| http://dbpedia.org/ontology/abstract
|
The S5.80 is a liquid pressure-fed rocket … The S5.80 is a liquid pressure-fed rocket engine burning N2O4/UDMH with an O/F of 1.85. It is used for crew-rated spacecraft propulsion applications. It is currently used in the Soyuz-TMA-M spacecraft propulsion module KTDU-80, and its sibling, the S5.79 rocket engine, is still used as the main propulsion of the Zvezda ISS module.The S5.80 generates 2.95 kN (660 lbf) of thrust with a chamber pressure of 0.88 MPa (128 psi) and a nozzle expansion of 153.8 that enables it to achieve a specific impulse of 302 s (2.96 km/s). It is rated for 30 starts with a total firing time of 890 seconds. The engine, without the pressurization system or propellant tanks, weighs 310 kg (680 lb) and is an integrated unit that is 1.2 m (47 in) long with a diameter of 2.1 m (83 in).in) long with a diameter of 2.1 m (83 in).
, O S5.80 é um motor de foguete a combustível líquido queimando N2O4/UDMH. Ele é usado para efetuar manobras em espaçonaves tripuladas. Ele é usado atualmente no módulo de propulsão da espaçonave Soyuz-TMA-M e no módulo Zvezda da ISS.
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|
http://kbhmisaeva.ru/main.php%3Fid=53 +
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47376249
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|
10538
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1084022776
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| http://dbpedia.org/ontology/wikiPageWikiLink
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http://dbpedia.org/resource/Soyuz_%28spacecraft%29 +
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, http://dbpedia.org/resource/Category:Rocket_engines_using_the_pressure-fed_cycle +
, http://dbpedia.org/resource/Soyuz-TM +
, http://dbpedia.org/resource/KTDU-35 +
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, http://dbpedia.org/resource/KTDU-426 +
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, http://dbpedia.org/resource/Category:Rocket_engines_using_hypergolic_propellant +
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, http://dbpedia.org/resource/Progress-M +
, http://dbpedia.org/resource/International_Space_Station +
, http://dbpedia.org/resource/Category:KB_KhimMash_rocket_engines +
, http://dbpedia.org/resource/Soyuz-TMA +
, http://dbpedia.org/resource/Category:Rocket_engines_of_Russia +
, http://dbpedia.org/resource/Pirs_%28ISS_module%29 +
, http://dbpedia.org/resource/KTDU-80 +
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, http://dbpedia.org/resource/Poisk_%28ISS_module%29 +
, http://dbpedia.org/resource/Soyuz-T +
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| http://dbpedia.org/property/burnTime
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890.0
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| http://dbpedia.org/property/combustionChamber
|
1
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| http://dbpedia.org/property/countryOfOrigin
|
http://dbpedia.org/resource/USSR +
|
| http://dbpedia.org/property/cycle
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http://dbpedia.org/resource/Pressure-fed_engine +
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| http://dbpedia.org/property/date
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1977
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| http://dbpedia.org/property/designer
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OKB-2, Anton Tavzarachvili
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| http://dbpedia.org/property/firstDate
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"1986-05-21"^^xsd:date
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| http://dbpedia.org/property/fuel
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http://dbpedia.org/resource/Unsymmetrical_dimethylhydrazine +
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| http://dbpedia.org/property/gimbal
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±5°
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| http://dbpedia.org/property/mixtureRatio
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1.85
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| http://dbpedia.org/property/name
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S5.80
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| http://dbpedia.org/property/nozzleRatio
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153.8
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| http://dbpedia.org/property/oxidiser
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http://dbpedia.org/resource/Dinitrogen_tetroxide +
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| http://dbpedia.org/property/predecessor
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11
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| http://dbpedia.org/property/purpose
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Spacecraft main propulsion
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| http://dbpedia.org/property/restarts
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30
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| http://dbpedia.org/property/status
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In Production
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| http://dbpedia.org/property/type
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liquid
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| http://dbpedia.org/property/usedIn
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Soyuz since Soyuz-TM and Progress since Progress-M
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|
http://dbpedia.org/resource/Template:Convert +
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| http://purl.org/dc/terms/subject
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http://dbpedia.org/resource/Category:Rocket_engines_using_hypergolic_propellant +
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|
| http://purl.org/linguistics/gold/hypernym
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http://dbpedia.org/resource/UDMH +
|
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http://en.wikipedia.org/wiki/S5.80?oldid=1084022776&ns=0 +
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http://kbhmisaeva.ru/main.php%3Fid=53 +
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http://en.wikipedia.org/wiki/S5.80 +
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http://yago-knowledge.org/resource/S5.80 +
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|
| rdfs:comment |
The S5.80 is a liquid pressure-fed rocket … The S5.80 is a liquid pressure-fed rocket engine burning N2O4/UDMH with an O/F of 1.85. It is used for crew-rated spacecraft propulsion applications. It is currently used in the Soyuz-TMA-M spacecraft propulsion module KTDU-80, and its sibling, the S5.79 rocket engine, is still used as the main propulsion of the Zvezda ISS module.The S5.80 generates 2.95 kN (660 lbf) of thrust with a chamber pressure of 0.88 MPa (128 psi) and a nozzle expansion of 153.8 that enables it to achieve a specific impulse of 302 s (2.96 km/s). It is rated for 30 starts with a total firing time of 890 seconds. The engine, without the pressurization system or propellant tanks, weighs 310 kg (680 lb) and is an integrated unit that is 1.2 m (47 in) long with a diameter of 2.1 m (83 in).in) long with a diameter of 2.1 m (83 in).
, O S5.80 é um motor de foguete a combustível líquido queimando N2O4/UDMH. Ele é usado para efetuar manobras em espaçonaves tripuladas. Ele é usado atualmente no módulo de propulsão da espaçonave Soyuz-TMA-M e no módulo Zvezda da ISS.
|
| rdfs:label |
S5.80
|
