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Statements

Subject Item
dbr:Rocketdyne_J-2
dbo:wikiPageWikiLink
dbr:HG-3_(rocket_engine)
dbp:successor
dbr:HG-3_(rocket_engine)
Subject Item
dbr:Saturn_II
dbo:wikiPageWikiLink
dbr:HG-3_(rocket_engine)
Subject Item
dbr:Saturn_MLV
dbo:wikiPageWikiLink
dbr:HG-3_(rocket_engine)
Subject Item
dbr:Saturn_V-3
dbo:wikiPageWikiLink
dbr:HG-3_(rocket_engine)
Subject Item
dbr:Aerojet_M-1
dbo:wikiPageWikiLink
dbr:HG-3_(rocket_engine)
Subject Item
dbr:HG-3_(rocket_engine)
rdf:type
yago:Reaction-propulsionEngine104057435 yago:Rocket104099175 yago:Motor103789946 yago:WikicatRocketEnginesUsingHydrogenPropellant yago:JetEngine103596285 yago:Engine103287733 yago:Artifact100021939 yago:PhysicalEntity100001930 yago:Whole100003553 yago:WikicatRocketdyneEngines yago:Object100002684 yago:Machine103699975 yago:Device103183080 yago:Instrumentality103575240 dbo:Software
rdfs:label
HG-3 (ロケットエンジン) HG-3 (rocket engine) HG-3 (motor de foguete)
rdfs:comment
HG-3は、アポロ計画の後にサターンロケットの上段用として設計された極低温液体燃料ロケットエンジンである。 アメリカのロケットダイン社によって設計されたHG-3は極低温の液体水素と液体酸素を推進剤として燃焼し、飛行中にそれぞれのエンジンの推力は1,400.7 kN (315,000 lbf)を生み出す。エンジンの比推力(Isp)は真空中で451秒または海面高度で280秒である 。、とロケットで使用する予定の改良型のとで使用するために、S-IIとS-IVBで使用されたロケットダイン社のJ-2ロケットエンジンを元に設計された。また、のために海面高度に最適化されたHG-3-SLが設計された。 アポロ計画後に進行していたサターンロケットの改良版開発が中止されたことで、HG-3の開発も中止されたが、後にスペースシャトル主エンジン(RS-25)の設計の原型として使用された。 The HG-3 was a liquid-fuel cryogenic rocket engine which was designed for use on the upper stages of Saturn rockets in the post-Apollo era. Designed in the United States by Rocketdyne, the HG-3 was to have burned cryogenic liquid hydrogen and liquid oxygen propellants, with each engine producing 1,400.7 kN (315,000 lbf) of thrust during flight. The engine was designed to produce a specific impulse (Isp) of 451 seconds (4.42 km/s) in a vacuum, or 280 seconds (2.7 km/s) at sea level. Developed from Rocketdyne's J-2 engine used on the S-II and S-IVB stages, the engine was intended to replace the J-2 on the upgraded S-II-2 and S-IVB-2 stages intended for use on the Saturn MLV, Saturn IB-B and Saturn V/4-260 rockets, with a sea-level optimised version, the HG-3-SL, intended for use on the Satur O HG-3 é um motor de foguete de combustível líquido , que foi projetado para uso nos estágios superiores dos foguetes Saturno depois do Programa Apollo. Projetado nos Estados Unidos pela Rocketdyne, o HG-3 deveria queimar uma combinação criogênica de hidrogênio líquido e oxigênio líquido como propelentes, com cada motor produzindo 1.400,7 kN de empuxo durante o voo. O motor foi projetado para gerar um impulso específico (Isp) de 451 segundos no vácuo ou 280 segundos ao nível do mar.
dbp:name
HG-3
dcterms:subject
dbc:Rocketdyne_engines dbc:Rocket_engines_of_the_United_States dbc:Rocket_engines_using_hydrogen_propellant
dbo:wikiPageID
34785687
dbo:wikiPageRevisionID
1068534288
dbo:wikiPageWikiLink
dbr:Saturn_(rocket_family) dbc:Rocket_engines_of_the_United_States dbc:Rocketdyne_engines dbr:Saturn_II dbr:Upper_stage dbr:J-2_(rocket_engine) dbr:Liquid-fuel_rocket dbr:Saturn_IB-B dbc:Rocket_engines_using_hydrogen_propellant dbr:Saturn_MLV dbr:United_States dbr:Marshall_Space_Flight_Center dbr:Rocketdyne dbr:Specific_impulse dbr:Cryogenic_fuel dbr:Liquid_oxygen dbr:J-2X dbr:Apollo_program dbr:RS-25 dbr:Cryogenic_rocket_engine dbr:Thrust dbr:S-II dbr:Liquid_hydrogen dbr:S-IVB
owl:sameAs
n8:4kDdr freebase:m.0j3c7dj dbpedia-ja:HG-3_(ロケットエンジン) wikidata:Q5629533 yago-res:HG-3_(rocket_engine) dbpedia-pt:HG-3_(motor_de_foguete)
dbp:wikiPageUsesTemplate
dbt:Rocketry-stub dbt:Short_description dbt:Convert dbt:Infobox_rocket_engine dbt:Reflist
dbp:countryOfOrigin
dbr:United_States
dbp:designer
dbr:Rocketdyne dbr:Marshall_Space_Flight_Center
dbp:fuel
dbr:Liquid_hydrogen
dbp:manufacturer
dbr:Rocketdyne
dbp:oxidiser
dbr:Liquid_oxygen
dbp:predecessor
dbr:J-2_(rocket_engine)
dbp:purpose
Upper stage engine
dbp:status
Canceled
dbp:successor
dbr:RS-25
dbp:type
liquid
dbo:abstract
O HG-3 é um motor de foguete de combustível líquido , que foi projetado para uso nos estágios superiores dos foguetes Saturno depois do Programa Apollo. Projetado nos Estados Unidos pela Rocketdyne, o HG-3 deveria queimar uma combinação criogênica de hidrogênio líquido e oxigênio líquido como propelentes, com cada motor produzindo 1.400,7 kN de empuxo durante o voo. O motor foi projetado para gerar um impulso específico (Isp) de 451 segundos no vácuo ou 280 segundos ao nível do mar. The HG-3 was a liquid-fuel cryogenic rocket engine which was designed for use on the upper stages of Saturn rockets in the post-Apollo era. Designed in the United States by Rocketdyne, the HG-3 was to have burned cryogenic liquid hydrogen and liquid oxygen propellants, with each engine producing 1,400.7 kN (315,000 lbf) of thrust during flight. The engine was designed to produce a specific impulse (Isp) of 451 seconds (4.42 km/s) in a vacuum, or 280 seconds (2.7 km/s) at sea level. Developed from Rocketdyne's J-2 engine used on the S-II and S-IVB stages, the engine was intended to replace the J-2 on the upgraded S-II-2 and S-IVB-2 stages intended for use on the Saturn MLV, Saturn IB-B and Saturn V/4-260 rockets, with a sea-level optimised version, the HG-3-SL, intended for use on the Saturn INT-17. The engine was cancelled, however, during the post-Apollo drawdown when development of the more advanced Saturn rockets ceased, and never flew, although the engine was later used as the basis for the design of the RS-25 engine. HG-3は、アポロ計画の後にサターンロケットの上段用として設計された極低温液体燃料ロケットエンジンである。 アメリカのロケットダイン社によって設計されたHG-3は極低温の液体水素と液体酸素を推進剤として燃焼し、飛行中にそれぞれのエンジンの推力は1,400.7 kN (315,000 lbf)を生み出す。エンジンの比推力(Isp)は真空中で451秒または海面高度で280秒である 。、とロケットで使用する予定の改良型のとで使用するために、S-IIとS-IVBで使用されたロケットダイン社のJ-2ロケットエンジンを元に設計された。また、のために海面高度に最適化されたHG-3-SLが設計された。 アポロ計画後に進行していたサターンロケットの改良版開発が中止されたことで、HG-3の開発も中止されたが、後にスペースシャトル主エンジン(RS-25)の設計の原型として使用された。
dbp:associated
dbr:Saturn_MLV dbr:Saturn_IB-B Saturn V/4-260 dbr:Saturn_II
gold:hypernym
dbr:Engine
prov:wasDerivedFrom
wikipedia-en:HG-3_(rocket_engine)?oldid=1068534288&ns=0
dbo:wikiPageLength
4005
foaf:isPrimaryTopicOf
wikipedia-en:HG-3_(rocket_engine)
Subject Item
dbr:J-2X
dbo:wikiPageWikiLink
dbr:HG-3_(rocket_engine)
Subject Item
dbr:Saturn_IB-B
dbo:wikiPageWikiLink
dbr:HG-3_(rocket_engine)
Subject Item
dbr:RS-25
dbo:wikiPageWikiLink
dbr:HG-3_(rocket_engine)
dbp:predecessor
dbr:HG-3_(rocket_engine)
Subject Item
dbr:Expanding_nozzle
dbo:wikiPageWikiLink
dbr:HG-3_(rocket_engine)
Subject Item
wikipedia-en:HG-3_(rocket_engine)
foaf:primaryTopic
dbr:HG-3_(rocket_engine)