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- Rocketdyne_RS-27A abstract "The RS-27A is a liquid-fuel rocket engine developed by Rocketdyne for use on the first stage of the Delta II and Delta III launch vehicles. It provides 1.05 meganewtons (240,000 lbf) of thrust burning RP-1 and LOX in a gas-generator cycle. The engine is a modified version of its predecessor, the RS-27; its thrust nozzle has been extended to increase its area ratio from 8:1 to 12:1, which provides greater efficiency at altitude. The earlier RS-27 was derived from surplus Rocketdyne H-1 engines used in the Saturn 1B launcher.The RS-27A main engine is neither restartable nor throttleable. In addition to its main engine, the RS-27A includes two vernier engines to provide vehicle roll control during flight. The RS-27A has a run duration of 265 seconds.".
- Rocketdyne_RS-27A thumbnail Tail_of_an_Thor_XLT_Stage_with_the_RS-27_A_engine.jpg?width=300.
- Rocketdyne_RS-27A wikiPageExternalLink B-4-4-5_pwr_RS-27A.pdf.
- Rocketdyne_RS-27A wikiPageExternalLink RS27A_Engine.
- Rocketdyne_RS-27A wikiPageID "2636275".
- Rocketdyne_RS-27A wikiPageRevisionID "586283283".
- Rocketdyne_RS-27A burnTime "274.0".
- Rocketdyne_RS-27A caption "RS-27A Engine on Delta II".
- Rocketdyne_RS-27A chamberPressure "4.8".
- Rocketdyne_RS-27A combustionChamber "1".
- Rocketdyne_RS-27A countryOfOrigin United_States.
- Rocketdyne_RS-27A cycle Gas-generator_cycle.
- Rocketdyne_RS-27A date "1989".
- Rocketdyne_RS-27A designer Rocketdyne.
- Rocketdyne_RS-27A diameter "1.07 m".
- Rocketdyne_RS-27A dryWeight "1147.0".
- Rocketdyne_RS-27A fuel RP-1.
- Rocketdyne_RS-27A hasPhotoCollection Rocketdyne_RS-27A.
- Rocketdyne_RS-27A imageSize "150".
- Rocketdyne_RS-27A length "3.78 m".
- Rocketdyne_RS-27A manufacturer Rocketdyne.
- Rocketdyne_RS-27A name "RS-27A".
- Rocketdyne_RS-27A oxidiser Liquid_oxygen.
- Rocketdyne_RS-27A predecessor RS-27.
- Rocketdyne_RS-27A purpose Booster_(rocketry).
- Rocketdyne_RS-27A status "In use".
- Rocketdyne_RS-27A thrust(sl)_ "890.1 kN".
- Rocketdyne_RS-27A thrust(vac)_ "1,054.2 kN".
- Rocketdyne_RS-27A thrustToWeight "102.47".
- Rocketdyne_RS-27A type "liquid".
- Rocketdyne_RS-27A usedIn "Delta 7000, first stage".
- Rocketdyne_RS-27A subject Category:Rocket_engines.
- Rocketdyne_RS-27A subject Category:Rocketdyne_engines.
- Rocketdyne_RS-27A comment "The RS-27A is a liquid-fuel rocket engine developed by Rocketdyne for use on the first stage of the Delta II and Delta III launch vehicles. It provides 1.05 meganewtons (240,000 lbf) of thrust burning RP-1 and LOX in a gas-generator cycle. The engine is a modified version of its predecessor, the RS-27; its thrust nozzle has been extended to increase its area ratio from 8:1 to 12:1, which provides greater efficiency at altitude.".
- Rocketdyne_RS-27A label "RS-27A (motor de foguete)".
- Rocketdyne_RS-27A label "RS-27A".
- Rocketdyne_RS-27A label "RS-27A".
- Rocketdyne_RS-27A label "Rocketdyne RS-27A".
- Rocketdyne_RS-27A sameAs RS-27A.
- Rocketdyne_RS-27A sameAs RS-27A.
- Rocketdyne_RS-27A sameAs RS-27A.
- Rocketdyne_RS-27A sameAs RS-27A_(motor_de_foguete).
- Rocketdyne_RS-27A sameAs m.07tczt.
- Rocketdyne_RS-27A sameAs Q1093814.
- Rocketdyne_RS-27A sameAs Q1093814.
- Rocketdyne_RS-27A wasDerivedFrom Rocketdyne_RS-27A?oldid=586283283.
- Rocketdyne_RS-27A depiction Tail_of_an_Thor_XLT_Stage_with_the_RS-27_A_engine.jpg.
- Rocketdyne_RS-27A isPrimaryTopicOf Rocketdyne_RS-27A.