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assembly and ignition system, the control system and accompanying valves and plumbing, and the main combustion chamber. In
September 2003, the first combustion chamber for the engine was delivered to be tested. This testing resulted in an unknown (classified) anomaly. The root cause of the anomaly was identified and a second test was planned, but activities attempting to recover from the anomaly were slowed due to uncertain future market opportunities and timing.
513:. The SPW2000 program was thus rejected by ESA, resulting in the SPW2000 program's cancellation on 22 June 2000. Pratt & Whitney re-established the project under its own RL60 program, so-called to identify it design thrust level of 60,000 lbf. The RL60 Demonstrator Program was initiated in the end of 2000, and was planned to enter full-scale development in early 2003.
25:
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inlet and LOX control valves); and
Chemical Automatics Design Bureau (CADB) of Russia (LOX turbopump). As well as performing the systems engineering and integration for the engine, Pratt & Whitney would have manufactured the thrust chamber assembly (TCA) of the engine, consisting of the injector
516:
In 2003, Pratt & Whitney Space
Propulsion had 90% of the work completed for the RL60 engine. The RL60 was to be built and tested in the US, with key components provided by four international industry strategic suppliers: Volvo Aero of Sweden (regeneratively cooled nozzle); Ishikawajima-Harima
470:
The RL60 has its beginnings in the original commercial
Cryogenic Advanced Upper Stage Engine (cCAUSE) program, which began in 1999 and resulted in the RL50 program, a planned 220 kN (50,000 lbf) thrust class engine. The RL50 program later evolved to develop a cryogenic engine that encompassed the
529:
The development testing of the engine was planned to culminate in the testing of the first full-scale engine in early 2005, followed by engine qualification and certification in 2006. RL60 production and delivery of flight engines to customers was planned to start in mid-2006.
336:
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
482:/LOX upper-stage engine. The intention was for the RL50 engine to function as the upper stage engine for both US and European expendable launch vehicles, achieving effective cost management and
367:
RL60 is an expander cycle, liquid-fuel cryogenic rocket engine burning liquid hydrogen and liquid oxygen. The engine's cycle is virtually identical to the RL10, with some key changes:
866:
355:, such as up to 45 engine restarts (up from 15 for RL10B-2), 550 seconds longer engine lifetime (+15.7%), and twice the thrust. Like the RL10B-2, RL60 was planned to incorporate a
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extendable nozzle. RL60 was designed to meet the evolving needs of expendable launch requirements and human-rated missions of the early 2000's.
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While the RL60 is designed, integrated and tested in the US, the engine sources multiple components from international partners:
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expander cycle engine designed as a joint effort by US's Boeing and Japan's
Mitsubishi Heavy Industries in the early 2000's
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800:. Joint Propulsion Conferences. Fort Lauderdale, Florida: American Institute of Aeronautics and Astronautics.
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effort resulted in the RL50 engine being designated the SPW2000 (Snecma-P&W; 2000 indicates the year).
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of up to 465 seconds in a vacuum. The engine was planned to be a more capable successor to the
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Bullock, J.R.; Popp, M. (May 2002). "Program Status of the Pratt & Whitney RL60 Engine".
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to accommodate lower propellant inlet pressures and allow higher main pump rotational speeds.
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twice as high chamber pressure, accompanied by twice as high thrust (with 10% growth margin)
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732:"Spaceflight Now | Breaking News | Pratt to develop new upper stage rocket engine"
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slightly redesigned ignition system (Dual Direct Spark
Igniter; DDSI)
705:(Press release). Pratt & Whitney. April 22, 2003. Archived from
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RL60 was planned to include major improvements to the high-thrust
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345:
798:
40th AIAA/ASME/SAE/ASEE Joint
Propulsion Conference and Exhibit
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Planned US hydrolox rocket engine, intended to replace the RL10
502:, the provider of RL10's carbon-carbon composite nozzles, and
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794:"RL60 - The Next Step in the Evolution of Upperstage Engines"
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requirements and capabilities of both the planned RL50 and
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AIAA/ASME/SAE/ASEE Joint
Propulsion Conference and Exhibit
612:"RL60 Demonstrator Engine Design, Manufacturing, and Test"
703:"Pratt & Whitney's RL60 Moves Closer to Completion"
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However, the RL50 program was not fully embraced by
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through a common engine shared between the
European
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engine, the European 180 kN thrust expander cycle LH
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498:US vehicles. The planned collaboration between
792:Santiago, Jorge; Bullock, James (2004-07-11).
552:engine the SPW2000 program intended to replace
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46:. There might be a discussion about this on
521:turbopump); Techspace Aero of Belgium (LH
403:Other key changes from the RL10 include:
66:Learn how and when to remove this message
887:Rocket engines using hydrogen propellant
892:Rocket engines using the expander cycle
595:
610:Bullock, J.; Popp, M. (20 July 2003).
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872:Astronautix web page for RL-60 engine
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423:three times as many engine restarts.
517:Heavy Industries (IHI) of Japan (LH
328:propellants. The engine runs on an
742:from the original on 14 March 2021
14:
581:, a Chinese expander cycle LOX/LH
571:(MB-60), same thrust class LOX/LH
558:, a Russian expander cycle LOX/LH
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420:slightly longer engine lifetime
562:engine with co-development by
410:high-heat load copper tubular
385:instead of a gear drive system
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223:465 seconds (4.56 km/s)
457:nozzle provided by Swedish
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542:, the predecessor of RL60
377:is driven by a separate
307:cryogenic rocket engine
185:Thrust-to-weight ratio
455:regeneratively cooled
448:provided by Japanese
774:on December 28, 2016
435:provided by Russian
36:confusing or unclear
834:www.astronautix.com
806:10.2514/6.2004-3529
688:. AAAF-2002-S.10.2.
628:10.2514/6.2003-4489
564:Pratt & Whitney
504:Pratt & Whitney
315:Pratt & Whitney
96:Pratt & Whitney
80:
44:clarify the article
862:P&W fact sheet
840:on August 20, 2016
736:spaceflightnow.com
644:on 10 August 2022.
484:economies of scale
412:combustion chamber
357:radiatively cooled
343:Aerojet Rocketdyne
122:Liquid-fuel engine
116:Development halted
815:978-1-62410-037-6
709:on March 23, 2012
637:978-1-62410-098-7
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168:Thrust, sea-level
84:Country of origin
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32:This article
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842:. Retrieved
838:the original
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707:the original
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388:addition of
383:bypass valve
381:and turbine
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62:
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42:Please help
33:
490:and future
397:boost pumps
363:Description
304:liquid-fuel
163:Performance
106:Upper stage
102:Application
881:Categories
844:2021-03-29
778:2021-03-29
764:"SPW-2000"
746:2021-03-29
590:References
459:Volvo Aero
334:turbopumps
317:, burning
290:References
285:References
236:Dimensions
208:MPa; 1,200
175:kN (60,000
148:4.5 to 6.2
128:Propellant
38:to readers
446:turbopump
433:turbopump
375:turbopump
319:cryogenic
56:July 2021
740:Archived
534:See also
488:Ariane 5
395:and LOX
273:Dry mass
257:Diameter
228:Restarts
220:, vacuum
204:bar (8.3
196:pressure
194:Chamber
92:Designer
830:"MB-60"
713:June 1,
569:MARC-60
556:RD-0146
466:History
379:turbine
353:RL10B-2
34:may be
812:
634:
585:engine
579:YF-75D
500:Snecma
278:
266:
264:m (7.5
262:
250:
248:m (7.3
246:
241:Length
210:
206:
202:
177:
173:
113:Status
108:engine
546:Vinci
496:Delta
492:Atlas
476:Vinci
276:1,100
171:266.9
153:Cycle
810:ISBN
715:2012
632:ISBN
540:RL10
494:and
437:CADB
431:LOX
346:RL10
324:and
300:RL60
298:The
260:2.29
244:2.23
212:psi)
179:lbf)
79:RL60
802:doi
624:doi
511:ESA
450:IHI
372:LOX
313:by
268:ft)
252:ft)
132:LOX
883::
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620:39
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598:^
441:LH
390:LH
280:lb
231:45
200:83
189:51
136:LH
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