites	Kennedy Space Center Kennedy Space Center Launch Complex 39
dbp:wikiPageUsesTemplate	dbt:About dbt:Convert dbt:Reflist dbt:Short_description dbt:Ubl dbt:Infobox_rocket/Stage dbt:Infobox_rocket/stage dbt:Infobox_rocket dbt:Infobox_rocket/Payload dbt:Saturns
thumbnail	wiki-commons:Special:FilePath/Saturn_II.svg?width=300
caption	Saturn II proposals: INT-17, INT-18, INT-19. (en)
family	Saturn (rocket family)
manufacturer	North American Aviation Douglas (en)
status	Study 1966 (en)
stages	2 (xsd:integer)
has abstract	The Saturn II was a series of American expendable launch vehicles, studied by North American Aviation under NASA contract in 1966, derived from the Saturn V rocket used for the Apollo lunar program. 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. (en)
country-origin	United States (en)
function	Orbital launch vehicle (en)
launches	0 (xsd:integer)
launch site	Kennedy Space Center
rocket function	Launch vehicle
gold:hypernym	Series
prov:wasDerivedFrom	wikipedia-en:Saturn_II?oldid=1106908849&ns=0
diameter (μ)	10.0584 (metre)
height (mm)	50901.6 (millimetre)
page length (characters) of wiki page	15989 (xsd:nonNegativeInteger)
diameter (μ)	10.058400 (xsd:double)
height (μ)	50.901600 (xsd:double)

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