Q1093699: Difference between revisions
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{{Page|S-II|Classes|second stage of the Saturn V rocket}} | {{Page|S-II|Classes|second stage of the Saturn V rocket|}} | ||
Latest revision as of 12:55, 17 February 2025
The S-II (pronounced "S-two") was the second stage of the Saturn V rocket. It was built by North American Aviation. Using liquid hydrogen (LH2) and liquid oxygen (LOX) it had five J-2 engines in a quincunx pattern. The second stage accelerated the Saturn V through the upper atmosphere with 1,000,000 pounds-force (4.4 MN) of thrust.
Wikimedia, Wikidata
height 24.84 metre, mass 35356 kilogram, mass 375826 kilogram, mass 493536 kilogram, mass 72001 kilogram, mass 471114 kilogram, mass 40143 kilogram, diameter 10.06 metre, maximum thrust 1150000 pound-force,
North American Aviation, United States,
United States, Ashkenaz, Calvinist Republic of Ghent, Chinland, Democratic Republic of the Congo, Havilah, Kingdom of Martabam-hongsawatoi, Kingdom of Wolaita, Persia, Sikh Confederacy, Tarshish, Dong Fang Hong 2, Ekran, Republic of Haiti,
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Location: KML, Cluster Map, Maps,
Two technicians apply insulation to the outer surface of the S-II second stage booster for the Saturn V moon rocket. The towering 363-foot Saturn V was a multi-stage, multi-engine launch vehicle standing taller than the Statue of Liberty.







