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Comparison of orbital rocket engines

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This page is an incomplete list of orbital rocket engine data and specifications.

Current, Upcoming, and In-Development rocket engines

[edit]
Engine Origin Designer Vehicle Status Use Propellant Power cycle Specific impulse (s)[a] Thrust (N)[a] Chamber pressure (bar) Mass (kg) Thrust:​weight ratio[b] Oxidiser:​fuel ratio
AJ-10-190  USA Aerojet Space Shuttle, Orion, Apollo CSM Active Upper N2O4/MMH Pressure-fed 316[1] 26,689[1] 8.62[1] 118[1] 23.08
Archimedes  New Zealand  USA Rocket Lab Neutron Development 1st, 2nd CH4 / LOX Staged, oxidizer-rich 730,000
Aeon-R  USA Relativity Space Terran R Development 1st, 2nd CH4 / LOX Gas generator 1,147,000
BE-3  USA Blue Origin New Shepard Active 1st LH2 / LOX Combustion tap-off 490,000[2]
BE-3U  USA Blue Origin New Glenn Development 2nd LH2 / LOX Expander, open 445[3] 765,000[3]
BE-4  USA Blue Origin New Glenn, Vulcan Active[4] 1st CH4 / LOX Staged, oxidizer-rich 340[3] 2,400,000[5][6] 138[3]
BE-7  USA Blue Origin Blue Moon Development 1st LH2 / LOX Expander, open 44,000
CE-20  India LPSC GSLV Mk III Active Upper LH2 / LOX Gas generator 434 196,500 60.00 588 34.1 5.05
CE-7.5  India LPSC GSLV Mk II Active Upper LH2 / LOX Staged 454[7] 73,500 58 445 16.85
E2  USA ABL Space Systems RS1 Active 1st RP-1 / LOX // Jet-A / LOX Gas generator 53,800[8] 64
E2 Vacuum  USA ABL Space Systems RS1 Active 2nd RP-1 / LOX // Jet-A / LOX Gas generator 57,800[8]
Engine-2  USA Vast TBA Development 1st RP-1 / LOX Staged, oxidizer-rich 327[9]
290 (SL) 		100,000[9] 100 2.62
Engine-2 Vacuum  USA Vast TBA Development 2nd RP-1 / LOX Staged, oxidizer-rich 365[9] 100,000[9] 2.62
GEM 63  USA Northrop Grumman Atlas V Active Booster HTPB Solid fuel 279.06 (Vac)[10] 1,662,745[11] 49,300 with fuel
GEM 63XL  USA Northrop Grumman Vulcan Active Booster HTPB Solid fuel 280.3 (Vac)[12] 2,025,720[11] 53,400 with fuel
Hadley  USA Ursa Major Technologies Rocket 4 Active 2nd RP-1 / LOX Staged, oxidizer-rich 22,241 (SL)[13] 62
Helix [DE]  Germany Rocket Factory Augsburg RFA One Development 1st, 2nd RP-1/LOX Staged combustion 350,
325 (SL)[14] 		100,000[14] 100[15]
HyPER-15[16]  South Korea Innospace Hanbit-Nano, -Micro, -Mini Development 1st Paraffin / LOX Electric pump 292 150,000[17]
LE-5B  Japan Mitsubishi, JAXA H-IIA,
H-IIB 		Active Upper LH2 / LOX Expander, open 447[18] 137,000 36.0 269 51.93 5
LE-7A  Japan Mitsubishi, JAXA H-IIA,
H-IIB 		Active 1st LH2 / LOX Staged 438[19]
338 (SL)[19] 		1,098,000
870,000 (SL) 		120 1,800 65.9 5.9
LE-9  Japan Mitsubishi, JAXA H-3 Development 1st LH2 / LOX Expander, open 425[20] 1,471,000 100 2,400 62.5 5.9
Lightning 1  USA Firefly Aerospace Alpha Active 2nd RP-1 / LOX Combustion tap-off 322[21] 70,100[21]
Merlin 1D FT  USA SpaceX Falcon 9 B5, Heavy Active 1st RP-1 / LOX Gas generator 311 914,000[22]
845,000 (SL)[22] 		108.0[23] 470 194.5[22]
Merlin Vacuum 1D  USA SpaceX Falcon 9 B5, Heavy Active 2nd RP-1 / LOX Gas generator 348[24] 981,000[25] 2.36
Miranda  USA Firefly Aerospace Antares 300 Series,
MLV 		Development 1st RP-1 / LOX Combustion tap-off 305[26] 1,023,000[26]
M10  EU Avio Vega-E[27] Development Upper[27] CH4 / LOX[27] Expander, closed 362[27] 98,000[27] 3.4[27]
NK-33A (AJ26-62),
11Д111 / 14Д15 		 Soviet Union JSC Kuznetsov Antares 100, Soyuz-2-1v Active 1st RP-1 / LOX Staged, oxidizer-rich 331[28]
297 (SL) 		1,680,000
1,510,000 (SL) 		145 1,222 136.8
P120  Europe Avio Ariane 6,
Vega-C 		Active Booster, 1st HTPB Solid fuel 279[29] 4,650,000[29] 105 153,000 with fuel[29]
S139  India SDSC PSLV Active 1st HTPB Solid fuel 269[30] 4,860,000 58 160,200
with fuel
Raptor[31]  USA SpaceX Starship Development 1st, 2nd CH4 / LOX Staged, full-flow 350[32]
327 (SL)[33] 		2,750,000 (SL)[32] 350[34] 1,525[32] 184[32] 3.6[35]
Raptor Vacuum[31]  USA SpaceX Starship Development 2nd CH4 / LOX Staged, full-flow 380 est.[36] >2,750,000[32] 350[34] >1,525[32] <184[32] 3.6[35]
RD-0124,
14Д23 		 Russia KBKhA Soyuz-2.1b,
Soyuz-2-1v,
Angara 		Active 2nd, 3rd RP-1 / LOX Staged, oxidizer-rich 359[37] 294,300 160 520 57.7
RD-0146D  Russia KBKhA Angara Development Upper LH2 / LOX Expander, closed 470[38] 68,600 59
RD-107A,
14Д22 		 Russia NPO Energomash Soyuz-FG, -2 Active 1st RP-1 / LOX Gas generator 320.2[39]
263.3 (SL) 		1,019,892
839,449 (SL) 		61.2 1,090 78.53
RD-108A,
14Д21 		 Russia NPO Energomash Soyuz-FG, -2 Active 2nd RP-1 / LOX Gas generator 320.6[39]
257.7 (SL) 		921,825
792,377 (SL) 		55.5 1,075 75.16
RD-171M,[c] 11Д520  Russia NPO Energomash Soyuz-5, Zenit-2M, -3SL, -3SLB, -3SLBF Active 1st RP-1 / LOX Staged, oxidizer-rich 337.2[40]
309.5 (SL) 		7,904,160
7,256,921 (SL) 		250 9,300 79.57
RD-180  Russia NPO Energomash Atlas V, III Active 1st RP-1 / LOX Staged, oxidizer-rich 338.4[41]
311.9 (SL) 		4,152,136
3,826,555 (SL) 		261.7 5,480 71.2 2.72
RD-191  Russia NPO Energomash Angara Active 1st RP-1 / LOX Staged, oxidizer-rich 337.5[42]
311.2 (SL) 		2,084,894
1,922,103 (SL) 		262.6 2,200 89.09
RD-193  Russia NPO Energomash Soyuz-2-1v Development 1st RP-1 / LOX Staged, oxidizer-rich 337.5[43]
311.2 (SL) 		2,084,894
1,922,103 (SL) 		1,900 103.15
RD-276,
14Д14М 		 Russia NPO Energomash Proton-M Active 1st N2O4 / UDMH Staged, oxidizer-rich 315.8[44]
288 (SL) 		1,831,882
1,671,053 (SL) 		168.5 1,120 171.2
RD-801  Ukraine Pivdenne/​Pivdenmash Mayak Development 1st RP-1 / LOX Staged, oxidizer-rich 336[45]
300.7 (SL) 		1,339,255
1,198,608 (SL) 		180 1,630 2.65
RD-809K  Ukraine Pivdenne/​Pivdenmash Mayak Development Upper RP-1 / LOX Staged, oxidizer-rich 352[45] 98,067 330 2.62
RD-810  Ukraine Pivdenne/​Pivdenmash Mayak, Zenit Development 1st RP-1 / LOX Staged, oxidizer-rich 335.5[46]
299 (SL) 		2,104,890
1,876,149 (SL) 		180 2,800 2.65
RD-861K  Ukraine Pivdenne/​Pivdenmash Cyclone-4M Development 2nd N2O4 / UDMH Gas generator 330[47] 77,629 207 2.41
RD-870  Ukraine Pivdenne/​Pivdenmash Cyclone-4M Development 1st RP-1 / LOX Staged, oxidizer-rich 340[48]
301.5 (SL) 		876,715
777,667 (SL) 		1,353 2.684
Reaver 1  USA Firefly Aerospace Alpha Active 1st RP-1 / LOX Combustion tap-off 265 (SL)

295.6[21] (Vac)

184,000[21] 75
RL-10A-4-2[49]  USA Aerojet Rocketdyne Atlas IIIB, V Retired Upper LH2 / LOX Expander, closed 451 99,195 42 168 60.27 5.5
RL-10B-2[49]  USA Aerojet Rocketdyne Delta III, IV, SLS Active Upper LH2 / LOX Expander, closed 465.5 110,093 44 301 37.27 5.88
RL-10C-1[49]  USA Aerojet Rocketdyne Delta III, IV, SLS, Vulcan Active Upper LH2 / LOX Expander, closed 450 101,820 44 191 54.5 5.5
RS-25  USA Rocketdyne Space Shuttle, SLS Active 1st LH2 / LOX Staged, fuel-rich 452.3
366 (SL) 		2,279,000
1,860,000 (SL)[50] 		206.4 3,526 53.79
Rutherford  New Zealand  USA Rocket Lab Electron Active 1st RP-1 / LOX Electric pump 311 24,900
25,000 (SL) 		55 35[51] 72.8 (SL)
Rutherford Vacuum  New Zealand  USA Rocket Lab Electron Active 2nd RP-1 / LOX Electric pump 343 25,800[51]
S200  India SDSC GSLV Mk III Active Booster HTPB Solid fuel 274.5[52] 5,150,000[53][54][55] 207,000
with fuel[52]
SCE-200  India LPSC GSLV Mk III,
ULV 		Development Upper, main RP-1 / LOX Staged, oxidizer-rich 335
299 (SL) 		2,030,000
1,820,000 (SL) 		180 2,700
SLS Solid Rocket Booster[d]  USA Orbital ATK SLS Active Booster PBAN Solid fuel 267 16,000,000 730,000
with fuel
SLV-1  India Godrej & Boyce PSLV Active Booster HTPB Solid fuel 253[56] 502,600 43 10,800
with fuel
SRB-A3  Japan IHI Aerospace,
JAXA 		H-IIA,
H-IIB,
Epsilon 		Active Booster HTPB Solid fuel 283.6[57] 2,305,000
2,150,000 (SL) 		111 76,600
with fuel
TEPREL-B  Spain PLD Space Miura 1 Active 1st RP-1 / LOX Pressure-fed 30,200 (SL)
TEPREL-C  Spain PLD Space Miura 5 Development 1st, 2nd RP-1 / LOX Gas-generator 190,000 (SL)
TQ-12[58]  China Landspace ZQ-2 Active 1st CH4 / LOX Gas generator 284 667,000 (SL) 101
Vikas (rocket engine)  India LPSC PSLV, GSLV, GSLV Mk III Active 2nd, main, booster N2O4 / UDMH Gas generator 262 680,500–804,500
600,500–756,500 (SL) 		53.0–58.5
Vinci  Europe Snecma Ariane 6 Active Upper LH2 / LOX Expander, closed[59] 457[60] 180,000 60 280 65.60 6.1
Vulcain 2.1  Europe Snecma Ariane 6 Active 1st LH2 / LOX Gas generator 1,324,000 120.8 2,000 66.2
YF-21B  China AALPT Long March 2E, 2F, 3 Active Booster, 1st N2O4 / UDMH Gas generator 260.66 (SL)[61] 740,400 (SL)[61]
YF-21C  China AALPT Long March 2C, 2D, 3A, 3B, 3C, 4B, 4C Active 1st N2O4 / UDMH Gas generator 260.7 (SL)[61] 740,400 (SL)[61]
YF-25  China AALPT Long March 3B, 3C Active Booster N2O4 / UDMH Gas generator 260.66 (SL)[61] 740,400 (SL)[61]
YF-22B  China AALPT Long March 2E, 2F Active 2nd N2O4 / UDMH Gas generator 298.0[61] 738,400
YF-22C  China AALPT Long March 2C, 2D, 4B, 4C Active 2nd N2O4 / UDMH Gas generator 298.0[61] 742,040
YF-22D  China AALPT Long March 3 Active 2nd N2O4 / UDMH Gas generator 298.0[61] 741,400
YF-22E  China AALPT Long March 3A, 3B, 3C Active 2nd N2O4 / UDMH Gas generator 298.0[61] 741,400
YF-40  China AALPT Long March 4B, 4C Active 3rd N2O4 / UDMH Gas generator 303 103,000
YF-50D  China AALPT Long March 3B, 3C, 5, 7 Active Upper N2O4 / UDMH Pressure-fed 315.5 6,500
YF-73  China AALPT Long March 3 Active 3rd LH2 / LOX Gas generator 420.0 44,150
YF-75  China AALPT Long March 3A, 3B, 3C Active 3rd LH2 / LOX Gas generator 438.0[61] 78,450
YF-75D  China AALPT Long March 5 Active 2nd LH2 / LOX Expander, closed 442.6 88,360 41 265 34 6.0
YF-77  China AALPT Long March 5 Active 1st LH2 / LOX Gas generator 428
316.7 (SL) 		700,000
518,000 (SL) 		102 1,054 50 5.5
YF-79  China AALPT Long March 9 Development 3rd LH2 / LOX Expander, closed 455.2 250,000 70 6.0
YF-90[62]  China AALPT Long March 9 Development 2nd LH2 / LOX Staged, fuel-rich 453 2,200,000 183 4,800 46.74 6.0
YF-100  China AALPT Long March 7, 5 Active 1st RP-1/ LOX Staged, oxidizer-rich 335.1
300(SL) 		1,339,480
1,199,190 (SL) 		180 1,912 64 2.6
YF-115  China AALPT Long March 6, 7 Active 2nd RP-1/ LOX Staged, oxidizer-rich 341.5 182,400 120 2.5
YF-130  China AALPT Long March 9 Development 1st RP-1/ LOX Staged, oxidizer-rich 308 (SL) ~5,000,000 (SL) 220 ~6,500 78 2.62
Zefiro 9A  European Union Avio Vega-C Active 3rd HTPB Solid fuel 295.2[63] 314,000[63] 75 11,400 with fuel
Zefiro 40  European Union Avio Vega-C Active 3rd HTPB Solid fuel 293.5[64] 1,304,000[64] 115 39,206 with fuel

Retired and canceled rocket engines

[edit]
Engine Origin Designer Vehicle Use Propellant Power cycle Specific impulse (s)[a] Thrust (N)[a] Chamber pressure (bar) Mass (kg) Thrust:​weight ratio[e] Oxidiser:​fuel ratio
Aeon 1  USA Relativity Space Terran 1 1st CH4 / LOX Gas generator 310 86,740 (SL)[65]
Aeon 1 Vacuum  USA Relativity Space Terran 1 2nd CH4 / LOX Gas generator 360 100,085 (SL)[65]
Aestus  Europe Airbus Defence and Space Ariane 5 G, G+, ES Upper N2O4 / MMH Pressure-fed 324[66] 30,000 11 111 27.6 1.9
Aestus II  Europe Airbus Defence and Space Ariane 5 Upper N2O4 / MMH Gas generator 340[67] 55,400 60 138 41.0 1.9
Aether  USA Astra Space Rocket 3.3 2nd RP-1/LOX[68] Pressure-fed 3,300[69]
AJ-60A  USA Aerojet Atlas V Booster HTPB Solid fuel 275 1,270,000[70]
AJ-260-2 United States USA Aerojet S-I stage replacement (proposed) 1st PBAN Solid fuel 263 26,183,755 831,345 with fuel
AR1  USA Aerojet Rocketdyne 1st RP-1 / LOX Staged, oxidizer-rich 2,200,000 (SL)[71] 2.72
Delphin  USA Astra Space Rocket 3.3 1st RP-1/LOX[68] Electric pump 29,000[69] 31
F-1[f]  USA Rocketdyne Saturn V 1st RP-1 / LOX Gas generator 304
263 (SL) 		7,770,000
6,770,000 (SL) 		70 8,391 82.27 2.27
F-1A[g][72]  USA Rocketdyne 1st RP-1 / LOX Gas generator 303
270 (SL) 		8,989,000
8,007,000 (SL) 		80 9,015 90.6 2.27
Gamma 2  United Kingdom Bristol Siddeley Black Arrow 2nd RP-1 / H2O2 Staged, decomposition and combustion 265[73] 68,200 173 40.22 8
Gamma 8  United Kingdom Bristol Siddeley Black Arrow 1st RP-1 / H2O2 Staged, decomposition and combustion 265[74] 234,800 47.40 342 70.01 8
HM-7A  Europe Snecma Ariane 1 3rd LH2 / LOX Gas generator 443[75]
308 (SL) 		61,700 30 149 42.2 5
HM-7B  Europe Snecma Ariane 2, 3, 4, 5 ECA Upper LH2 / LOX Gas generator 446[76]
310 (SL)[77] 		64,800[76]
43,600 (SL)[77] 		37[76] 165[76] 43.25 5
J-2  USA Rocketdyne Saturn V, IB 2nd, 3rd LH2 / LOX Gas generator 421[78]
200 (SL) 		1,033,100
486,200 (SL) 		52.6 1,438 73.18 5.5
J-2X  USA Pratt & Whitney Rocketdyne SLS (proposed) Upper LH2 / LOX Gas generator 448[79] 1,310,000 95 2,470 58.41 5.5–4.5
Kestrel  USA SpaceX Falcon 1 Upper RP-1 / LOX Pressure fed 317 31,000 9.3 52 65
LE-5  Japan Mitsubishi, NASDA H-I Upper LH2 / LOX Gas generator 450[80] 103,000 36.0 245 42.87 5.5
LE-5A  Japan Mitsubishi, NASDA H-II Upper LH2 / LOX Expander, open 452[81] 121,500 40.0 242 51.19 5
LE-7  Japan Mitsubishi, NASDA H-II 1st LH2 / LOX Staged combustion 446[82] 1,078,000
843,500 (SL) 		127 1,714 64.13 5.9
M-1  USA Aerojet 1st, 2nd? LH2 / LOX Gas generator 428 (SL) 6,670,000 9,068 60
Merlin 1D  USA SpaceX Falcon 9 v1.1 1st RP-1 / LOX Gas generator 311[83]
282 (SL)[83] 		723,000 97 470 158 2.34
Merlin Vacuum 1C  USA SpaceX Falcon 1, 9 2nd RP-1 / LOX Gas generator 336[84] 413,644[84] 92
NewtonThree  USA Virgin Orbit LauncherOne Booster RP-1 / LOX Gas generator[85] 266,893[86] 70
NewtonFour  USA Virgin Orbit LauncherOne 2nd RP-1 / LOX Gas generator[85] 22,241[86]
P80  Europe Avio Vega 1st HTPB Solid fuel 280[87] 3,015,000[87] 88 96,000 with fuel
P230  Europe Avio Ariane 5 Booster HTPB Solid fuel 286[88]
259 (SL) 		6,996,000
5,860,000 (SL) 		69 269,000 with fuel[88]
RD-0120
11Д122 		 Soviet Union KBKhA Energia 1st LH2 / LOX Staged, fuel-rich 455[89] 1,962,000
1,526,000 (SL) 		219 3,450 57.80
RD-8,
11D513 		 Soviet Union Pivdenne/​Pivdenmash Zenit 2nd vernier RP-1 / LOX Staged, oxidizer-rich 342 78,450 77.47 356 2.4
RD-56 (KVD-1)
11Д56У 		 Russia KBKhM GSLV Mk I Upper LH2 / LOX Staged, fuel-rich 462[90] 69,626 55.9 282 25.17
RD-117
11Д511 		 Soviet Union NPO Energomash Soyuz-U 1st RP-1 / LOX Gas generator 316[91]
253 (SL) 		978,000
778,648 (SL) 		54.2 1,100 72.18
RD-118
11Д512 		 Soviet Union NPO Energomash Soyuz-U 2nd RP-1 / LOX Gas generator 314[91]
257 (SL) 		1,000,278
818,855 (SL) 		59.7 1,100 75.91
RD-170[h]11Д521[92]  Soviet Union NPO Energomash Energia 1st RP-1 / LOX Staged, oxidizer-rich 337.2
309.5 (SL) 		7,904,160
7,256,921 (SL) 		250 9,300 79.57
RD-181  Russia NPO Energomash Antares 200 1st RP-1 / LOX Staged, oxidizer-rich 339.2[93]
311.9 (SL) 		2,085,000
1,922,000 (SL) 		262.6 2,200 89
RD-264
11Д119 		 Soviet Union NPO Energomash Dnepr 1st N2O4 / UDMH Staged, oxidizer-rich 318[94]
293 (SL) 		4,521,000 206 3,600 128.15
RD-270[i]
8Д420 		 Soviet Union NPO Energomash UR-700 (proposed), UR-900 (proposed) 1st N2O4 / UDMH Staged, full-flow 322[95]
301 (SL) 		6,710,000
6,270,000 (SL) 		261 3,370 189.91
RD-275
14Д14 		 Russia NPO Energomash Proton-M 1st N2O4 / UDMH Staged, oxidizer-rich 316[96]
287 (SL) 		1,831,882
1,671,053 (SL) 		160.0 1,070 171.2
RD-843  Ukraine Pivdenne/​Pivdenmash Vega upper N2O4 / UDMH Pressure-fed 315.5 2,452 20.4 15.93 2.0
RD-854
8D612 		 Soviet Union Pivdenne/​Pivdenmash R-36ORB 3rd N2O4 / UDMH Gas generator
RD-855
8D68M 		 Soviet Union Pivdenne/​Pivdenmash Tsyklon-2, -3, R-36 1st vernier N2O4 / UDMH Gas generator 328,000 65.70 320 1.97
RD-856
8D69M 		 Soviet Union Pivdenne/​Pivdenmash Tsyklon-2, -3 (-4), R-36 2nd vernier N2O4 / UDMH Gas generator 54,230 71.60 112.5 1.98
RD-861
11D25 		 Soviet Union Pivdenne/​Pivdenmash Tsyklon-2, -3 3rd N2O4 / UDMH Gas generator 78,710 88.8 123 2.1
RD-864
15D177 		 Soviet Union Pivdenne/​Pivdenmash R-36 (missile), Dnipro 3rd N2O4 / UDMH Gas generator 298–309 8,450–20,200 17–41 199 1.8
RD-869
15D300 		 Soviet Union Pivdenne/​Pivdenmash R-36M 3rd N2O4 / UDMH Gas generator 302.3–313 8,580–20,470 17–41 196 1.8
RS-27A  USA Rocketdyne Delta 1st RP-1 / LOX Gas generator 302[97]
255 (SL) 		1,054,200 49 1,091 102.5 2.245
RS-68A[j]  USA Rocketdyne Delta IV, IV Heavy 1st LH2 / LOX Gas generator 411[98]
362 (SL) 		3,558,577
3,135,996 (SL) 		109 6,686 54.31 5.97
Space Shuttle Solid Rocket Booster[k]  USA Thiokol Space Shuttle, Ares I Booster PBAN / APCP Solid fuel 268 14,000,000
12,500,000 (SL) 		590,000
with fuel
SRB-A  Japan IHI Aerospace, JAXA H-IIA Booster HTPB Solid fuel 280[99] 2,250,000 76,400 with fuel
UA1207  USA United Technologies Titan IV Booster PBAN Solid fuel 272[100]
245 (SL) 		7,116,000
6,410,400 (SL) 		319,330
with fuel
Viking 2  Europe Snecma Ariane 1 1st N2O4 / UDMH Gas generator 690,000
611,200 (SL) 		776 90.67
Viking 2B  Europe Snecma Ariane 2, 3 1st N2O4 / UH 25 Gas generator 643,000 (SL) 776 84.5
Viking 4  Europe Snecma Ariane 1 2nd N2O4 / UDMH Gas generator 713,000 826 88
Viking 4B  Europe Snecma Ariane 2, 3, 4 2nd N2O4 / UH 25 Gas generator 800,000 826 98.76
Viking 5C  Europe Snecma Ariane 4 1st N2O4 / UH 25 Gas generator 758,000
678,000 (SL) 		826 93.57
Viking 6  Europe Snecma Ariane 4 Booster N2O4 / UH 25 Gas generator 750,000 826 92.59
Vulcain
HM-60 		 Europe Snecma Ariane 5 1st LH2 / LOX Gas generator 439[101]
326 (SL)[102] 		1,113,000[101]
773,200 (SL)[102] 		109[101] 1,300[102] 84.38
Vulcain 2  Europe Snecma Ariane 5 1st LH2 / LOX Gas generator 429[103]
318 (SL)[104] 		1,359,000[103]
939,500 (SL)[104] 		117.3[103] 1,800[103] 77.04
Waxwing  United Kingdom Bristol Aerojet Black Arrow Upper Solid fuel 278[105]
245 (SL) 		29,400
25,900 (SL) 		87 34.48
Zefiro 23  European Union Avio Vega 2nd HTPB Solid fuel 287.5[106] 1,122,000[106] 94 25,935 with fuel

See also

[edit]

Notes

[edit]
  1. ^ a b c d At sea level if denoted SL, in vacuum otherwise
  2. ^ Weight is calculated at standard gravity.
  3. ^ Most powerful multi-chamber rocket engine in the world
  4. ^ Largest, most powerful solid-fuel rocket motor ever built
  5. ^ Weight is calculated at standard gravity.
  6. ^ Most powerful single-chamber liquid-fueled rocket engine ever developed
  7. ^ Tested but never flown
  8. ^ World's most powerful liquid fueled rocket engine
  9. ^ Tested but never flown
  10. ^ Most powerful hydrogen-fueled engine in the world
  11. ^ Largest solid-fuel rocket motor ever flown, and the first to be used for primary propulsion on human spaceflight missions

References

[edit]
  1. ^ a b c d "In-Space Product Data Sheets" (PDF). Aerojet Rocketdyne. September 13, 2019. Archived from the original (PDF) on January 11, 2020. Retrieved January 29, 2020.
  2. ^ "BE-3". Blue Origin.
  3. ^ a b c d "First Look Inside Blue Origin's New Glenn Factory w/ Jeff Bezos!". YouTube. August 15, 2024. Retrieved August 16, 2024.
  4. ^ Belam, Martin (January 8, 2024). "Nasa Peregrine 1 launch: Vulcan Centaur rocket carrying Nasa moon lander lifts off in Florida – live updates". the Guardian. ISSN 0261-3077. Retrieved January 8, 2024.
  5. ^ Ferster, Warren (September 17, 2014). "ULA To Invest in Blue Origin Engine as RD-180 Replacement". Space News. Archived from the original on September 18, 2014. Retrieved September 19, 2014.
  6. ^ "BE-4". Blue Origin. Archived from the original on September 17, 2014. Retrieved September 17, 2014.
  7. ^ "GSLV Launch Vehicle Information". Spaceflight101.com. Archived from the original on January 6, 2014. Retrieved January 6, 2014.
  8. ^ a b "RS1". ABL. Retrieved August 21, 2022.
  9. ^ a b c d "Engine-2". LAUNCHER. Archived from the original on October 26, 2021. Retrieved November 9, 2019.
  10. ^ "NG Prop Catalog" (PDF). December 10, 2020. Archived from the original (PDF) on December 10, 2020.
  11. ^ a b "Developing Vulcan Centaur". ULA. April 4, 2019. Archived from the original on August 25, 2019.
  12. ^ "NG Prop Catalog" (PDF). December 10, 2020. Archived from the original (PDF) on December 10, 2020.
  13. ^ "The Engines". Ursa Major Technologies. Retrieved May 20, 2017.
  14. ^ a b Arizaga, Monica (March 18, 2022). ""Helix" - public names RFA engine". Rocket Factory Augsburg. Retrieved September 28, 2023.
  15. ^ Arizaga, Monica (July 13, 2022). "RFA successfully hot fires Helix engine for a total of 74 seconds". Rocket Factory Augsburg. Retrieved September 28, 2023.
  16. ^ "South Korea's INNOSPACE will launch Brazilian payload on inaugural flight from Alcântara". May 7, 2022.
  17. ^ "innospacecorp on Twitter: "Very proud and excited as we get ready to test the world's largest LOx/Paraffin Hybrid rocket engine developed for a smallsat Launcher.The HyPER-15, a 150kN Hybrid rocket engine, is scheduled to test this month at our Geumsan Engine Test Facility. Keep an eye out for our updates!"". Twitter. Retrieved July 26, 2021.
  18. ^ "LE-5B". Encyclopedia Astronautica. Archived from the original on October 27, 2016. Retrieved January 13, 2016.
  19. ^ a b "LE-7A". Encyclopedia Astronautica. Archived from the original on February 28, 2017. Retrieved January 13, 2016.
  20. ^ "LE-9" (PDF).
  21. ^ a b c d "Launch-alpha". Firefly Aerospace. Archived from the original on February 24, 2021. Retrieved February 2, 2020.
  22. ^ a b c "Merlin 1D". SpaceX. Archived from the original on September 6, 2015. Retrieved February 26, 2016.
  23. ^ "Evolution of the SpaceX Merlin engine". www.b14643.de. Retrieved May 8, 2022.
  24. ^ "SpaceX Falcon 9 Product Page". Archived from the original on August 5, 2014. Retrieved November 1, 2015.
  25. ^ "SpaceX". SpaceX. Retrieved September 24, 2020.
  26. ^ a b "MLV". Retrieved August 16, 2024.
  27. ^ a b c d e f "M10 Engine". Avio.
  28. ^ "NK-33". Encyclopedia Astronautica. Archived from the original on June 25, 2002. Retrieved January 30, 2014.
  29. ^ a b c Press release: Successful first test firing for the P120C solid rocket motor for Ariane 6 and Vega-C
  30. ^ "PSLV-1". Archived from the original on August 5, 2014. Retrieved April 4, 2014.
  31. ^ a b "Spacex Raptor". NASA SpaceFlight. March 7, 2014. Retrieved July 2, 2015.
  32. ^ a b c d e f g "Raptor 3 (sea level variant) Thrust: 280tf Specific impulse: 350s Engine mass: 1525kg Engine + vehicle-side commodities and hardware mass : 1720kg". August 3, 2024.
  33. ^ "Raptor 1 vs Raptor 2: What did SpaceX change?". July 14, 2022.
  34. ^ a b "Raptor V3 just achieved 350 bar chamber pressure (269 tons of thrust). Congrats to @SpaceX propulsion team! Starship Super Heavy Booster has 33 Raptors, so total thrust of 8877 tons or 19.5 million pounds". May 13, 2023.
  35. ^ a b Katy Groom; Rebecca Bolt; Resa Cancro; Patrice Hall; Kandi Lawson; Mark Mercadante; Michelle Moore; Jane Provancha; Matthew Thompson; Don Dankert; James Brooks; Daniel Czelusnaik; Eva Long (August 1, 2019). "Draft Environmental Assessment for the SpaceX Starship and Super Heavy Launch Vehicle at Kennedy Space Center (KSC)" (PDF). netspublic.grc.nasa.gov. Space Exploration Technologies Corporation. p. 250. Archived (PDF) from the original on August 2, 2019. Retrieved August 5, 2019.
  36. ^ "In a few years, we will finally have a Raptor 3/4 vacuum version (giant nozzle) that has an Isp of 380". August 3, 2024.
  37. ^ "RD-0124 Engine". KBKha. Retrieved January 7, 2016.
  38. ^ "ГКНПЦ имени М.В.Хруничева | Жидкостный ракетный двигатель РД - 0146". www.khrunichev.ru. Archived from the original on December 29, 2021. Retrieved July 27, 2019.
  39. ^ a b "RD-107A and RD-108A". NPO Energomash. Retrieved June 30, 2015.
  40. ^ "RD-171M". NPO Energomash. Retrieved June 30, 2015.
  41. ^ "RD-180". NPO Energomash. Retrieved June 30, 2015.
  42. ^ "RD-191". NPO Energomash. Retrieved June 30, 2015.
  43. ^ "Универсальный ракетный двигатель РД-193. Мнение инженера-разработчика". Журнал «Новости космонавтики». Archived from the original on October 18, 2016. Retrieved January 6, 2016.
  44. ^ "RD-276 "Comrade"". NPO Energomash. Archived from the original on January 27, 2022. Retrieved October 14, 2019.
  45. ^ a b "RD-801". www.yuzhnoye.com. Archived from the original on February 25, 2022. Retrieved January 19, 2020.
  46. ^ "RD-810". www.yuzhnoye.com. Archived from the original on February 25, 2022. Retrieved January 19, 2020.
  47. ^ "RD-861K". www.yuzhnoye.com. Archived from the original on February 25, 2022. Retrieved January 19, 2020.
  48. ^ "RD-870". Yuzhnoye SDO. Archived from the original on February 25, 2022. Retrieved January 19, 2020.
  49. ^ a b c "RL10 Data Sheet-1" (PDF). February 2016. Archived from the original (PDF) on July 5, 2016. Retrieved March 23, 2019.
  50. ^ Aerojet Rocketdyne, RS-25 Engine Archived 2015-12-29 at the Wayback Machine (accessed July 22, 2014)
  51. ^ a b "Rocket Lab Increases Electron Payload Capacity, Enabling Interplanetary Missions and Reusability". Rocket Lab. Retrieved October 26, 2020.
  52. ^ a b "LVM3". Archived from the original on September 10, 2015. Retrieved December 21, 2014.
  53. ^ "ISRO Press Release: S200 First Static Test (S-200-ST-01)" (PDF). Archived from the original (PDF) on March 11, 2013. Retrieved September 25, 2015.
  54. ^ "Isro successfully tests world's 3rd largest solid booster". dna. Retrieved October 4, 2014.
  55. ^ "India to test world's third largest solid rocket booster". Science and Technology Section. The Hindu News Paper. December 7, 2009. Retrieved December 7, 2009.
  56. ^ "SLV-1". Archived from the original on August 5, 2014. Retrieved April 4, 2014.
  57. ^ "SRB-A3". Spaceflight101. Retrieved January 13, 2016.
  58. ^ “天鹊”80吨液氧甲烷发动机100%推力100秒试车圆满成功
  59. ^ "Vinci". Encyclopedia Astronautica. Archived from the original on October 27, 2016. Retrieved June 10, 2017.
  60. ^ "Vinci® engine" (PDF). Ariane. Retrieved October 10, 2022.
  61. ^ a b c d e f g h i j k "2.2 LM-3A Launch Vehicle". LM-3A Series Launch Vehicle User's Manual. Issue 2011 (PDF). CASC. 2011. pp. 2–4. Retrieved January 16, 2016.
  62. ^ 孙纪国,郑孟伟,龚杰峰,陶瑞峰 (January 15, 2022). "220tf补燃循环氢氧发动机研制进展" (in Simplified Chinese). 《火箭推进》2022年02期. Retrieved June 5, 2022.{{cite web}}: CS1 maint: multiple names: authors list (link)
  63. ^ a b "VEGA C: 3° stage - zefiro 9". Avio.com. Archived from the original on June 5, 2019. Retrieved January 20, 2020.
  64. ^ a b "Zefiro 40 Motor Main Characteristics". Avio.com. Retrieved May 24, 2021.
  65. ^ a b "Terran 1 Technical Specifications". Relativity. Retrieved October 5, 2019.
  66. ^ "Aestus Rocket Engine". Airbus Defence and Space. Archived from the original on April 20, 2015. Retrieved January 29, 2014.
  67. ^ "Aestus Rocket Engine". Airbus Defence and Space. Archived from the original on May 28, 2015. Retrieved January 29, 2014.
  68. ^ a b "Astra Space Rocket". www.spacelaunchreport.com. Retrieved July 3, 2020.
  69. ^ a b "Astra Media Kit LV0006" (PDF). August 28, 2021.
  70. ^ "Atlas V Solid Rocket Motor". Aerojet Rocketdyne. Archived from the original on March 14, 2017. Retrieved June 2, 2015.
  71. ^ "AR1 Engine". Aerojet Rocketdyne. Archived from the original on March 4, 2016. Retrieved October 26, 2016.
  72. ^ Alternate Propulsion Subsystem Concepts NAS8-39210 DCN 1-1-PP-02147
  73. ^ "Gamma 2". Encyclopedia Astronautica. Archived from the original on May 22, 2013. Retrieved April 26, 2013.
  74. ^ "Gamma 8". Encyclopedia Astronautica. Archived from the original on May 22, 2013. Retrieved April 26, 2013.
  75. ^ Wade, Mark. "HM7-A". Encyclopedia Astronautica. Archived from the original on December 21, 2016. Retrieved June 10, 2017.
  76. ^ a b c d "HM-7 and HM-7B Rocket Engine - Thrust Chamber". Airbus Defence and Space. Archived from the original on March 18, 2015. Retrieved November 1, 2015.
  77. ^ a b Wade, Mark. "HM7-B". Encyclopedia Astronautica. Archived from the original on December 27, 2016. Retrieved June 10, 2017.
  78. ^ Wade, Mark. "J-2". Encyclopedia Astronautica. Archived from the original on July 19, 2016. Retrieved December 23, 2011.
  79. ^ "J-2X Engine". Pratt & Whitney Rocketdyne. Archived from the original on January 3, 2012. Retrieved December 23, 2011.
  80. ^ "LE-5". Encyclopedia Astronautica. Archived from the original on October 27, 2016. Retrieved January 13, 2016.
  81. ^ "LE-5A". Encyclopedia Astronautica. Archived from the original on March 11, 2016. Retrieved January 13, 2016.
  82. ^ "LE-7". Encyclopedia Astronautica. Archived from the original on March 11, 2016. Retrieved January 13, 2016.
  83. ^ a b "Merlin section of Falcon 9 page". SpaceX. Archived from the original on July 15, 2013. Retrieved October 16, 2012.
  84. ^ a b "Falcon 9 Space Launch Report". SpaceLaunchReport. Retrieved November 1, 2015.
  85. ^ a b Sargent, Scott R.; Noall, Jeff; Becker, Matthew; MacKlin, Scott (2016). "Turbopump Design and Development for the Virgin Galactic Newton Three Engine System". 52nd AIAA/SAE/ASEE Joint Propulsion Conference. doi:10.2514/6.2016-4984. ISBN 978-1-62410-406-0.
  86. ^ a b "LauncherOne Service Guide" (PDF). Archived from the original (PDF) on October 22, 2017.
  87. ^ a b "VEGA: 1° stage - P80 Motor". Avio.com. Retrieved January 20, 2020.
  88. ^ a b "P230". Encyclopedia Astronautica. Archived from the original on December 31, 2011. Retrieved December 27, 2011.
  89. ^ "RD0120". KBKhA.
  90. ^ "KVD1 Rocket Engine" Двигатель КВД1 (in Russian). КБХМ им. A.M. Исаева. Archived from the original on February 2, 2014. Retrieved May 31, 2013.
  91. ^ a b "RD-117". Liquid Propellant Rocket Engines. Archived from the original on August 26, 2012. Retrieved November 27, 2012.
  92. ^ "RD-170". Encyclopedia Astronautica. Archived from the original on August 8, 2016. Retrieved September 24, 2019.
  93. ^ "Antares 200 Series – Rockets".
  94. ^ Wade, Mark. "RD-264". Encyclopedia Astronautica. Archived from the original on October 14, 2016. Retrieved June 10, 2017.
  95. ^ "RD-270 (8D420)". NPO Energomash. Retrieved February 6, 2023.
  96. ^ "RD-253 and RD-275". NPO Energomash. Archived from the original on April 5, 2015. Retrieved June 30, 2015.
  97. ^ "RS-27A". Encyclopedia Astronautica. Archived from the original on August 25, 2016. Retrieved November 2, 2021.
  98. ^ "RS-68A". www.rocket.com. Retrieved January 19, 2020.
  99. ^ "SRB-A". Encyclopedia Astronautica. Archived from the original on March 1, 2002. Retrieved January 13, 2016.
  100. ^ "UA1207". Encyclopedia Astronautica. Archived from the original on March 4, 2016. Retrieved December 27, 2015.
  101. ^ a b c "Vulcain Astrium". Airbus Defence and Space. Archived from the original on February 25, 2012. Retrieved December 27, 2011.
  102. ^ a b c "Vulcain". Encyclopedia Astronautica. Archived from the original on December 28, 2016. Retrieved December 27, 2011.
  103. ^ a b c d "Vulcain Astrium". Airbus Defence and Space. Archived from the original on March 27, 2012. Retrieved December 27, 2011.
  104. ^ a b "Vulcain 2". Encyclopedia Astronautica. Archived from the original on December 28, 2016. Retrieved December 27, 2011.
  105. ^ "Black Arrow-3". Encyclopedia Astronautica. Archived from the original on December 28, 2016. Retrieved April 26, 2013.
  106. ^ a b "VEGA: 2° stage - zefiro 23". Avio.com. Retrieved January 20, 2020.
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