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- S5.142 abstract "The S5.142 (AKA DST-25) 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, as the low thrust thruster (DPO-M).The S5.142 generates 25 N (5.6 lbf) of thrust with a chamber pressure of 0.88 MPa (128 psi) and a nozzle expansion of 45 that enables it to achieve a specific impulse of 285 s (2.79 km/s). It is rated for 300,000 starts with a total firing time of 25,000 seconds and can do single burns from 0.03seconds to 4,000 seconds. Each unit weights 0.9 kg (2.0 lb).".
- S5.142 wikiPageExternalLink main.php?id=53.
- S5.142 wikiPageID "47398222".
- S5.142 wikiPageLength "4997".
- S5.142 wikiPageOutDegree "31".
- S5.142 wikiPageRevisionID "675950288".
- S5.142 wikiPageWikiLink A.M._Isayev_Chemical_Engineering_Design_Bureau.
- S5.142 wikiPageWikiLink Angara_(rocket_family).
- S5.142 wikiPageWikiLink Attitude_control.
- S5.142 wikiPageWikiLink Category:Rocket_engines_of_Russia.
- S5.142 wikiPageWikiLink Category:Rocket_engines_using_hypergolic_propellant.
- S5.142 wikiPageWikiLink Category:Spaceflight.
- S5.142 wikiPageWikiLink Dinitrogen_tetroxide.
- S5.142 wikiPageWikiLink Human_spaceflight.
- S5.142 wikiPageWikiLink KTDU-80.
- S5.142 wikiPageWikiLink KVTK_(rocket_stage).
- S5.142 wikiPageWikiLink Liquid-propellant_rocket.
- S5.142 wikiPageWikiLink Pressure-fed_engine.
- S5.142 wikiPageWikiLink Rocket_engine.
- S5.142 wikiPageWikiLink Rocket_propellant.
- S5.142 wikiPageWikiLink Roscosmos_State_Corporation.
- S5.142 wikiPageWikiLink Russia.
- S5.142 wikiPageWikiLink Soyuz-TM.
- S5.142 wikiPageWikiLink Soyuz-TMA.
- S5.142 wikiPageWikiLink Soyuz_TM-23.
- S5.142 wikiPageWikiLink Spacecraft_propulsion.
- S5.142 wikiPageWikiLink Specific_impulse.
- S5.142 wikiPageWikiLink Unsymmetrical_dimethylhydrazine.
- S5.142 wikiPageWikiLinkText "S5.142 (DST-25)".
- S5.142 wikiPageWikiLinkText "S5.142".
- S5.142 burnTime "25000.0".
- S5.142 combustionChamber "1".
- S5.142 countryOfOrigin Russia.
- S5.142 cycle Pressure-fed_engine.
- S5.142 date "1990".
- S5.142 designer A.M._Isayev_Chemical_Engineering_Design_Bureau.
- S5.142 firstDate "1996-02-21".
- S5.142 fuel Unsymmetrical_dimethylhydrazine.
- S5.142 mixtureRatio "1.85".
- S5.142 name "S5.142".
- S5.142 nozzleRatio "45".
- S5.142 oxidiser Dinitrogen_tetroxide.
- S5.142 predecessor "11".
- S5.142 purpose "attitude control thruster".
- S5.142 restarts "300000".
- S5.142 status "In Production".
- S5.142 type "liquid".
- S5.142 usedIn KTDU-80.
- S5.142 wikiPageUsesTemplate Template:Convert.
- S5.142 wikiPageUsesTemplate Template:Infobox_rocket_engine.
- S5.142 wikiPageUsesTemplate Template:Orbital_spacecraft_rocket_engines.
- S5.142 wikiPageUsesTemplate Template:Reflist.
- S5.142 wikiPageUsesTemplate Template:Rocket-stub.
- S5.142 subject Category:Rocket_engines_of_Russia.
- S5.142 subject Category:Rocket_engines_using_hypergolic_propellant.
- S5.142 subject Category:Spaceflight.
- S5.142 hypernym UDMH.
- S5.142 comment "The S5.142 (AKA DST-25) 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, as the low thrust thruster (DPO-M).The S5.142 generates 25 N (5.6 lbf) of thrust with a chamber pressure of 0.88 MPa (128 psi) and a nozzle expansion of 45 that enables it to achieve a specific impulse of 285 s (2.79 km/s).".
- S5.142 label "S5.142".
- S5.142 sameAs Q20982786.
- S5.142 sameAs S5.142.
- S5.142 sameAs Q20982786.
- S5.142 wasDerivedFrom S5.142?oldid=675950288.
- S5.142 homepage main.php?id=53.
- S5.142 isPrimaryTopicOf S5.142.