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{{Infobox rocket engine
|name =RL10
|image =RL-10 with cutaway.JPG
|image_size =250
|caption =An RL10 at the [[U.S. Space & Rocket Center]] with cutaway showing tubing through the bell.
|country_of_origin=[[United States|United States of America]]
|date =
|first_date =1962 (RL10A-1)
|last_date =
|designer = [[Pratt & Whitney]]/[[Marshall Space Flight Center|MSFC]]
|manufacturer = [[Pratt & Whitney Space Propulsion]] <br/>[[Pratt & Whitney Rocketdyne]]<br/>[[Aerojet Rocketdyne]]
|purpose =[[Upper stage]] engine
|associated =[[Atlas (rocket family)|Atlas]]<br/>[[Titan (rocket family)|Titan]]<br/>[[Delta IV]]<br/>[[Saturn I]]
|successor =
|status =In production
|type =liquid
|oxidiser =[[Liquid oxygen]]
|fuel =[[Liquid hydrogen]]
|mixture_ratio =5.5 or 5.85:1
|cycle =[[Expander cycle (rocket)|Expander cycle]]
|pumps =
|description =
|combustion_chamber=
|nozzle_ratio =84:1 or 280:1
|thrust =
|thrust_at_altitude=
|thrust(Vac) ={{Convert|110|kN|abbr=on}}
|thrust(SL) =
|thrust_to_weight=
|chamber_pressure=
|specific_impulse=
|specific_impulse_vacuum={{convert|450|to|465.5|isp}}
|specific_impulse_sea_level=
|total_impulse =
|burn_time =700 seconds
|capacity =
|dimensions =
|length ={{Convert|4.14|m|abbr=on}} (nozzle extended)
|diameter ={{Convert|2.13|m|abbr=on}}
|dry_weight ={{Convert|277|kg|abbr=on}}
|used_in =[[Centaur (rocket stage)|Centaur]]<br/>[[S-IV]]<br/>[[Delta Cryogenic Second Stage|DCSS]]
|references =<ref name="EA10B2"/>
|notes =Performance values and dimensions are for RL-10B-2.
}}
'''RL10''' adalah sebuah [[mesin roket]] bahan bakar cair kriogenik yang digunakan pada Centaur, S-IV dan tahap atas DCSS. Dibangun di Amerika Serikat oleh Aerojet Rocketdyne (sebelumnya oleh Pratt & Whitney Rocketdyne), RL10 membakar cryogenic [[hidrogen cair]] & propelan [[oksigen cair]], dengan masing-masing mesin memproduksi 64,7-110 kN (14,545-24,729 lbf) daya dorong dalam ruang hampa tergantung pada versi digunakan. RL10 adalah mesin roket yang pertama menggunakan cairan hidrogen yang akan dibangun di Amerika Serikat, dan pengembangan mesin oleh Marshall Space Flight Center dan Pratt & Whitney dimulai pada tahun 1950, dengan penerbangan pertama terjadi pada tahun 1961.
== Variants ==
{| class="sortable wikitable"
! Version
! Status
! First flight
! Dry mass
! Thrust
! [[Specific impulse|''I''<sub>sp</sub> (vac)]]
! Length
! Diameter
! [[Thrust-to-weight ratio|T:W]]
! O:F
! [[Expansion ratio]]
! Chamber pressure
! Burn time
! Associated stage
! Notes
|-
| RL10A-1
| Retired
| 1962
| {{Convert|131|kg|abbr=on}}
| {{Convert|66.7|kN|abbr=on}}
| {{Convert|425|isp|abbr=on}}
| {{Convert|1.73|m|abbr=on}}
| {{Convert|1.53|m|abbr=on}}
| 52:1
|
| 40:1
|
| 430 s
| [[Centaur (rocket stage)|Centaur A]]
| Prototype<br/><ref name="EA10A1">{{cite web|url=http://www.astronautix.com/engines/rl10a1.htm|title=RL-10A-1|publisher=Encyclopedia Astronautica|author=Mark Wade|accessdate=27 February 2012|date=17 November 2011}}</ref><ref name="S2S"/><ref name="GSPAC">{{cite web|url=http://space.skyrocket.de/doc_lau/atlas_centaur.htm|title=Atlas Centaur|publisher=Gunter's Space Page|accessdate=29 February 2012}}</ref>
|-
| RL10A-3
| Retired
| 1963
| {{Convert|131|kg|abbr=on}}
| {{Convert|65.6|kN|abbr=on}}
| {{Convert|444|isp|abbr=on}}
| {{Convert|2.49|m|abbr=on}}
| {{Convert|1.53|m|abbr=on}}
| 51:1
| 5:1
| 57:1
| {{Convert|32.75|bar|abbr=on}}
| 470 s
| [[Centaur (rocket stage)|Centaur]] B/C/D/E<br/>[[S-IV]]
| <ref name="EA10A3">{{cite web|url=http://www.astronautix.com/engines/rl10a3.htm|title=RL-10A-3|publisher=Encyclopedia Astronautica|author=Mark Wade|accessdate=27 February 2012|date=17 November 2011}}</ref>
|-
| RL10A-4
| Retired
| 1992
| {{Convert|168|kg|abbr=on}}
| {{Convert|92.5|kN|abbr=on}}
| {{Convert|449|isp|abbr=on}}
| {{Convert|2.29|m|abbr=on}}
| {{Convert|1.17|m|abbr=on}}
| 56:1
| 5.5:1
| 84:1
|
| 392 s
| [[Centaur (rocket stage)|Centaur IIA]]
| <ref name="EA10A4">{{cite web|url=http://www.astronautix.com/engines/rl10a4.htm|title=RL-10A-4|publisher=Encyclopedia Astronautica|author=Mark Wade|accessdate=27 February 2012|date=17 November 2011}}</ref>
|-
| RL10A-4-1
| Retired
| 2000
| {{Convert|167|kg|abbr=on}}
| {{Convert|99.1|kN|abbr=on}}
| {{Convert|451|isp|abbr=on}}
|
| {{Convert|1.53|m|abbr=on}}
| 61:1
|
| 84:1
|
| 740 s
| [[Centaur (rocket stage)|Centaur IIIA]]
| <ref name="EA10A41">{{cite web|url=http://www.astronautix.com/engines/rl10a41.htm|title=RL-10A-4-1|publisher=Encyclopedia Astronautica|author=Mark Wade|accessdate=27 February 2012|date=17 November 2011}}</ref>
|-
| RL10A-4-2
| In production
| 2002
| {{Convert|167|kg|abbr=on}}
| {{Convert|99.1|kN|abbr=on}}
| {{Convert|451|isp|abbr=on}}
|
| {{Convert|1.53|m|abbr=on}}
| 61:1
|
| 84:1
|
| 740 s
| [[Centaur (rocket stage)|Centaur IIIB]]<br/>Centaur V1<br/>Centaur V2
| <ref name="EA10A42">{{cite web|url=http://www.astronautix.com/engines/rl10a42.htm|title=RL-10A-4-2|publisher=Encyclopedia Astronautica|author=Mark Wade|accessdate=27 February 2012|date=17 November 2011}}</ref>
|-
| RL10A-5
| Retired
| 1993
| {{Convert|143|kg|abbr=on}}
| {{Convert|64.7|kN|abbr=on}}
| {{Convert|373|isp|abbr=on}}
| {{Convert|1.07|m|abbr=on}}
| {{Convert|1.02|m|abbr=on}}
| 46:1
| 6:1
| 4:1
|
| 127 s
| [[McDonnell Douglas DC-X|DC-X]]
| <ref name="EA10A5">{{cite web|url=http://www.astronautix.com/engines/rl10a5.htm|title=RL-10A-5|publisher=Encyclopedia Astronautica|author=Mark Wade|accessdate=27 February 2012|date=17 November 2011}}</ref>
|-
| RL10B-2
| In production
| 1998
| {{Convert|277|kg|abbr=on}}
| {{Convert|110|kN|abbr=on}}
| {{Convert|462|isp|abbr=on}}
| {{Convert|4.14|m|abbr=on}}
| {{Convert|2.13|m|abbr=on}}
| 40:1
| 5.85:1
| 280:1
| {{Convert|44.12|bar|abbr=on}}
| 700 s
| [[Delta Cryogenic Second Stage]]
| <ref name="EA10B2">{{cite web|url=http://www.astronautix.com/engines/rl10b2.htm|title=RL-10B-2|publisher=Encyclopedia Astronautica|author=Mark Wade|accessdate=27 February 2012|date=17 November 2011}}</ref>
|-
| RL10B-X
| Cancelled
|
| {{Convert|317|kg|abbr=on}}
| {{Convert|93.4|kN|abbr=on}}
| {{Convert|470|isp|abbr=on}}
|
| {{Convert|1.53|m|abbr=on}}
| 30:1
|
| 250:1
|
| 408 s
| [[Centaur (rocket stage)|Centaur B-X]]
| <ref name="EA10BX">{{cite web|url=http://www.astronautix.com/engines/rl10bx.htm|title=RL-10B-X|publisher=Encyclopedia Astronautica|author=Mark Wade|accessdate=27 February 2012|date=17 November 2011}}</ref>
|-
| CECE
| In development
|
| {{Convert|160|kg|abbr=on}}
| {{Convert|66.7|kN|abbr=on}}
| >{{Convert|445|isp|abbr=on}}
| {{Convert|1.53|m|abbr=on}}
|
|
|
|
|
|
|
| Base demonstrator<br/><ref name="PWRCECE">{{cite web|url=http://www.pw.utc.com/products/pwr/propulsion_solutions/cece.asp|title=Commons Extensible Cryogenic Engine|publisher=Pratt & Whitney Rocketdyne|accessdate=28 February 2012|archive-date=2012-03-04|archive-url=https://web.archive.org/web/20120304081145/http://www.pw.utc.com/products/pwr/propulsion_solutions/cece.asp|dead-url=yes}}</ref><ref>{{Cite web |url=http://www.rocket.com/common-extensible-cryogenic-engine-0 |title=Salinan arsip |access-date=2015-11-09 |archive-date=2014-07-03 |archive-url=https://web.archive.org/web/20140703051039/http://www.rocket.com/common-extensible-cryogenic-engine-0 |dead-url=yes }}</ref>
|-
| RL10C-1
| In testing
| 12/2014
| {{Convert|191|kg|abbr=on}}
| {{Convert|106.31|kN|abbr=on}}
| {{Convert|448.5|isp|abbr=on}}
| {{Convert|2.22|m|abbr=on}}
| {{Convert|1.44|m|abbr=on}}
| 57:1
| 5.88:1
| 130:1
|
| 2000
| Centaur
| <br/><ref name="CPS">{{cite web|url=http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20110015783.pdf|title=Cryogenic Propulsion Stage|publisher=NASA|accessdate=11 October 2014}}</ref><ref>[http://forum.nasaspaceflight.com/index.php?topic=34891.0]</ref>
|}
== Specifications ==
=== Original RL10 ===
* Thrust (altitude): 15,000 [[Pound-force|lbf]] (66.7 kN)<ref name="S2S">{{citation | url=http://history.nasa.gov/SP-4206/ch5.htm | title=Stages to Saturn; A Technological History of the Apollo/Saturn Launch Vehicles|author=Bilstein, Roger E.|chapter=Unconventional Cryogenics: RL-10 and J-2|date=1996|publisher=National Aeronautics and Space Administration, NASA History Office|place=Washington, D.C.|accessdate=2011-12-02}}</ref>
* Burn Time: 470 s<ref name="S2S" />
* Design: [[Expander cycle (rocket)|Expander cycle]]{{Citation needed|date=March 2011}}
* [[Specific impulse]]: {{convert|433|isp}}{{Citation needed|date=March 2011}}
* Engine weight - [[dry weight|dry]]: 298 lb (135 kg)<!--http://www.astronautix.com/engines/rl10.htm says 288 lb/131 kg-->
* Height: 68 in (1.73 m)
* Diameter: 39 in (0.99 m)
* Nozzle expansion ratio: 40 to 1
* Propellants: Liquid Oxygen & Liquid Hydrogen
* Propellant flow: 35 lb/s (16 kg/s)
* Contractor: Pratt & Whitney
* Vehicle application: [[Saturn I]] / [[S-IV]] 2nd stage - 6-engines
* Vehicle application: [[Centaur (rocket stage)|Centaur]] upper stage - 2-engines
=== Current design ===
[[Berkas:Second stage of a Delta IV Medium rocket.jpg|jmpl|Second stage of a Delta IV Medium rocket featuring an RL10B-2 engine.]]
; RL10B-2 Specifications
* Thrust (altitude): 24,750 lbf (110.1 kN)<ref name=pwr_rl10b-2.pdf>{{cite web |url=http://www.pw.utc.com/products/pwr/assets/pwr_rl10b-2.pdf |title=RL10B-2 |publisher=[[Pratt & Whitney Rocketdyne]] |date=2009 |accessdate=January 29, 2012 |archive-date=2012-03-26 |archive-url=https://web.archive.org/web/20120326211303/http://www.pw.utc.com/products/pwr/assets/pwr_rl10b-2.pdf |dead-url=yes }}</ref>
* Design: [[Expander cycle (rocket)|Expander cycle]]<ref name="">{{cite journal |url=http://www.dtic.mil/cgi-bin/GetTRDoc?AD=ADA397948 |title=50K expander cycle engine demonstration |journal=AIP Conference Proceedings |first1=A M |last1=Sutton |first2=S D |last2=Peery |first3=A B |last3=Minick |volume=420 |pages=pp. 1062–1065 |date=January 1998 |doi=10.1063/1.54719 |access-date=2015-11-09 |archive-date=2013-04-13 |archive-url=https://web.archive.org/web/20130413151618/http://www.dtic.mil/cgi-bin/GetTRDoc?AD=ADA397948 |dead-url=yes }}</ref>
* [[Specific impulse]]: {{convert|464|isp}}<ref name=pwr_rl10b-2.pdf />
* Engine weight - dry: 610 lb (277 kg)<ref name=pwr_rl10b-2.pdf />
* Height: 163 in (4.14 m)<ref name=pwr_rl10b-2.pdf />
* Diameter: 87 in (2.21 m)<ref name=pwr_rl10b-2.pdf />
* [[Expansion ratio]]: 250 to 1
* Mixture ratio: 5.85 to 1 <ref name=pwr_rl10b-2.pdf />
* Propellants: [[Liquid oxygen]] & [[liquid hydrogen]]<ref name=pwr_rl10b-2.pdf />
* Propellant flow: Oxidizer 41.42 lb/s (20.6 kg/s), fuel 7.72 lb/s (3.5 kg/s)<ref name=pwr_rl10b-2.pdf />
* Contractor: Pratt & Whitney
* Vehicle application: [[Delta III]], Delta IV second stage (1 engine)
; RL10A-4-2
The other current model, the RL10A-4-2, is the engine used on [[Centaur (rocket stage)|Centaur]] upper stage for [[Atlas V]].<ref name=pwr_rl10b-2.pdf />
== Referensi ==
;Notes
{{Reflist|30em}}
;Bibliography
* {{cite book|last= Connors|first= Jack|title= The Engines of Pratt & Whitney: A Technical History|publisher= [[American Institute of Aeronautics and Astronautics]]|location= Reston. Virginia|date= 2010|isbn= 978-1-60086-711-8|url=|pages= }}
== Pranala luar ==
{{Commons category|RL10}}
* [http://www.astronautix.com/engines/rl10b2.htm RL10B-2 at Astronautix]
* [http://www.spaceflightnow.com/news/n0708/16rl10valve/ Spaceflight Now article]
* [http://www.spaceflightnow.com/news/n0901/26altair/ Spaceflight Now article]
[[Kategori:Mesin roket]]
[[Kategori:Mesin roket tahap atas]]
[[Kategori:North American Aviation]]
[[Kategori:Mesin roket Amerika Serikat]]
[[Kategori:Mesin roket yang menggunakan propelan hidrogen]]
[[Kategori:Mesin roket yang menggunakan siklus ekspander]]
[[Kategori:Mesin Rocketdyne]]
[[Kategori:Space Launch System]]
[[Kategori:Mesin roket tahap inti]]
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