About: RL60

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The RL60 was a planned liquid-fuel cryogenic rocket engine designed in the United States by Pratt & Whitney, burning cryogenic liquid hydrogen and liquid oxygen propellants. The engine runs on an expander cycle, running the turbopumps with waste heat absorbed from the main combustion process. This high-efficiency, waste heat based combustion cycle combined with the high-performance liquid hydrogen fuel enables the engine to reach a very high specific impulse of up to 465 seconds in a vacuum. The engine was planned to be a more capable successor to the Aerojet Rocketdyne RL10, providing improved performance and efficiency while maintaining the installation envelope of the RL10.

Attributes	Values
rdf:type	software yago:WikicatRocketEngines yago:WikicatRocketEnginesUsingHydrogenPropellant yago:Artifact100021939 yago:Device103183080 yago:Engine103287733 yago:Instrumentality103575240 yago:JetEngine103596285 yago:Machine103699975 yago:Motor103789946 yago:Object100002684 yago:PhysicalEntity100001930 yago:Reaction-propulsionEngine104057435 yago:Rocket104099175 yago:Whole100003553
rdfs:label	RL60 (ca) RL-60 (fr) RL-60 (ja) RL60 (en) RL60 (pt)
rdfs:comment	L'RL60 és un motor de coet desenvolupat per . El disseny consisteix en un hidrogen líquid/oxigen líquid d'alta energia, capaç de múltiples ignicions a l'espai. (ca) RL-60はプラット・アンド・ホイットニーが開発したエキスパンダーサイクルのロケットエンジンである。推進剤として液体水素と液体酸素を使用し、宇宙空間で複数回、再着火する能力を有する。 (ja) O RL60 é um , que está em desenvolvimento pela Pratt & Whitney. O projeto é de um motor de ciclo expansor de alta energia (200-250 kN de empuxo), usando a combinação LH2/LOX, capaz de multiplas ignições no espaço. Em 2003, a Pratt & Whitney já tinha 90% do trabalho completo no RL60 em substituição ao RL10. (pt) The RL60 was a planned liquid-fuel cryogenic rocket engine designed in the United States by Pratt & Whitney, burning cryogenic liquid hydrogen and liquid oxygen propellants. The engine runs on an expander cycle, running the turbopumps with waste heat absorbed from the main combustion process. This high-efficiency, waste heat based combustion cycle combined with the high-performance liquid hydrogen fuel enables the engine to reach a very high specific impulse of up to 465 seconds in a vacuum. The engine was planned to be a more capable successor to the Aerojet Rocketdyne RL10, providing improved performance and efficiency while maintaining the installation envelope of the RL10. (en) Le RL60 (parfois confondu avec le MB-60) était un projet de moteur-fusée à ergols liquides américain d'environ 25 tonnes de poussée brûlant un mélange cryogénique qui était en développement chez Pratt & Whitney avant son rachat par GenCorp en 2013. Le moteur aurait brûlé un mélange LH2/LOX à haute énergie et devait mettre en œuvre un cycle à expandeur qui lui aurait permis d'atteindre une impulsion spécifique de 465 secondes. Il était conçu pour propulser un étage supérieur de lanceur et être capable de multiples redémarrages dans l'espace. Le RL60 était conçu pour produire 200 à 250 kN de poussée dans le vide. Le moteur devait pouvoir répondre à l'évolution des besoins de lancement et aux exigences des missions habitées. (fr)
name	RL60 (en)
dcterms:subject	Rocket engines using the expander cycle Rocket engines using hydrogen propellant
Wikipage page ID	20867326 (xsd:integer)
Wikipage revision ID	1109304490 (xsd:integer)
Link from a Wikipage to another Wikipage	Pratt & Whitney Bypass valve Booster pump United States Vinci (rocket engine) Volvo Aero LH2 Radiative cooling Cryogenic rocket engine Cryogenics Rocket engines using the expander cycle Liquid hydrogen MARC-60 Combustion chamber Delta (rocket family) Liquid-propellant rocket Liquid oxygen European Space Agency Atlas (rocket family) ArianeGroup Ariane 5 Aerojet Rocketdyne Rocket engines using hydrogen propellant Chemical Automatics Design Bureau Economies of scale Turbine Regenerative cooling (rocketry) Expander cycle (rocket) IHI Corporation RD-0146 RL10 YF-75D Specific impulse Snecma LOX Turbopump Upper stage
Link from a Wikipage to an external page	https://web.archive.org/web/20090204084535/http:/www.pw.utc.com/vgn-ext-templating/v/index.jsp%3Fvgnextoid=34c309d09e91c010VgnVCM1000000881000aRCRD https://web.archive.org/web/20160827164501/http:/www.astronautix.com/r/rl-60.html http://www.pw.utc.com/StaticFiles/Pratt%20&%20Whitney/Assets/Documents/space_2003_status_rl60.pdf
sameAs	RL60 RL60 RL60 RL60 RL60 RL60 RL60 RL60
thrust to weight	51 (xsd:integer)
dbp:thrust(sl)_	266.9kN (en)
dbp:wikiPageUsesTemplate	dbt:Confusing dbt:Convert dbt:Infobox_rocket_engine dbt:Nbsp dbt:Reflist dbt:Short_description dbt:Sub
caption	RL60 full-scale development engine (en)
country of origin	United States (en)
cycle	Expander cycle (rocket)
designer	Pratt & Whitney
diameter	2.29m (en)
fuel	LH2
image alt	The RL60 engine with its nozzle extended. (en)
length	2.23m (en)
mixture ratio	4.500000 (xsd:double)
oxidiser	LOX
purpose	Upper stage engine (en)
restarts	45 (xsd:integer)
status	Development halted (en)

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