Difference between revisions 9149557 and 9149558 on thwiki

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สเปซเอ็กซ์แรพเตอร์
{{infobox rocket engine
  |image              = SpaceX sea-level Raptor at Hawthorne - 2.jpg
  |image_size         =
  |caption            = Raptor at SpaceX Hawthorne facility
  |name               = SpaceX Raptor
  |country_of_origin  = [[United States]]
  |manufacturer       = [[SpaceX]]
  |purpose            = 1st and 2nd stage propulsion of the [[SpaceX Starship|Starship]] vehicle
  |status             = Under development
  |type               = liquid
  |oxidiser           = [[Liquid oxygen]]
  |fuel               = [[liquid methane]]
  |mixture_ratio      = 3.55<ref name=musk20200507>{{cite tweet |number=1258580078218412033 |user=elonmusk |title=Starship + Super Heavy propellant mass is 4800 tons (78% O2 & 22% CH4). I think we can get propellant cost down to ~$100/ton in volume, so ~$500k/flight. With high flight rate, probably below $1.5M fully burdened cost for 150 tons to orbit or ~$10/kg. |author-link=Elon Musk |date=7 May 2020}}</ref><ref name=house20200905>{{YouTube|id=BrHMGTCMJ0Q|time=3m28s|user=MarcusHouse|title="SpaceX Starship Super Heavy and Raptor Engine Evolution, Starship SN-6 Hop, Starlink, SAOCOM 1B"}} "Also mentioned was that the propellant for this was intended to be 78% liquid oxygen and 22% liquid methane from this point on."</ref>
  |cycle              = [[Full-flow staged combustion|Full-flow]] [[staged combustion cycle (rocket)|staged combustion]]
  |pumps              = 2 turbopumps
  |description        =
  |combustion_chamber = 1
  |nozzle_ratio       = 40
  |thrust             = {{cvt|500,000|lbf|kN|order=flip|lk=out}} max<ref name=musk20200817a/><br/>{{cvt|90|t-f|kN lbf|order=flip|lk=out}} min (40%)<ref name=musk20200817b/>
  |thrust_at_altitude =
  |thrust_to_weight   = 200 (goal)<ref name="msheetz31Aug20">Michael Sheetz on Twitter: [https://twitter.com/thesheetztweetz/status/1300541467526680578 Musk goes into a long explanation of the potential capabilities of the SpaceX Raptor rocket engine (which will power Starship), saying that the company thinks Raptor could achieve a thrust-to-weight ratio of 200.]</ref>
  |chamber_pressure   = {{convert|300|bar|MPa psi|abbr=on}}<ref name=SpaceX20180917/><ref name="tweet19jun20">Elon Musk on Twitter:[https://twitter.com/elonmusk/status/1273871381353033729?s=19 Reaching chamber pressure of 300 atmospheres]</ref><br/>{{convert|330|bar|MPa psi|abbr=on}}<ref name=musk20200817a/> <small>(~ 7s test)</small>
 <!-- |thrust(Vac)        = -->
  |specific_impulse_vacuum    = {{convert|380|isp|m/s|abbr=on}} (goal)<ref name="SpaceX20180917"/>
  |specific_impulse_sea_level = {{convert|330|isp|m/s|abbr=on}}<ref name="SpaceX20180917"/>
  |total_impulse      =
  |burn_time          =
  |capacity           =
  |dimensions         =
  |length             = {{convert|3.1|m|abbr=on}}<ref>https://www.spacex.com/starship</ref>
  |diameter           = {{convert|1.3|m|abbr=on}}<ref name=youtube-makinglifemulti/>
  |dry_weight         = {{convert|1500|kg|abbr=on}} (goal)<ref name="tweet15Oct19">Elon Musk on Twitter: [https://twitter.com/elonmusk/status/1183866120240955392 Max thrust version of Raptor should achieve true T/W > 170. Target is 1.5 ton engine with >260 t-F. Max Isp version should achieve ~380 sec, but T/W probably <120 due to big nozzle. These are just guesses for now.]</ref>
  |used_in            = [[SpaceX Starship|Starship]]
}}⏎
⏎
'''สเปซเอ็กซ์แรพเตอร์''' ({{lang-en|SpaceX Raptor}}) เป็น[[เครื่องยนต์จรวด]]ที่ใช้เชื้อเพลิง[[มีเทน]][[แบบฟูลโฟลว]]ที่สามารถ[[นำกลับมาใช้ใหม่ได้]]ซึ่งผลิตโดย [[SpaceX]] เครื่องยนต์ขับเคลื่อนด้วย[[การแช่แข็ง]][[มีเทนเหลว]]และ[[ออกซิเจนเหลว]] (LOX) แทนที่จะเป็นน้ำมันก๊าด [[RP-1]] และ LOX ที่ใช้ในเครื่องยนต์จรวด [[สเปซเอ็กซ์เมอร์ลิน|Merlin]] และ [[Kestrel]] รุ่นก่อนของ SpaceX แนวคิดแรกสุดของ Raptor ถือว่า[[ไฮโดรเจนเหลว]] ({{chem2|LH2}}) เป็นเชื้อเพลิงมากกว่าก๊าซมีเทน <ref>{{(contracted; show full)== อ้างอิง ==
{{รายการอ้างอิง}}

{{SpaceX}}
{{อีลอน มัสก์}}

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