Rocketdyne H-1 (original) (raw)
H-1 byl raketový motor na kapalné pohonné látky používaný na prvním stupni raket Saturn I a Saturn IB. Navrhla a vyráběla jej firma Rocketdyne, dnes divize společnosti Pratt & Whitney. Konstrukčně navazuje na motor , vyvinutý v padesátých letech a používaný na balistických raketách Thor a Jupiter. H-1 byl používán vždy ve svazku osmi motorů, v takzvaném Clusteru. Jako palivo sloužil vysoce rafinovaný petrolej RP-1 a jako okysličovadlo kapalný kyslík.
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| dbo:abstract | H-1 byl raketový motor na kapalné pohonné látky používaný na prvním stupni raket Saturn I a Saturn IB. Navrhla a vyráběla jej firma Rocketdyne, dnes divize společnosti Pratt & Whitney. Konstrukčně navazuje na motor , vyvinutý v padesátých letech a používaný na balistických raketách Thor a Jupiter. H-1 byl používán vždy ve svazku osmi motorů, v takzvaném Clusteru. Jako palivo sloužil vysoce rafinovaný petrolej RP-1 a jako okysličovadlo kapalný kyslík. (cs) Le H-1 est un moteur-fusée de 900 kN (91 tonnes) de poussée, développé à la fin des années 1950 par le motoriste américain Rocketdyne. Brûlant un mélange de RP-1 (un type de kérosène très raffiné) et d'oxygène liquide, il a été utilisé sur le premier étage des fusées Saturn I et Saturn IB, sur lesquelles étaient installés huit moteurs de ce type pour propulser une masse d'environ 600 tonnes pour le lanceur le plus lourd. (fr) Rocketdyne H-1 adalah roket mesin pembakaran cair-propelan LOX dan RP-1 daya dorong lbf 205.000 (910 kN) . H-1 dikembangkan untuk digunakan di tahap pertama S-IB roket Saturnus I dan Saturnus IB, di mana ia digunakan dalam kelompok delapan mesin. Setelah program Apollo, surplus H-1 mesinnya di rebranded dan reworked sebagai mesin Rocketdyne RS-27 dengan penggunaan pertama pada seri Delta 2000 pada tahun 1974. (in) The Rocketdyne H-1 was a 205,000 lbf (910 kN) thrust liquid-propellant rocket engine burning LOX and RP-1. The H-1 was developed for use in the S-I and S-IB first stages of the Saturn I and Saturn IB rockets, respectively, where it was used in clusters of eight engines. After the Apollo program, surplus H-1 engines were rebranded and reworked as the Rocketdyne RS-27 engine with first usage on the Delta 2000 series in 1974. The RS-27 variant is also used on the Delta II and Delta III. (en) Il Rocketdyne H-1 è un motore a razzo a propellente liquido alimentato a LOX e RP-1, capace di produrre 900 kN di spinta. È stato sviluppato per essere utilizzato negli stadi primari S-I ed S-IB dei Saturn I e Saturn IB, dove operava in un cluster di otto unità. Dopo il programma Apollo, i motori H-1 rimanenti vennero modificati e rinominati in Rocketdyne , che furono utilizzati nel 1974 nel primo stadio del lanciatore . (it) H-1 エンジンは推力200,000 lbf (890 kN)の液体酸素/RP-1を推進剤とするロケットエンジンで、ソーデルタロケットとジュピターロケットの1段目に使用された。簡略化してサターンIとサターンIBのS-IBに搭載された。サターンIBには8基が束ねられて使用された。後に推力が205,000 lbf (912 kN)まで増強された。H-1の経験はF-1エンジンの開発に役立てられた。 (ja) O H-1, foi um motor de foguete de alta performance, movido a combustíveis líquidos criogênicos, no caso, RP-1 e LOX, que foi usado nos foguetes Saturno I e Saturno IB. O H-1, construído pela Rocketdyne, gerava 910 kN. Nos foguetes Saturno 1 e Saturno 1B, eram usados em grupos de oito.Depois do Programa Apollo, motores H-1 que estavam em estoque, foram reformados e atualizados, gerando o motor ,usado no foguete Delta II. (pt) H-1是一种能产生200,000磅力（890kN）推力的液氧／RP-1火箭发动机，仅用于和的第一级。 它源自于，经过简化并改善后用于土星一号和土星一号B的第一级，所有的S-IB级都使用八台发动机组。 后来发动机推力增加到205,000磅力（912kN），优于用在土星五号的F-1。 H-1在使用之前通常要进行数次静态试验试车来调试性能，然而在飞行中却不能重新开始，因为发动机上用于重启动的元件是不可重用的。而且，发动机点火采用固体推进剂燃气发生器（SPGG），其实就是一枚小型的固体燃料火箭，每次点火后都要换上新的。 SPGG上使500V交流电压来点火固体推进剂，产生的高温气体达到600-700psi的压力，驱动涡轮泵工作。 高温气体也是点燃燃料／氧化剂混合物的初始能量，燃料一经点燃，就不再需要SPGG驱动，直至发动机停车。 (zh) |
| dbo:thumbnail | wiki-commons:Special:FilePath/20180328_H-1_engine_Udvar-Hazy.jpg?width=300 |
| dbo:wikiPageExternalLink | https://archive.org/details/vonbraundreamero00neuf https://history.nasa.gov/SP-4206/sp4206.htm%7Cpublisher=NASA%7Cseries=The https://web.archive.org/web/20041015005320/https:/history.nasa.gov/SP-4206/sp4206.htm%7Carchive-date=2004-10-15 https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19740021163_1974021163.pdf |
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| dbo:wikiPageLength | 15352 (xsd:nonNegativeInteger) |
| dbo:wikiPageRevisionID | 1124273236 (xsd:integer) |
| dbo:wikiPageWikiLink | dbr:Pound_(force) dbr:Pound_(mass) dbr:Pound_per_square_inch dbr:Rocketdyne_S-3D dbr:Saturn_I dbr:Saturn_IB dbr:Aerojet_General dbr:Delta_2000 dbr:Delta_II dbr:Delta_III dbr:US_Army dbr:V-2_rocket dbr:S-IB dbr:S-IVB dbr:SAE_International dbr:SM-64_Navaho dbr:SM-65_Atlas dbr:Gas_generator dbr:NASA dbr:Cruise_missile dbr:Kerosene dbr:Gas-generator_cycle_(rocket) dbc:Rocket_engines_of_the_United_States dbc:Rocket_engines_using_the_gas-generator_cycle dbc:Rocketdyne_engines dbr:Wernher_von_Braun dbr:Heinz-Hermann_Koelle dbr:Liquid-propellant_rocket dbr:DARPA dbr:Escape_velocity dbr:Ethanol dbr:North_American_Aviation dbr:PGM-11_Redstone dbr:PGM-17_Thor dbr:PGM-19_Jupiter dbr:Paint_thinner dbr:Ramjet dbr:HGM-25A_Titan_I dbc:North_American_Aviation dbr:Army_Ballistic_Missile_Agency dbc:Rocket_engines_using_kerosene_propellant dbr:JP-4 dbr:JP-5 dbr:Marshall_Space_Flight_Center dbr:Booster_(rocketry) dbr:Sputnik_1 dbr:RP-1 dbr:RS-27 dbr:Specific_impulse dbr:Diesel_oil dbr:LOX dbr:Low_Earth_orbit dbr:Turbopump dbr:Rocketdyne dbr:Rocketdyne_E-1 dbr:Pyrophoricity dbr:Saturn_1B dbr:Saturn_I_(rocket) dbr:J-2_(rocket_engine) dbr:Rocket_fuel dbr:Flight-qualify dbr:US_Department_of_Defense dbr:Jupiter_missile dbr:Udvar-Hazy_Center dbr:Titan_missile dbr:File:Arkansas_Air_&_Military_Museum_Ma...24_(Rocketdyne_H-1_rocket_engine).jpg dbr:File:Comparison_of_Rocketdyne_S-3D_and_H-1_engines.jpg dbr:File:H-1_rocket_engine_diagram.jpg dbr:File:Saturn_I_test_article.jpg |
| dbp:burnTime | 155.0 |
| dbp:caption | An H-1 engine at the Udvar-Hazy Center (en) |
| dbp:chamberPressure | 700 (xsd:integer) |
| dbp:combustionChamber | 1 (xsd:integer) |
| dbp:countryOfOrigin | United States (en) |
| dbp:cycle | dbr:Gas-generator_cycle_(rocket) |
| dbp:date | 1963 (xsd:integer) |
| dbp:diameter | 4.9 |
| dbp:dryWeight | 2200.0 |
| dbp:fuel | dbr:RP-1 |
| dbp:length | 8.8 |
| dbp:manufacturer | dbr:Rocketdyne |
| dbp:name | H-1 (en) |
| dbp:oxidiser | dbr:LOX |
| dbp:purpose | dbr:Booster_(rocketry) |
| dbp:status | Retired (en) |
| dbp:successor | dbr:RS-27 |
| dbp:thrust(sl)_ | 205000 (xsd:integer) |
| dbp:thrustToWeight | 102.470000 (xsd:double) |
| dbp:type | liquid (en) |
| dbp:usedIn | dbr:Saturn_I dbr:Saturn_1B |
| dbp:wikiPageUsesTemplate | dbt:Cite_book dbt:Convert dbt:Infobox_rocket_engine dbt:Reflist dbt:Rocket_engines dbt:Sfn dbt:Short_description dbt:Include-NASA |
| dcterms:subject | dbc:Rocket_engines_of_the_United_States dbc:Rocket_engines_using_the_gas-generator_cycle dbc:Rocketdyne_engines dbc:North_American_Aviation dbc:Rocket_engines_using_kerosene_propellant |
| gold:hypernym | dbr:Lbf |
| rdf:type | yago:WikicatRocketEngines 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:comment | H-1 byl raketový motor na kapalné pohonné látky používaný na prvním stupni raket Saturn I a Saturn IB. Navrhla a vyráběla jej firma Rocketdyne, dnes divize společnosti Pratt & Whitney. Konstrukčně navazuje na motor , vyvinutý v padesátých letech a používaný na balistických raketách Thor a Jupiter. H-1 byl používán vždy ve svazku osmi motorů, v takzvaném Clusteru. Jako palivo sloužil vysoce rafinovaný petrolej RP-1 a jako okysličovadlo kapalný kyslík. (cs) Le H-1 est un moteur-fusée de 900 kN (91 tonnes) de poussée, développé à la fin des années 1950 par le motoriste américain Rocketdyne. Brûlant un mélange de RP-1 (un type de kérosène très raffiné) et d'oxygène liquide, il a été utilisé sur le premier étage des fusées Saturn I et Saturn IB, sur lesquelles étaient installés huit moteurs de ce type pour propulser une masse d'environ 600 tonnes pour le lanceur le plus lourd. (fr) Rocketdyne H-1 adalah roket mesin pembakaran cair-propelan LOX dan RP-1 daya dorong lbf 205.000 (910 kN) . H-1 dikembangkan untuk digunakan di tahap pertama S-IB roket Saturnus I dan Saturnus IB, di mana ia digunakan dalam kelompok delapan mesin. Setelah program Apollo, surplus H-1 mesinnya di rebranded dan reworked sebagai mesin Rocketdyne RS-27 dengan penggunaan pertama pada seri Delta 2000 pada tahun 1974. (in) The Rocketdyne H-1 was a 205,000 lbf (910 kN) thrust liquid-propellant rocket engine burning LOX and RP-1. The H-1 was developed for use in the S-I and S-IB first stages of the Saturn I and Saturn IB rockets, respectively, where it was used in clusters of eight engines. After the Apollo program, surplus H-1 engines were rebranded and reworked as the Rocketdyne RS-27 engine with first usage on the Delta 2000 series in 1974. The RS-27 variant is also used on the Delta II and Delta III. (en) Il Rocketdyne H-1 è un motore a razzo a propellente liquido alimentato a LOX e RP-1, capace di produrre 900 kN di spinta. È stato sviluppato per essere utilizzato negli stadi primari S-I ed S-IB dei Saturn I e Saturn IB, dove operava in un cluster di otto unità. Dopo il programma Apollo, i motori H-1 rimanenti vennero modificati e rinominati in Rocketdyne , che furono utilizzati nel 1974 nel primo stadio del lanciatore . (it) H-1 エンジンは推力200,000 lbf (890 kN)の液体酸素/RP-1を推進剤とするロケットエンジンで、ソーデルタロケットとジュピターロケットの1段目に使用された。簡略化してサターンIとサターンIBのS-IBに搭載された。サターンIBには8基が束ねられて使用された。後に推力が205,000 lbf (912 kN)まで増強された。H-1の経験はF-1エンジンの開発に役立てられた。 (ja) O H-1, foi um motor de foguete de alta performance, movido a combustíveis líquidos criogênicos, no caso, RP-1 e LOX, que foi usado nos foguetes Saturno I e Saturno IB. O H-1, construído pela Rocketdyne, gerava 910 kN. Nos foguetes Saturno 1 e Saturno 1B, eram usados em grupos de oito.Depois do Programa Apollo, motores H-1 que estavam em estoque, foram reformados e atualizados, gerando o motor ,usado no foguete Delta II. (pt) H-1是一种能产生200,000磅力（890kN）推力的液氧／RP-1火箭发动机，仅用于和的第一级。 它源自于，经过简化并改善后用于土星一号和土星一号B的第一级，所有的S-IB级都使用八台发动机组。 后来发动机推力增加到205,000磅力（912kN），优于用在土星五号的F-1。 H-1在使用之前通常要进行数次静态试验试车来调试性能，然而在飞行中却不能重新开始，因为发动机上用于重启动的元件是不可重用的。而且，发动机点火采用固体推进剂燃气发生器（SPGG），其实就是一枚小型的固体燃料火箭，每次点火后都要换上新的。 SPGG上使500V交流电压来点火固体推进剂，产生的高温气体达到600-700psi的压力，驱动涡轮泵工作。 高温气体也是点燃燃料／氧化剂混合物的初始能量，燃料一经点燃，就不再需要SPGG驱动，直至发动机停车。 (zh) |
| rdfs:label | H-1 (cs) H-1 (mesin roket) (in) H-1 (moteur-fusée) (fr) H-1 (motore a razzo) (it) H-1 (ロケットエンジン) (ja) Rocketdyne H-1 (en) H-1 (motor de foguete) (pt) H-1火箭发动机 (zh) |
| owl:sameAs | freebase:Rocketdyne H-1 yago-res:Rocketdyne H-1 wikidata:Rocketdyne H-1 dbpedia-cs:Rocketdyne H-1 dbpedia-fr:Rocketdyne H-1 dbpedia-gl:Rocketdyne H-1 dbpedia-he:Rocketdyne H-1 dbpedia-hu:Rocketdyne H-1 dbpedia-id:Rocketdyne H-1 dbpedia-it:Rocketdyne H-1 dbpedia-ja:Rocketdyne H-1 dbpedia-pt:Rocketdyne H-1 dbpedia-sl:Rocketdyne H-1 dbpedia-zh:Rocketdyne H-1 https://global.dbpedia.org/id/AafQ |
| prov:wasDerivedFrom | wikipedia-en:Rocketdyne_H-1?oldid=1124273236&ns=0 |
| foaf:depiction | wiki-commons:Special:FilePath/20180328_H-1_engine_Udvar-Hazy.jpg wiki-commons:Special:FilePath/Arkansas_Air_&_Milita...24_(Rocketdyne_H-1_rocket_engine).jpg wiki-commons:Special:FilePath/Comparison_of_Rocketdyne_S-3D_and_H-1_engines.jpg wiki-commons:Special:FilePath/Saturn_I_test_article.jpg wiki-commons:Special:FilePath/H-1_rocket_engine_diagram.jpg |
| foaf:isPrimaryTopicOf | wikipedia-en:Rocketdyne_H-1 |
| is dbo:wikiPageRedirects of | dbr:H-1_(rocket_engine) |
| is dbo:wikiPageWikiLink of | dbr:Rocketdyne_S-3D dbr:Saturn_A-2 dbr:Saturn_IB dbr:Saturn_IB-D dbr:Saverio_"Sonny"_Morea dbr:List_of_aircraft_engines dbr:S-IB dbr:Apollo_program dbr:Redstone_(rocket_family) dbr:Aerojet_Rocketdyne dbr:SpaceX_Merlin dbr:H1 dbr:H-1_(rocket_engine) dbr:Canceled_Apollo_missions dbr:RS-27 dbr:RS-56 dbr:Rocketdyne dbr:Rocket_engine |
| is dbp:predecessor of | dbr:RS-27 |
| is dbp:successor of | dbr:Rocketdyne_S-3D |
| is foaf:primaryTopic of | wikipedia-en:Rocketdyne_H-1 |
