About: S-II

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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.

Attributes	Values
rdf:type	person yago:WikicatRocketStages yago:Abstraction100002137 yago:FundamentalQuantity113575869 yago:Measure100033615 yago:Phase115290337 yago:TimePeriod115113229
rdfs:label	S-II (fr) S-II (ja) S-II (pl) S-II (en) S-II (ru) S-II (estágio de foguete) (pt) S-II (zh)
rdfs:comment	Le S-II était le deuxième étage du lanceur américain Saturn V, chargé de lancer les vaisseaux habités des missions lunaires du programme Apollo. Il a été construit par North American Aviation. Utilisant de l'hydrogène liquide (LH2) et de l'oxygène liquide (LOX), cet étage propulsait Saturn V dans la haute atmosphère grâce à la poussée cumulée de 4 400 kN que produisaient ses cinq moteurs J-2, disposés en croix. (fr) 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. (en) S-II（英語ではエス・ツーと発音される）は、アメリカ合衆国のアポロ計画で使用されたサターンV 型ロケットの、第二段ロケットである。ノース・アメリカン社製作。燃料に液体水素、酸化剤に液体酸素を使用するJ-2ロケットエンジンを5基搭載し、520トン（5MN）の推力でサターンV を大気圏上層部にまで到達させた。 (ja) S-II (lub S-2, wym. Es tu): stopień rakietowy wykorzystywany przez NASA dla rakiet Saturn V. (pl) S-II — американская ракетная ступень. Использовалась на ракете-носителе Сатурн V как вторая ступень, работала на участке выведения в верхних слоях атмосферы. Производитель — North American Aviation. Горючее — жидкий водород, окислитель — жидкий кислород. Тяга — 5 МН. (ru) O S-II, foi um estágio de foguete movido a combustíveis líquidos,nesse caso, LH-2 como combustível e LOX como oxidante, e era usado como segundo estágio no foguete Saturno V. O S-II foi produzido pela North American, e usava cinco motores J-2. Tinha 24,9 metros de altura e 10 metros de diâmetro, gerando 5.115 kN de empuxo inicial, acelerando o foguete até a atmosfera superior. Dos cinco motores, um ficava fixo no centro,e os demais eram controlados por eixos hidráulicos para dar direção ao foguete. (pt) S-II（读作“S-two”）是土星五号的第二级，由北美航空制造。该级由五台J-2液氢液氧发动机驱动，在高层大气中提供给火箭5 MN的推力。 (zh)
name	S-II (en)
foaf:depiction
dcterms:subject	Apollo program Rocket stages
Wikipage page ID	572843 (xsd:integer)
Wikipage revision ID	1122175963 (xsd:integer)
Link from a Wikipage to another Wikipage	California Rocketdyne J-2 Saturn INT-21 Saturn V Apollo (spacecraft) Huntsville, Alabama Johnson Space Center Vehicle Assembly Building LH2 S-IC S-IV S-IVB Ellipsoid NASA Apollo 10 Apollo 11 Apollo 12 Apollo 13 Apollo 14 Apollo 15 Apollo 16 Apollo 17 Apollo 4 Apollo 6 Apollo 8 Apollo 9 Liquid hydrogen MS-II Phenolic resin Pogo oscillation Apollo program Tonne U.S. Space & Rocket Center Gimbal Liquid oxygen Aluminium North American Aviation Gore (segment) Quincunx Rocket stages Kennedy Space Center Marshall Space Flight Center Apollo Command/Service Module Apollo-Saturn V Center Skylab 1 Explosive forming Rocketdyne J-2 (rocket engine) Seal Beach
Link from a Wikipage to an external page	https://history.nasa.gov/SP-4206/sp4206.htm http://www.apollosaturn.com/
sameAs	S-II S-II S-II S-II S-II S-II S-II S-II S-II S-II S-II S-II S-II
dbp:wikiPageUsesTemplate	dbt:J-2_(rocket_engine) dbt:Citation_needed dbt:Cite_book dbt:Convert dbt:Coord

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