Matches in DBpedia 2014 for { <http://dbpedia.org/resource/LR-87> ?p ?o. }
Showing items 1 to 45 of
45
with 100 items per page.
- LR-87 abstract "The LR-87 was an American liquid-propellant rocket engine, which was used to propel the first stages of Titan intercontinental ballistic missiles and launch vehicles. Though this powerful engine used two discrete combustion chambers, it is considered a single unit. The LR-87 first flew in 1959.The LR-87 was developed in the late 1950s by Aerojet. It was the first production rocket engine capable (in its various models) of burning the three most common liquid rocket propellant combinations, liquid oxygen and RP-1, liquid oxygen and hydrogen, and nitrogen tetroxide and Aerozine 50 (mixture of 50 percent MMH and 50 percent UDMH). The engine operated on an open gas-generator cycle and utilized a regenerative cooled nozzle and combustion chamber. Later versions had additional ablative-cooled flanges. The LR-87 served as a template for the LR-91, which was used in the second stage of the Titan missile.It was a fixed-thrust engine, which could not be throttled or restarted in flight. The LR-87 delivered approximately 1,900 kilonewtons (430,000 pounds) of thrust. When used on the Titan I, early LR-87 engines were fuelled by RP-1 and liquid oxygen. Because the liquid oxygen was cryogenic, it could not be stored in the missile for long periods of time, and had to be loaded before the missile could be launched. For the Titan II, the engine was converted to use Aerozine-50 and nitrogen tetroxide, which are hypergolic, and storable at room temperature, so they could remain in their tanks for long periods, allowing Titan II missiles to be launched quickly if a threat was detected.".
- LR-87 thumbnail Titan_I_XLR-87_Rocket_Engine.jpg?width=300.
- LR-87 wikiPageExternalLink lr87aj11.html.
- LR-87 wikiPageExternalLink lr87.htm.
- LR-87 wikiPageExternalLink factsheet.asp?id=888.
- LR-87 wikiPageID "24888729".
- LR-87 wikiPageRevisionID "602802740".
- LR-87 caption "XLR-87 Rocket Engine".
- LR-87 chamberPressure "40".
- LR-87 cycle Gas-generator_cycle.
- LR-87 diameter "1.14 m".
- LR-87 dryWeight "839.0".
- LR-87 firstFlight "1959".
- LR-87 fuel Aerozine_50.
- LR-87 fuel "-LR-87 LH2: liquid hydrogen".
- LR-87 fuel "LR-50-87-3: RP-1".
- LR-87 hasPhotoCollection LR-87.
- LR-87 imageSize "200".
- LR-87 lastYear "2005".
- LR-87 length "240.0".
- LR-87 length "3.13".
- LR-87 manufacturer Aerojet.
- LR-87 name "LR-87".
- LR-87 oxidiser Carbon_dioxide.
- LR-87 oxidiser "LR-87-3-LR-87 LH2: liquid oxygen".
- LR-87 purpose "Titan Main engine".
- LR-87 successor "D LR-91".
- LR-87 thrust(sl)_ "LR-87-3:647 kN".
- LR-87 thrust(vac)_ "733 kN".
- LR-87 type "liquid".
- LR-87 subject Category:Rocket_engines.
- LR-87 comment "The LR-87 was an American liquid-propellant rocket engine, which was used to propel the first stages of Titan intercontinental ballistic missiles and launch vehicles. Though this powerful engine used two discrete combustion chambers, it is considered a single unit. The LR-87 first flew in 1959.The LR-87 was developed in the late 1950s by Aerojet.".
- LR-87 label "LR-87 (motor de foguete)".
- LR-87 label "LR-87".
- LR-87 label "LR-87".
- LR-87 sameAs LR-87.
- LR-87 sameAs LR-87.
- LR-87 sameAs LR-87.
- LR-87 sameAs LR-87_(motor_de_foguete).
- LR-87 sameAs m.09ghlwp.
- LR-87 sameAs Q81567.
- LR-87 sameAs Q81567.
- LR-87 wasDerivedFrom LR-87?oldid=602802740.
- LR-87 depiction Titan_I_XLR-87_Rocket_Engine.jpg.
- LR-87 isPrimaryTopicOf LR-87.