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翻訳と辞書　辞書検索 [ 開発暫定版 ] スポンサード リンク Comparison of orbital rocket engines ： ウィキペディア英語版 Comparison of orbital rocket engines This page exposes an incomplete list of orbital rocket engines. Legend for below table:   (style="background-color:khaki">under development ) — (style="background-color:lightgrey">retired,canceled ) — (style="background-color:white">operational,inactive ) )(9.807\ \mathrm)}=76.99〕 | 〔 | Operational |Vulcain 2 |- style="background:white;font-style:italic;" |P230〔(【引用サイトリンク】 title=P230 )〕 | | SNPE (Societe Nationale des Poudres et Explosifs) |Ariane 5 |Booster |HTPB(68/18) | 〔 | 〔 | 〔 | 〔 | with fuel〔 | | | Operational |P230 |- style="background:white;font-style:italic;" |HM7B〔(【引用サイトリンク】 title=HM7-B )〕 | |Snecma |Ariane 5 ECA | Upper |LH2/LOX | 〔 | 〔 | 〔 | 〔 | 〔 | ?〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=40.05$〕 | 〔 | Operational |HM7B |- style="background:khaki;font-style:italic;" |Vinci〔(【引用サイトリンク】 title=Vinci )〕 | |Snecma |Ariane 6 | Upper |LH2/LOX | 〔 | | 〔 | | 〔 | 〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=65.55$〕 | 〔 | Development |Vinci |- style="background:white;font-style:italic" |RD-180〔(【引用サイトリンク】 title=RD-180 )〕 | |NPO Energomash |Atlas V Atlas III | 1st |RP-1/LOX | 〔 | | 〔 | | 〔 | 〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=71.2$〕 | 〔 | Operational |RD-180 |- style="background:white;font-style:italic;" |RD-191〔(【引用サイトリンク】 title=RD-191 )〕 | |NPO Energomash |Angara | 1st |RP-1/LOX | 〔 | | 〔 | | 〔 | 〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=89.09$〕 | 〔 | Operational |RD-191 |- style="background:white;font-style:italic" | RD-0124 14Д23 | | TsSKB Progress | Soyuz-2.1b Soyuz-2-1v Angara | 2nd,3rd | RP-1/LOX | | | | | | ?〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=62.5$〕 | | Operational |RD-0124 |- style="background:white;font-style:italic" |NK-33-1 (AJ26-58) 11Д111 | |Kuznetsov Design Bureau Aerojet |Antares Soyuz-2.1v | 1st |RP-1/LOX | 〔 | | 〔 | | 〔 | 〔 | 〔 | Operational |NK-33-1 (AJ26-58) |- style="background:lightgrey;font-style:italic" |Gamma 8 | |Bristol Siddeley |Black Arrow | 1st |H2O2/Kerosene | 〔 | | 〔 | | 〔 | 〔 | 〔 | Retired |Gamma 8 |- style="background:lightgrey;font-style:italic" |Gamma 2 | |Bristol Siddeley |Black Arrow | 2nd |H2O2/Kerosene | 〔 | | 〔 | | 〔 | 〔 | | Retired |Gamma 2 |- style="background:lightgrey;font-style:italic" |Waxwing | |Bristol Aerojet |Black Arrow | Upper ||Solid | 〔 | | 〔 | | 〔 | | | Retired |Waxwing |- style="background:lightgray;font-style:italic;" |Merlin 1C | |SpaceX |Falcon 9 Falcon 1 | 1st,2nd |RP-1/LOX | | 〔(【引用サイトリンク】 title=Falcon 9 Space Launch Report )〕 | 〔 | 〔 | | 〔 | | Retired |Merlin 1C |- style="background:lightgray;font-style:italic;" |Merlin Vacuum 1C | |SpaceX |Falcon 9 Falcon 1 | 2nd |RP-1/LOX | 〔 | | 〔 | | | | | Retired |Merlin Vacuum 1C |- style="background:white;font-style:italic;" |Merlin 1D | |SpaceX |Falcon 9 Falcon Heavy | 1st |RP-1/LOX | | 〔 | 〔(【引用サイトリンク】 title=Merlin 1D )〕 | 〔 | ?〔$\backslash frac)\}=430\backslash \; \backslash mathrm$〕 | | | Operational |Merlin 1D |- style="background:white;font-style:italic;" |Merlin Vacuum 1D | |SpaceX |Falcon 9 Falcon Heavy | 2nd |RP-1/LOX | 〔(【引用サイトリンク】 url=http://www.spacex.com/falcon9 )〕 | | 〔 | | | | | Operational |Merlin Vacuum 1D |- style="background:khaki;font-style:italic;" |Raptor | |SpaceX | | 1st |Methane/LOX〔 | 〔 | | | | | | | Development |Raptor |- style="background:white;font-style:italic;" |RD-171M〔(【引用サイトリンク】 title=RD-171M )〕 Most powerful liquid-fuel rocket engine in the world | |NPO Energomash |Zenit-3SL Zenit-3SLB | 1st |RP-1/LOX | 〔 | | 〔 | | 〔 | 〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=79.57$〕 | 〔 | Operational |RD-171M |- style="background:white;font-style:italic;" |RD-107A〔(【引用サイトリンク】 title=RD-107A and RD-108A )〕 14Д22 | |NPO Energomash |Soyuz-FG Soyuz-2 | 1st |RP-1/LOX | 〔 | | 〔 | | 〔 | 〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=78.53$〕 | 〔 | Operational |RD-107A |- style="background:white;font-style:italic;" |RD-108A〔 14Д21 | |NPO Energomash |Soyuz-FG Soyuz-2 | 2nd |RP-1/LOX | 〔 | | 〔 | | 〔 | 〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=75.16$〕 | 〔 | Operational |RD-108A |- style="background:white;font-style:italic;" |RD-117 11Д511 | |NPO Energomash |Soyuz-U | 1st |RP-1/LOX | 〔 | | | | 〔 | 〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=72.18$〕 | 〔 | Operational |RD-117 |- style="background:white;font-style:italic;" |RD-118〔 11Д512 | |NPO Energomash |Soyuz-U | 2nd |RP-1/LOX | 〔 | | 〔 | | 〔 | 〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=75.91$〕 | 〔 | Operational |RD-118 |- style="background:lightgrey;font-style:italic" |LE-5 | |Mitsubishi Heavy Industries NASDA |H-I | Upper |LH2/LOX | | | | | | | | Retired |LE-5 |- style="background:lightgrey;font-style:italic" |LE-5A | |Mitsubishi Heavy Industries NASDA |H-II | Upper |LH2/LOX | | | | | | | | Retired |LE-5A |- style="background:white;font-style:italic;" |LE-5B | |Mitsubishi Heavy Industries JAXA |H-IIA H-IIB | Upper |LH2/LOX | | | | | | ?〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=49.1$〕 | | Operational |LE-5B |- style="background:lightgrey;font-style:italic" |LE-7 | |Mitsubishi Heavy Industries NASDA |H-II | 1st |LH2/LOX | | | | | | | | Retired |LE-7 |- style="background:white;font-style:italic;" |LE-7A | |Mitsubishi Heavy Industries JAXA |H-IIA H-IIB | 1st |LH2/LOX | | | | | | | | Operational |LE-7A |- style="background:white;font-style:italic;" |SRB-A | |IHI Aerospace JAXA |H-IIA H-IIB | Booster | Solid | (SRB-A) (SRB-A3 version H-IIA F18) | | (SRB-A) (SRB-A3 version H-IIA F18) | | with fuel | | | Operational |SRB-A |- style="background:white;font-style:italic;" |RS-68A〔(【引用サイトリンク】url=http://spaceflight101.com/spacerockets/delta-iv-heavy/ )〕 Most powerful hydrogen-fueled engine in the world | |Pratt & Whitney Rocketdyne |Delta IV Delta IV Heavy | 1st |LH2/LOX | 〔 | | 〔 | 〔 | 〔 | 〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=53.80$〕 | 〔 | Operational |RS-68A |- style="background:white;font-style:italic;" |Atlas V SRB | |Aerojet |Atlas V |Booster |Solid |〔(【引用サイトリンク】url=http://www.rocket.com/atlas-v-solid-rocket-motor )〕 | |〔 | | | | | Operational |Atlas V SRB |- style="background:lightgrey;font-style:italic;" |F-1 Most powerful single-chamber liquid-fueled rocket engine ever developed | |Rocketdyne |Saturn V | 1st |RP-1/LOX | | | | | | ?〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=82.27$〕 | | Retired |F-1 |- style="background:white;font-style:italic;" |RS-25 - SSME | |Pratt & Whitney Rocketdyne |Space Shuttle | 1st |LH2/LOX | | | | | | 〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=53.79$〕 | | Inactive since STS-135 |RS-25 |- style="background:white;font-style:italic;" |Space Shuttle Solid Rocket Booster Largest solid-fuel rocket motor ever flown, and the first to be used for primary propulsion on human spaceflight missions | |Thiokol |Space Shuttle Ares I |Booster |APCP | | | | | with fuel | | | Inactive since STS-135 |Space Shuttle Solid Rocket Booster |- style="background:lightgrey;font-style:italic;" |J-2 | |Rocketdyne |Saturn V Saturn IB | 2nd, 3rd |LH2/LOX | | | | | | | | Retired |J-2 |- style="background:khaki;font-style:italic;" |J-2X | |Pratt & Whitney Rocketdyne |Space Launch System | Upper |LH2/LOX | | | | | 〔 | ?〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=54.97$〕 | | Development |J-2X |- style="background:white;font-style:italic;" |RL-10B-2 | |Pratt & Whitney Rocketdyne |Delta III Delta IV | Upper |LH2/LOX | | | | | | | | Operational |RL-10B-2 |- style="background:white;font-style:italic;" |RL-10A-4-2〔 | |Pratt & Whitney Rocketdyne |Atlas V | Upper |LH2/LOX | | | | | | | | Operational |RL-10A-4-2 |- style="background:white;font-style:italic;" |NSTAR First ever ion engine used as a main engine on an operational science spacecraft | |Hughes Electron Dynamics Boeing |Deep Space 1 Dawn |Ion thruster |Xenon | @2.3 kW | | @2.3 kW | | | | | Operational |NSTAR |- style="background:lightgrey;font-style:italic;" |HiPEP Most efficient inert gas ion thruster ever built | |NASA |Jupiter Icy Moons Orbiter |Ion thruster |Xenon | @39.3 kW | | @39.3 kW | | | | | Canceled |HiPEP |- style="background:khaki;font-style:italic;" |NEXT | |NASA | |Ion thruster |Xenon | @6.9 kW | | @6.9 kW | | | | | Development |NEXT |- style="background:khaki;font-style:italic;" |VASIMR | |Ad Astra Rocket Company | | Electro-magnetic thruster | Argon | @200 kW | | @200 kW | | | | | Development |VASIMR |- style="background:white;font-style:italic;" |PPS-1350 | |OKB Fakel Snecma | SMART-1 | Hall thruster | Xenon | @1.5 kW | | @1.5 kW | | | | | Operational |PPS-1350 |- style="background:white;font-style:italic;" |SPT-100 | |OKB Fakel | LS-1300 satellites | Hall thruster | Xenon | @1.35 kW | | @1.35 kW | | | | | Operational |SPT-100 |- style="background:white;font-style:italic;" |Boeing 601HP First ever ion engine used as a main engine on an operational commercial satellite (PAS-5) | |Boeing |Boeing 601HP satellites | Ion thruster | Xenon | @0.5 kW | | @0.5 kW | | | | | Operational |Boeing 601HP |- style="background:white;font-style:italic;" |Boeing 702 | |Boeing |Boeing 702 satellites | Ion thruster | Xenon | @4.5 kW | | @4.5 kW | | | | | Operational |Boeing 702 |- style="background:white;font-style:italic" |KVD-1 11Д56У | |KBKhM |GSLV Mk I | Upper |LH2/LOX | 〔 | | 〔 | | 〔 | | | Inactive |KVD-1 |- style="background:white;font-style:italic;" |CE-7.5〔(【引用サイトリンク】 title=Indigenous Cryogenic Engine and Stage )〕〔(【引用サイトリンク】 title=GSLV Launch Vehicle Information )〕 | |ISRO |GSLV Mk II | Upper | LH2/LOX | 〔 | | 〔 | | 〔 | ?〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=16.85$〕 | | Operational |CE-7.5 |- style="background:white;font-style:italic;" |PSLV-1〔(【引用サイトリンク】 title=PSLV-1 )〕 | |ISRO |PSLV | 1st | HTPB | 〔 | | 〔 | | 〔 | | 〔 | Operational |PSLV-1 |- style="background:white;font-style:italic;" |SLV-1〔(【引用サイトリンク】 title=SLV-1 )〕 | |ISRO |PSLV | Booster | HTPB | 〔 | | 〔 | | 〔 | | 〔 | Operational |SLV-1 |- style="background:white;font-style:italic;" |S200〔(【引用サイトリンク】 title=LVM3 )〕 | |ISRO |LVM3 | Booster | HTPB | 〔 | | 〔(ISRO Press Release: S200 First Static Test (S-200-ST-01) )〕〔(【引用サイトリンク】title=Isro successfully tests world's 3rd largest solid booster )〕 | | 〔 | | | Operational |S200 |- style="background:white;font-style:italic;" |RD-264〔 11Д119 | |NPO Energomash |Dnepr-1 | 1st | N2O4/UDMH | 〔 | | 〔 | | 〔 | 〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=117.77$〕 | 〔 | Operational |RD-264 |- style="background:white;font-style:italic;" |RD-275M〔(【引用サイトリンク】 title=RD-253 and RD-275M )〕 14Д14М | |NPO Energomash |Proton-M | 1st | N2O4/UDMH | 〔 | | 〔 | | 〔 | 〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=159.25$〕 | 〔 | Operational |RD-275M |- style="background:lightgrey;font-style:italic" |RD-0120〔(【引用サイトリンク】title= RD0120 )〕 11Д122 | |KBKhA |Energia | 1st |LH2/LOX | 〔 | | 〔 | | 〔 | | | Retired |RD-0120 |- style="background:khaki;font-style:italic;" |RD-193 (RD-181)〔(【引用サイトリンク】title= Energomash Test Fires New RD-193 Engine )〕 | ||NPO Energomash |Soyuz-2.1v Antares | 1st |RP-1/LOX | | | 〔 | | 〔 | 〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=105.26$〕 | | Development |RD-193 |- style="background:white;font-style:italic;" |Aestus | |Airbus Defence and Space |Ariane 5 ES | Upper |N2O4/MMH | 〔 | | 〔 | | 〔 | ?〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=27.6$〕 | 〔 | Operational |Aestus |- style="background:khaki;font-style:italic;" |Aestus II | |Airbus Defence and Space |Ariane 5 | Upper |N2O4/MMH | 〔 | | 〔 | | 〔 | ?〔$\backslash frac)(9.807\backslash \; \backslash mathrm)\}=40.9$〕 | 〔 | Development |Aestus II |- style="background:white;font-style:italic;" |BE-3 | |Blue Origin |New Shepard | 1st |LH2/LOX |Unknown | | | | | | |Operational |BE-3 |- style="background:khaki;font-style:italic;" |BE-4〔 | |Blue Origin |Atlas V Vulcan | 1st |Methane/LOX |Unknown | |〔 | | | | |Development |BE-4 |- style="background:khaki;font-style:italic;" |SLS Solid Rocket Booster Largest, most powerful solid-fuel rocket motor ever built | |Orbital ATK |SLS |Booster |PBAN | | | | | with fuel | | | Development |SLS Solid Rocket Booster |} == See also == *Comparison of orbital launch systems * Comparison of orbital spacecraft 抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』 ■ウィキペディアで「Comparison of orbital rocket engines」の詳細全文を読む スポンサード リンク 翻訳と辞書 : 翻訳のためのインターネットリソース Copyright(C) kotoba.ne.jp 1997-2016. 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