| dbo:abstract |
The ascent propulsion system (APS) or lunar module ascent engine (LMAE) is a fixed-thrust hypergolic rocket engine developed by Bell Aerosystems for use in the Apollo Lunar Module ascent stage. It used Aerozine 50 fuel, and N2O4 oxidizer. Rocketdyne provided the injector system, at the request of NASA, when Bell could not solve combustion instability problems. (en) Ascent Propulsion System (APS) atau LMAE (Lunar Module Ascent Engine) adalah sebuah mesin roket dorong hypergolic tetap dikembangkan oleh Bell Aerosystems untuk digunakan dalam Apollo Lunar Module Ascent Stage. Mesin ini mengunakan bahan bakar Aerozine 50, dan pengoksidasi N2O4. Rocketdyne menyediakan sistem injektor, atas permintaan NASA, ketika Bell tidak bisa memecahkan masalah ketidakstabilan pembakaran. (in) 月着陸船用上昇エンジン（LAME、Lunar Module Ascent Engine）は、APS（Ascent Propulsion System）とも呼称されるアポロ月着陸船の月面からの離陸用エンジンとして使用された、一定推力で駆動するエアロジン-50燃料と四酸化二窒素酸化剤の組み合わせのハイパーゴリック推進剤を用いたロケットエンジン。開発はベル・エアロシステムズにより行われた。 (ja) O Ascent Propulsion System (APS) ou Lunar Module Ascent Engine (LMAE) é um motor de foguete hipergólico de empuxo fixo, desenvolvido pela Bell Aerosystems para uso no estágio de ascensão do Módulo Lunar Apollo. Ele usava Aerozine 50 como combustível, e tetróxido de nitrogênio (N2O4) como oxidante. A Rocketdyne forneceu o sistema de injeção sob requisição da NASA, quando a Bell não conseguiu resolver os problemas de instabilidade da combustão. (pt) |
| dbo:thumbnail |
wiki-commons:Special:FilePath/Apollo_Lunar_Module_Ascent_Engine.jpg?width=300 |
| dbo:wikiPageExternalLink |
https://ntrs.nasa.gov/api/citations/19730011150/downloads/19730011150.pdf https://ntrs.nasa.gov/citations/20090016298 |
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| dbo:wikiPageWikiLink |
dbr:Project_Gemini dbr:Bell_Aircraft dbr:United_States dbc:Rocket_engines_using_hypergolic_propellant dbc:Rocket_engines_using_the_pressure-fed_cycle dbr:Corona_(satellite) dbr:RS-18 dbr:Missile_Defense_Alarm_System dbr:Apollo_Lunar_Module dbr:Apollo_command_and_service_module dbr:Lockheed_Corporation dbc:Apollo_program_hardware dbr:Titan_IIIB dbr:Agena_target_vehicle dbr:Spacecraft dbc:Spacecraft_propulsion dbr:Aerozine_50 dbr:Thrust dbr:Dinitrogen_tetroxide dbr:Hypergolic dbr:RM-81_Agena dbr:Ranger_program dbr:Exploration_Systems_Architecture_Study dbr:Lunar_module dbr:Reconnaissance_satellite dbr:Samos-F dbr:Rocketdyne dbr:Rocket_engine dbr:Pressure-fed_engine_(rocket) dbr:SAMOS dbr:Lunar_Orbiter dbr:File:Apollo_17_LM_Ascent_Stage.jpg |
| dbp:burnTime |
465.0 (dbd:second) |
| dbp:caption |
Apollo LM ascent engine (en) |
| dbp:chamberPressure |
120 (xsd:integer) |
| dbp:combustionChamber |
1 (xsd:integer) |
| dbp:countryOfOrigin |
dbr:United_States |
| dbp:cycle |
dbr:Pressure-fed_engine_(rocket) |
| dbp:date |
1964 (xsd:integer) |
| dbp:fuel |
dbr:Aerozine_50 |
| dbp:manufacturer |
dbr:Bell_Aircraft dbr:Rocketdyne |
| dbp:mixtureRatio |
1.600000 (xsd:double) |
| dbp:name |
Ascent propulsion system (en) |
| dbp:nozzleRatio |
46 (xsd:integer) |
| dbp:oxidiser |
dbr:Dinitrogen_tetroxide |
| dbp:predecessor |
Bell 8247 (en) |
| dbp:pumps |
None (en) |
| dbp:purpose |
Lunar Ascent Stage/Spacecraft propulsion (en) |
| dbp:restarts |
Designed for 2 restarts (en) |
| dbp:status |
Retired (en) |
| dbp:successor |
dbr:RS-18 |
| dbp:thrustToWeight |
16.700000 (xsd:double) |
| dbp:type |
liquid (en) |
| dbp:usedIn |
Lunar module as ascent engine (en) |
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dbt:Chem dbt:Convert dbt:Infobox_rocket_engine dbt:Main dbt:Orbital_spacecraft_rocket_engines dbt:Reflist dbt:Short_description dbt:Apollo_program_hardware dbt:Include-NASA |
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dbc:Rocket_engines_using_hypergolic_propellant dbc:Rocket_engines_using_the_pressure-fed_cycle dbc:Apollo_program_hardware dbc:Spacecraft_propulsion |
| rdfs:comment |
The ascent propulsion system (APS) or lunar module ascent engine (LMAE) is a fixed-thrust hypergolic rocket engine developed by Bell Aerosystems for use in the Apollo Lunar Module ascent stage. It used Aerozine 50 fuel, and N2O4 oxidizer. Rocketdyne provided the injector system, at the request of NASA, when Bell could not solve combustion instability problems. (en) Ascent Propulsion System (APS) atau LMAE (Lunar Module Ascent Engine) adalah sebuah mesin roket dorong hypergolic tetap dikembangkan oleh Bell Aerosystems untuk digunakan dalam Apollo Lunar Module Ascent Stage. Mesin ini mengunakan bahan bakar Aerozine 50, dan pengoksidasi N2O4. Rocketdyne menyediakan sistem injektor, atas permintaan NASA, ketika Bell tidak bisa memecahkan masalah ketidakstabilan pembakaran. (in) 月着陸船用上昇エンジン（LAME、Lunar Module Ascent Engine）は、APS（Ascent Propulsion System）とも呼称されるアポロ月着陸船の月面からの離陸用エンジンとして使用された、一定推力で駆動するエアロジン-50燃料と四酸化二窒素酸化剤の組み合わせのハイパーゴリック推進剤を用いたロケットエンジン。開発はベル・エアロシステムズにより行われた。 (ja) O Ascent Propulsion System (APS) ou Lunar Module Ascent Engine (LMAE) é um motor de foguete hipergólico de empuxo fixo, desenvolvido pela Bell Aerosystems para uso no estágio de ascensão do Módulo Lunar Apollo. Ele usava Aerozine 50 como combustível, e tetróxido de nitrogênio (N2O4) como oxidante. A Rocketdyne forneceu o sistema de injeção sob requisição da NASA, quando a Bell não conseguiu resolver os problemas de instabilidade da combustão. (pt) |
| rdfs:label |
Ascent propulsion system (en) Ascent Propulsion System (in) 月着陸船用上昇エンジン (ja) Ascent Propulsion System (pt) |
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wikidata:Ascent propulsion system dbpedia-he:Ascent propulsion system dbpedia-id:Ascent propulsion system dbpedia-ja:Ascent propulsion system dbpedia-pt:Ascent propulsion system https://global.dbpedia.org/id/4Tcbg |
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wikipedia-en:Ascent_propulsion_system?oldid=1122187713&ns=0 |
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wiki-commons:Special:FilePath/Apollo_Lunar_Module_Ascent_Engine.jpg wiki-commons:Special:FilePath/Apollo_17_LM_Ascent_Stage.jpg |
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wikipedia-en:Ascent_propulsion_system |
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dbr:Ascent |
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wikipedia-en:Ascent_propulsion_system |
