About: J-2X

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The J-2X is a liquid-fueled cryogenic rocket engine that was planned for use on the Ares rockets of NASA's Constellation program, and later the Space Launch System. Built in the United States by Aerojet Rocketdyne (formerly, Pratt & Whitney Rocketdyne), the J-2X burns cryogenic liquid hydrogen and liquid oxygen propellants, with each engine producing 1,307 kN (294,000 lbf) of thrust in vacuum at a specific impulse (Isp) of 448 seconds (4.39 km/s). The engine's mass is approximately 2,470 kg (5,450 Lb), significantly heavier than its predecessors.

Attributes	Values
rdf:type	software yago:WikicatRocketEngines yago:WikicatRocketEnginesUsingHydrogenPropellant yago:WikicatRocketdyneEngines yago:Artifact100021939 yago:Device103183080 yago:Engine103287733 yago:Instrumentality103575240 yago:JetEngine103596285 yago:Machine103699975 yago:Motor103789946 yago:Object100002684 yago:PhysicalEntity100001930 yago:Reaction-propulsionEngine104057435 yago:Rocket104099175 yago:Whole100003553
rdfs:label	J-2X (en) J-2X (ja) J-2X (silnik rakietowy) (pl) J-2X (pt)
rdfs:comment	J-2X – silnik rakietowy opracowany i zbudowany przez Pratt & Whitney Rocketdyne dla NASA z przeznaczeniem dla wyższych stopni ciężkich rakiet nośnych NASA. Silnik J-2X wywodzi się z silnika J-2, który był używany w rakietach Saturn IB i Saturn V w ramach programu Apollo. (pl) O J-2X é um motor de foguete de combustível líquido , que foi planejado para uso nos foguetes Ares do Projeto Constellation da NASA, e mais tarde para o Space Launch System. Construído nos Estados Unidos pela Aerojet Rocketdyne (anteriormente, Pratt & Whitney Rocketdyne), o J-2X queima uma mistura criogênica de hidrogênio líquido e oxigênio líquido como propelentes, cada motor produzindo 1.307 kN de empuxo no vácuo gerando um impulso específico (Isp) de 448 (4.39 km/s). A massa do motor é de aproximadamente 2.470 kg, significativamente mais pesado que seus antecessores. (pt) The J-2X is a liquid-fueled cryogenic rocket engine that was planned for use on the Ares rockets of NASA's Constellation program, and later the Space Launch System. Built in the United States by Aerojet Rocketdyne (formerly, Pratt & Whitney Rocketdyne), the J-2X burns cryogenic liquid hydrogen and liquid oxygen propellants, with each engine producing 1,307 kN (294,000 lbf) of thrust in vacuum at a specific impulse (Isp) of 448 seconds (4.39 km/s). The engine's mass is approximately 2,470 kg (5,450 Lb), significantly heavier than its predecessors. (en) J-2Xはアメリカのエアロジェット・ロケットダイン (旧: プラット・アンド・ホイットニー・ロケットダイン) が開発した極低温液体燃料ロケットエンジンで、NASAのコンステレーション計画において打ち上げ機として開発されたアレスロケットのエンジンに採用される予定だった。J-2Xは液水/液酸エンジンで、真空中推力 1,307 kN (294,000 lbf)、比推力 (Isp) 448秒 (4.39 km/s)を発揮する。エンジン重量は約2,470 kg(5,450Lb)で、原型となったJ-2よりも重くなっている。 (ja)
name	J-2X (en)
foaf:depiction
dcterms:subject	Rocket engines of the United States Rocket engines using the gas-generator cycle Rocketdyne engines Rocket engines using hydrogen propellant Space Launch System
Wikipage page ID	5846760 (xsd:integer)
Wikipage revision ID	1110300518 (xsd:integer)
Link from a Wikipage to another Wikipage	Beryllium Powerpack (rocket engine) Constellation program S-II S-IVB Gas generator M-1 (rocket engine) NASA Cryogenic fuel Cryogenic rocket engine Apollo program Liquid hydrogen Gas-generator cycle (rocket) Pratt & Whitney Rocketdyne Rocket engines of the United States Rocket engines using the gas-generator cycle Rocketdyne engines Liquid oxygen Earth Departure Stage Exploration Upper Stage Hancock County, Mississippi HG-3 (rocket engine) Ares I Ares V Aerojet Rocketdyne Rocket engines using hydrogen propellant John C. Stennis Space Center Thrust Space Launch System Space Launch System RL10 RS-25 RS-68 Specific impulse Saturn (rocket family) Upper stage Liquid-fuel rocket J-2 (rocket engine)
Link from a Wikipage to an external page	https://web.archive.org/web/20140826172627/http:/rocket.com/j-2x-engine
sameAs	J-2X J-2X J-2X J-2X J-2X J-2X J-2X J-2X J-2X
thrust to weight	55.040000 (xsd:double)
dbp:wikiPageUsesTemplate	dbt:J-2_(rocket_engine) dbt:Commons_category dbt:Convert dbt:Frac dbt:Infobox_rocket_engine dbt:Reflist dbt:Rocket_engines dbt:Project_Constellation
thumbnail	wiki-commons:Special:FilePath/J-2X.jpg?width=300
caption	A computer rendering of a J-2X. (en)
country of origin	United States (en)
cycle	Gas-generator cycle (rocket)
fuel	Liquid hydrogen
image size	200 (xsd:integer)

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