About: Aerojet LR87

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The LR87 was an American liquid-propellant rocket engine used on the first stages of Titan intercontinental ballistic missiles and launch vehicles. Composed of twin motors with separate combustion chambers and turbopump machinery, it is considered a single unit. The LR87 first flew in 1959. For the Titan III and IV, which were larger, more capable space launch vehicles, the LR87 was modified further. Thrust and nozzle area ratio were progressively increased, requiring heavier turbopumps, pipes, and other parts.

Attributes	Values
rdfs:label	LR-87 (cs) Aerojet LR87 (en) LR-87 (in) LR-87 (fr) LR-87 (ko) LR-87 (ja) LR-87 (motor de foguete) (pt)
rdfs:comment	LR-87 byl raketový motor na kapalné pohonné látky, vyvinutý na konci 50. let 20. století americkou společností Aerojet. Jedná se o světově první a jediný raketový motor, který je schopen (s úpravami) spalovat všechny tři nejpoužívanější druhy raketového paliva, kapalný kyslík a RP-1, kapalný kyslík a vodík a oxid dusičitý a aerozin 50 (směs 50% MMH a 50% UDMH). Byl používán na prvním stupni raket Titan, v roce 1986 byl zvažován pro koncepci těžké nosné rakety s nosností 45 000 kg . Technicky se jedná o motor s otevřeným cyklem a regenerativně chlazenou tryskou a spalovací komorou, pozdější verze mají přídavné ablativně chlazené obruby. LR-87 posloužil jako předloha pro jeho menšího bratříčka LR-91, který je používán na druhém stupni raket Titan. (cs) LR-87はタイタン大陸間弾道ミサイルと衛星打ち上げロケットの1段目に使用された液体燃料ロケットエンジンである。この強力なエンジンは一見したところ2基のエンジンが束ねてあるように見えるが、実際には2基が1組として共に作動する。LR-87の最初の打ち上げは1959年である。タイタンロケットの歴史はLR-87エンジンと共にあったといっても過言ではなく、現時点においてタイタンIVロケットの引退後は使用されていない。 (ja) LR-87은 미국 타이탄 (로켓) 시리즈의 1단 액체연료 엔진이다. 진공추력 75톤, 해면추력 65톤의 케로신/액체산소 로켓 엔진으로서, 1959년 타이탄 I ICBM의 1단 엔진으로 최초 발사되었다. (ko) The LR87 was an American liquid-propellant rocket engine used on the first stages of Titan intercontinental ballistic missiles and launch vehicles. Composed of twin motors with separate combustion chambers and turbopump machinery, it is considered a single unit. The LR87 first flew in 1959. For the Titan III and IV, which were larger, more capable space launch vehicles, the LR87 was modified further. Thrust and nozzle area ratio were progressively increased, requiring heavier turbopumps, pipes, and other parts. (en) LR-87 adalah roket mesin Amerika propelan cair, yang digunakan untuk menggerakkan tahap pertama rudal balistik antarbenua Titan dan kendaraan peluncur . Meskipun mesin kuat ini menggunakan dua ruang pembakaran diskrit, itu dianggap sebagai satu kesatuan karena menggunakan kedua kamar untuk turbomachinery umum yang kemudian tidak berbeda dengan mesin Rusia seperti RD-170 . LR-87 pertama kali terbang pada tahun 1959. (in) LR87 désigne une famille de moteurs-fusées à ergols liquides de la société américaine Aerojet dont le développement a débuté dans les années 1950. Deux exemplaires de ce moteur de relativement forte poussée pour son époque (734 kNewtons dans le vide) ont propulsé le premier étage du missile balistique intercontinental SM-68 Titan puis du lanceur Titan dérivé. Il a été mis en oeuvre avec différents combinaisons d'ergols : RP-1 / Oxygène liquide dans la première version LR87-3 propulsant le missile, peroxyde d'azote / Aérozine 50 pour les versions LR87-5, 7, 9, 11). Il a été enfin proposé avec les ergols LH2 / Oxygène liquide (LR87-LH2) pour propulser le deuxième étage de la fusée Saturn V. Le moteur a effectué son premier vol en 1959 et sa dernière utilisation correspond au retrait du lance (fr) O LR-87, foi um motor de foguete de alta performance, movido a combustíveis líquidos, fabricado nos Estados Unidos. Foi usado no primeiro estágio dos foguetes Titan. Apesar desse motor possuir duas câmaras de combustão, era considerado apenas um motor com um único conjunto de mecanismos e turbo bombas alimentando as duas câmaras de combustão, de maneira semelhante ao motor Russo , desenvolvido na Rússia pela NPO Energomash. * LOX e RP-1 * LOX e LH2 * Aerozine 50 e NTO (pt)
name	LR87 (en)
foaf:depiction
dcterms:subject	Rocket engines using hypergolic propellant Rocket engines of the United States Rocket engines using the gas-generator cycle Rocket engines using kerosene propellant Rocket engines using hydrogen propellant
Wikipage page ID	24888729 (xsd:integer)
Wikipage revision ID	1124933979 (xsd:integer)
Link from a Wikipage to another Wikipage	Project Gemini Saturn IB Saturn V Hydrazine United States Intercontinental ballistic missile LH2 Rocket engines using hypergolic propellant Cryogenic M-1 (rocket engine) NASA Liquid hydrogen Gas-generator cycle (rocket) Bar (unit) Rocket engines of the United States Rocket engines using the gas-generator cycle Titan II GLV Titan IV Liquid-propellant rocket Liquid oxygen Altitude Nitrogen tetroxide Titan (rocket family) AJ-10 Hypergolic propellant LR-91 Rocket engines using kerosene propellant Aerojet Aerozine 50 Rocket engines using hydrogen propellant LGM-25C Titan II Titan I Dinitrogen tetroxide Autogenous pressurization Human-rating certification Hypergolic RL10 RP-1 Specific impulse Vacuum LOX Turbopump Rocket engine UDMH Liquid-fuel rocket J-2 (rocket engine) Titan (rocket) Titan III
Link from a Wikipage to an external page	http://cobweb.ecn.purdue.edu/~propulsi/propulsion/rockets/liquids/lr87aj11.html https://web.archive.org/web/20101225182027/http:/www.nationalmuseum.af.mil/factsheets/factsheet.asp%3Fid=888 https://web.archive.org/web/20110604072940/http:/www.astronautix.com/engines/lr87.htm
sameAs	Aerojet LR87 Aerojet LR87 Aerojet LR87 Aerojet LR87 Aerojet LR87 Aerojet LR87 Aerojet LR87 Aerojet LR87
dbp:thrust(sl)_	LR87-3: 647 kN (en)
dbp:wikiPageUsesTemplate	dbt:Citation_needed dbt:Commons_category dbt:Convert dbt:Efn dbt:Expand_section dbt:Infobox_rocket_engine dbt:More_citations_needed dbt:Nbsp dbt:Notelist dbt:Portal dbt:R

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