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Comparison of orbital rocket engines

Topic: Astronomy

 From HandWiki - Reading time: 13 min
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This page is an incomplete list of orbital rocket engine data and specifications.

Current, Upcoming, and In-Development rocket engines

Engine Origin Designer Vehicle Status Use Propellant Power cycle Specific impulse (s)[lower-alpha 1] Thrust (N)[lower-alpha 1] Chamber pressure (bar) Mass (kg) Thrust:​weight ratio[lower-alpha 2] 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 CH4 / LOX Staged, oxidizer-rich 730,000
Aeon-R  USA Relativity Space Terran R Development 1st, 2nd CH4 / LOX Gas generator
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 710,000[2]
BE-4  USA Blue Origin New Glenn, Vulcan Active[3] 1st CH4 / LOX Staged, oxidizer-rich 339[4] 2,400,000[5][6] 134[7]
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[8] 73,500 58 445 16.85
E2  USA ABL Space Systems RS1 Active 1st RP-1 / LOX Gas generator 53,800[9]
E2 Vacuum  USA ABL Space Systems RS1 Active 2nd RP-1 / LOX Gas generator 57,800[9]
Engine-2  USA Vast TBA Development 1st RP-1 / LOX Staged, oxidizer-rich 327[10]
290 (SL) 		100,000[10] 2.62
Engine-2 Vacuum  USA Vast TBA Development 2nd RP-1 / LOX Staged, oxidizer-rich 365[10] 100,000[10] 2.62
GEM 63  USA Northrop Grumman Atlas V Active Booster HTPB Solid fuel 279.06 (Vac)[11] 1,662,745[12] 49,300 with fuel
GEM 63XL  USA Northrop Grumman Vulcan Active Booster HTPB Solid fuel 280.3 (Vac)[13] 2,025,720[12] 53,400 with fuel
Hadley  USA Ursa Major Technologies Rocket 4 Active 2nd RP-1 / LOX Staged, oxidizer-rich 22,241 (SL)[14]
 Germany Rocket Factory Augsburg RFA One Development 1st, 2nd RP-1/LOX Staged combustion 350,
325 (SL)[15] 		100,000[15] 100[16]
HM-7B  Europe Snecma Ariane 2, 3, 4, 5 ECA Active Upper LH2 / LOX Gas generator 446[17]
310 (SL)[18] 		64,800[17]
43,600 (SL)[18] 		37[17] 165[17] 43.25 5
HyPER-15[19]  South Korea Hanbit-Nano, -Micro, -Mini Development 1st Paraffin / LOX Electric pump 292 150,000[20]
LE-5B  Japan Mitsubishi, JAXA H-IIA,
H-IIB 		Active Upper LH2 / LOX Expander, open 447[21] 137,000 36.0 269 51.93 5
LE-7A  Japan Mitsubishi, JAXA H-IIA,
H-IIB 		Active 1st LH2 / LOX Staged 438[22]
338 (SL)[22] 		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[23] 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[24] 70,100[24]
Merlin 1D FT  USA SpaceX Falcon 9 B5, Heavy Active 1st RP-1 / LOX Gas generator 311 914,000[25]
845,000 (SL)[25] 		108.0[26] 470 194.5[25]
Merlin Vacuum 1D  USA SpaceX Falcon 9 B5, Heavy Active 2nd RP-1 / LOX Gas generator 348[27] 981,000[28] 2.36
M10  EU Avio Vega-E[29] Development Upper[29] CH4 / LOX[29] Expander, closed 362[29] 98,000[29] 3.4[29]
NK-33A (AJ26-62),
11Д111 / 14Д15 		 Soviet Union JSC Kuznetsov Antares 100, Soyuz-2-1v Active 1st RP-1 / LOX Staged, oxidizer-rich 331[30]
297 (SL) 		1,680,000
1,510,000 (SL) 		145 1,222 136.8
P80  Europe Avio Vega Active 1st HTPB Solid fuel 280[31] 3,015,000[31] 88 96,000 with fuel
P120  Europe Avio Ariane 6,
Vega-C 		Active Booster, 1st HTPB Solid fuel 279[32] 4,650,000[32] 105 153,000 with fuel[32]
S139  India SDSC PSLV Active 1st HTPB Solid fuel 269[33] 4,860,000 58 160,200
with fuel
Raptor[34]  USA SpaceX Starship Development 1st, 2nd CH4 / LOX Staged, full-flow 350[35]
327 (SL) 		2,640,000 (SL)[36] 350[36] 1,600 est.[37] 168 est.[36][37] 3.6[38]
Raptor Vacuum[34]  USA SpaceX Starship Development 2nd CH4 / LOX Staged, full-flow 380[35] >2,640,000 [36] 350[36] >1,600[37] <120[39] 3.6[38]
RD-0124,
14Д23 		 Russia KBKhA Soyuz-2.1b,
Soyuz-2-1v,
Angara 		Active 2nd, 3rd RP-1 / LOX Staged, oxidizer-rich 359[40] 294,300 160 520 57.7
RD-0146D  Russia KBKhA Angara Development Upper LH2 / LOX Expander, closed 470[41] 68,600 59
RD-107A,
14Д22 		 Russia NPO Energomash Soyuz-FG, -2 Active 1st RP-1 / LOX Gas generator 320.2[42]
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[42]
257.7 (SL) 		921,825
792,377 (SL) 		55.5 1,075 75.16
RD-171M,[lower-alpha 3] 11Д520  Russia NPO Energomash Soyuz-5, Zenit-2M, -3SL, -3SLB, -3SLBF Active 1st RP-1 / LOX Staged, oxidizer-rich 337.2[43]
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[44]
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[45]
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[46]
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[47]
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 [48]
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 [48] 98,067 330 2.62
RD-810  Ukraine Pivdenne/​Pivdenmash Mayak, Zenit Development 1st RP-1 / LOX Staged, oxidizer-rich 335.5 [49]
299 (SL) 		2,104,890
1,876,149 (SL) 		180 2,800 2.65
RD-843  Ukraine Pivdenne/​Pivdenmash Vega Active upper N2O4 / UDMH Pressure-fed 315.5 2,452 20.4 15.93 2.0
RD-861K  Ukraine Pivdenne/​Pivdenmash Cyclone-4M Development 2nd N2O4 / UDMH Gas generator 330 [50] 77,629 207 2.41
RD-870  Ukraine Pivdenne/​Pivdenmash Cyclone-4M Development 1st RP-1 / LOX Staged, oxidizer-rich 340 [51]
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 295.6[24] 184,000[24]
RL-10A-4-2[52]  USA Aerojet Rocketdyne Atlas IIIB, V Active Upper LH2 / LOX Expander, closed 451 99,195 42 168 60.27 5.5
RL-10B-2[52]  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[52]  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)[53] 		206.4 3,526 53.79
RS-68A[lower-alpha 4]  USA Rocketdyne Delta IV, IV Heavy Active 1st LH2 / LOX Gas generator 411[54]
362 (SL) 		3,558,577
3,135,996 (SL) 		109 6,686 54.31 5.97
Rutherford  New Zealand  USA Rocket Lab Electron Active 1st RP-1 / LOX Electric pump 311 24,900
25,000 (SL) 		35[55] 72.8 (SL)
Rutherford Vacuum  New Zealand  USA Rocket Lab Electron Active 2nd RP-1 / LOX Electric pump 343 25,800[55]
S200  India SDSC GSLV Mk III Active Booster HTPB Solid fuel 274.5[56] 5,150,000[57][58][59] 207,000
with fuel[56]
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[lower-alpha 5]  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[60] 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[61] 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[62]  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 Development Upper LH2 / LOX Expander, closed[63] 457[64] 180,000 60 280 65.60 6.1
Vulcain 2.1  Europe Snecma Ariane 6 Development 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)[65] 740,400 (SL)[65]
YF-21C  China AALPT Long March 2C, 2D, 3A, 3B, 3C, 4B, 4C Active 1st N2O4 / UDMH Gas generator 260.7 (SL)[65] 740,400 (SL)[65]
YF-25  China AALPT Long March 3B, 3C Active Booster N2O4 / UDMH Gas generator 260.66 (SL)[65] 740,400 (SL)[65]
YF-22B  China AALPT Long March 2E, 2F Active 2nd N2O4 / UDMH Gas generator 298.0[65] 738,400
YF-22C  China AALPT Long March 2C, 2D, 4B, 4C Active 2nd N2O4 / UDMH Gas generator 298.0[65] 742,040
YF-22D  China AALPT Long March 3 Active 2nd N2O4 / UDMH Gas generator 298.0[65] 741,400
YF-22E  China AALPT Long March 3A, 3B, 3C Active 2nd N2O4 / UDMH Gas generator 298.0[65] 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[65] 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[66]  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 Active 3rd HTPB Solid fuel 295.2[67] 314,000[67] 75 11,400 with fuel
Zefiro 23  European Union Avio Vega Active 2nd HTPB Solid fuel 287.5[68] 1,122,000[68] 94 25,935 with fuel
Zefiro 40  European Union Avio Vega-C Active 3rd HTPB Solid fuel 293.5[69] 1,304,000[69] 115 39,206 with fuel

Retired and canceled rocket engines

Engine Origin Designer Vehicle Use Propellant Power cycle Specific impulse (s)[lower-alpha 1] Thrust (N)[lower-alpha 1] Chamber pressure (bar) Mass (kg) Thrust:​weight ratio[lower-alpha 6] Oxidiser:​fuel ratio
Aeon 1  USA Relativity Space Terran 1 1st CH4 / LOX Gas generator 310 86,740 (SL)[70]
Aeon 1 Vacuum  USA Relativity Space Terran 1 2nd CH4 / LOX Gas generator 360 100,085 (SL)[70]
Aestus  Europe Airbus Defence and Space Ariane 5 G, G+, ES Upper N2O4 / MMH Pressure-fed 324[71] 30,000 11 111 27.6 1.9
Aestus II  Europe Airbus Defence and Space Ariane 5 Upper N2O4 / MMH Gas generator 340[72] 55,400 60 138 41.0 1.9
Aether  USA Astra Space Rocket 3.3 2nd RP-1/LOX[73] Pressure-fed 3,300[74]
AJ-60A  USA Aerojet Atlas V Booster HTPB Solid fuel 275 1,270,000[75]
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)[76] 2.72
Delphin  USA Astra Space Rocket 3.3 1st RP-1/LOX[73] Electric pump 29,000[74]
F-1[lower-alpha 7]  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[lower-alpha 8][77]  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[78] 68,200 173 40.22 8
Gamma 8  United Kingdom Bristol Siddeley Black Arrow 1st RP-1 / H2O2 Staged, decomposition and combustion 265[79] 234,800 47.40 342 70.01 8
HM-7A  Europe Snecma Ariane 1 3rd LH2 / LOX Gas generator 443[80]
308 (SL) 		61,700 30 149 42.2 5
J-2  USA Rocketdyne Saturn V, IB 2nd, 3rd LH2 / LOX Gas generator 421[81]
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[82] 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[83] 103,000 36.0 245 42.87 5.5
LE-5A  Japan Mitsubishi, NASDA H-II Upper LH2 / LOX Expander, open 452[84] 121,500 40.0 242 51.19 5
LE-7  Japan Mitsubishi, NASDA H-II 1st LH2 / LOX Staged combustion 446[85] 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[86]
282 (SL)[86] 		723,000 97 470 158 2.34
Merlin Vacuum 1C  USA SpaceX Falcon 1, 9 2nd RP-1 / LOX Gas generator 336[87] 413,644[87] 92
NewtonThree  USA Virgin Orbit LauncherOne Booster RP-1 / LOX Gas generator[88] 266,893[89]
NewtonFour  USA Virgin Orbit LauncherOne 2nd RP-1 / LOX Gas generator[88] 22,241[89]
P230  Europe Avio Ariane 5 Booster HTPB Solid fuel 286[90]
259 (SL) 		6,996,000
5,860,000 (SL) 		69 269,000 with fuel[90]
Polaris  United States Exela Space Industries Aims-1, Aims-4 1st Propane/LOX Pressure-fed 23 2,000 25 5 40.8 0.8-1
RD-0120
11Д122 		 Soviet Union KBKhA Energia 1st LH2 / LOX Staged, fuel-rich 455[91] 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[92] 69,626 55.9 282 25.17
RD-117
11Д511 		 Soviet Union NPO Energomash Soyuz-U 1st RP-1 / LOX Gas generator 316[93]
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[93]
257 (SL) 		1,000,278
818,855 (SL) 		59.7 1,100 75.91
RD-170[lower-alpha 9]11Д521[94]  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[95]
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[96]
293 (SL) 		4,521,000 206 3,600 128.15
RD-270[lower-alpha 10]
8Д420 		 Soviet Union NPO Energomash UR-700 (proposed), UR-900 (proposed) 1st N2O4 / UDMH Staged, full-flow 322[97]
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[98]
287 (SL) 		1,831,882
1,671,053 (SL) 		160.0 1,070 171.2
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[99]
255 (SL) 		1,054,200 49 1,091 102.5 2.245
Space Shuttle Solid Rocket Booster[lower-alpha 11]  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[100] 2,250,000 76,400 with fuel
UA1207  USA United Technologies Titan IV Booster PBAN Solid fuel 272[101]
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[102]
326 (SL)[103] 		1,113,000[102]
773,200 (SL)[103] 		109[102] 1,300[103] 84.38
Vulcain 2  Europe Snecma Ariane 5 1st LH2 / LOX Gas generator 429[104]
318 (SL)[105] 		1,359,000[104]
939,500 (SL)[105] 		117.3[104] 1,800[104] 77.04
Waxwing  United Kingdom Bristol Aerojet Black Arrow Upper Solid fuel 278[106]
245 (SL) 		29,400
25,900 (SL) 		87 34.48

See also

Notes

  1. ↑ 1.0 1.1 1.2 1.3 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. ↑ Most powerful hydrogen-fueled engine in the world
  5. ↑ Largest, most powerful solid-fuel rocket motor ever built
  6. ↑ Weight is calculated at standard gravity.
  7. ↑ Most powerful single-chamber liquid-fueled rocket engine ever developed
  8. ↑ Tested but never flown
  9. ↑ World's most powerful liquid fueled rocket engine
  10. ↑ Tested but never flown
  11. ↑ Largest solid-fuel rocket motor ever flown, and the first to be used for primary propulsion on human spaceflight missions

References

  1. ↑ 1.0 1.1 1.2 1.3 "In-Space Product Data Sheets". September 13, 2019. https://www.rocket.com/sites/default/files/documents/In-Space%20Data%20Sheets%209.13.19.pdf. 
  2. ↑ 2.0 2.1 "BE-3". https://www.blueorigin.com/engines/be-3. 
  3. ↑ Belam, Martin (2024-01-08). "Nasa Peregrine 1 launch: Vulcan Centaur rocket carrying Nasa moon lander lifts off in Florida – live updates" (in en-GB). the Guardian. ISSN 0261-3077. https://www.theguardian.com/science/live/2024/jan/08/nasa-peregrine-1-launch-rocket-moon-latest-news-updates-live. 
  4. ↑ "Blue Origin's BE-4 Engine". https://forum.nasaspaceflight.com/index.php?topic=39674.msg1504802#msg1504802. 
  5. ↑ Ferster, Warren (2014-09-17). "ULA To Invest in Blue Origin Engine as RD-180 Replacement". Space News. http://www.spacenews.com/article/launch-report/41901ula-to-invest-in-blue-origin-engine-as-rd-180-replacement. Retrieved 2014-09-19. 
  6. ↑ "BE-4". Blue Origin. http://www.blueorigin.com/media/press_release/united-launch-alliance-and-blue-origin-announce-partnership-to-develop-new. Retrieved 17 September 2014. 
  7. ↑ Berger, Eric (2016-03-09). "Behind the curtain: Ars goes inside Blue Origin's secretive rocket factory". Ars Technica. https://arstechnica.com/science/2016/03/behind-the-curtain-ars-goes-inside-blue-origins-secretive-rocket-factory/. Retrieved 2016-03-09. 
  8. ↑ "GSLV Launch Vehicle Information". http://www.spaceflight101.com/gslv-launch-vehicle-information.html. Retrieved 6 January 2014. 
  9. ↑ 9.0 9.1 "RS1" (in en-US). https://ablspacesystems.com/rs1/. 
  10. ↑ 10.0 10.1 10.2 10.3 "Engine-2" (in en-US). https://launcherspace.com/engine-2. 
  11. ↑ "NG Prop Catalog". 2020-12-10. https://www.northropgrumman.com/wp-content/uploads/NG-Propulsion-Products-Catalog.pdf#page=43. 
  12. ↑ 12.0 12.1 "Developing Vulcan Centaur". April 4, 2019. https://www.ulalaunch.com/docs/default-source/evolution/190408_ulapanel_all_compressed.pdf/. 
  13. ↑ "NG Prop Catalog". 2020-12-10. https://www.northropgrumman.com/wp-content/uploads/NG-Propulsion-Products-Catalog.pdf#page=44. 
  14. ↑ "The Engines" (in en-US). https://www.ursamajortechnologies.com/engines. 
  15. ↑ 15.0 15.1 Arizaga, Monica (2022-03-18). ""Helix" - public names RFA engine" (in en-US). https://www.rfa.space/helix-public-names-rfa-engine/. 
  16. ↑ Arizaga, Monica (2022-07-13). "RFA successfully hot fires Helix engine for a total of 74 seconds" (in en-US). https://www.rfa.space/rfa-successfully-hot-fires-helix-engine-for-a-total-of-74-seconds/. 
  17. ↑ 17.0 17.1 17.2 17.3 "HM-7 and HM-7B Rocket Engine - Thrust Chamber". Airbus Defence and Space. http://cs.astrium.eads.net/sp/launcher-propulsion/rocket-engines/hm7b-rocket-engine.html. 
  18. ↑ 18.0 18.1 Wade, Mark. "HM7-B". Encyclopedia Astronautica. http://www.astronautix.com/h/hm7-b.html. Retrieved 10 June 2017. 
  19. ↑ https://www.spaceintel101.com/post/south-korea-s-innospace-will-launch-brazilian-payload-on-inaugural-flight-from-alc%C3%A2ntara
  20. ↑ "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!"" (in en). https://twitter.com/innospacecorp/status/1410563047266033669. 
  21. ↑ "LE-5B". Encyclopedia Astronautica. http://www.astronautix.com/engines/le5b.htm. Retrieved 13 January 2016. 
  22. ↑ 22.0 22.1 "LE-7A". Encyclopedia Astronautica. http://www.astronautix.com/engines/le7a.htm. Retrieved 13 January 2016. 
  23. ↑ "LE-9". https://www.jaxa.jp/press/2016/06/files/20160614_h3_01_j.pdf. 
  24. ↑ 24.0 24.1 24.2 24.3 "Launch-alpha" (in en-US). https://firefly.com/launch-alpha/. 
  25. ↑ 25.0 25.1 25.2 "Merlin 1D". SpaceX. http://www.spacex.com/news/2013/03/26/merlin-engines. Retrieved 26 February 2016. 
  26. ↑ "Evolution of the SpaceX Merlin engine". http://www.b14643.de/Spacerockets_2/United_States_1/Falcon-9/Merlin/index.htm. 
  27. ↑ "SpaceX Falcon 9 Product Page". http://www.spacex.com/falcon9. Retrieved 2015-11-01. 
  28. ↑ "SpaceX" (in en). http://www.spacex.com/. 
  29. ↑ 29.0 29.1 29.2 29.3 29.4 29.5 "Motore M10" (in Italian). Avio. https://www.avio.com/it/m-10. 
  30. ↑ "NK-33". Encyclopedia Astronautica. http://www.astronautix.com/engines/nk33.htm. Retrieved 30 January 2014. 
  31. ↑ 31.0 31.1 "VEGA: 1° stage - P80 Motor" (in en-US). http://www.avio.com/en/vega/vega/vega-1-stadio-p80-motor/. 
  32. ↑ 32.0 32.1 32.2 Press release: Successful first test firing for the P120C solid rocket motor for Ariane 6 and Vega-C
  33. ↑ "PSLV-1". http://www.astronautix.com/engines/pslv1.htm. Retrieved 4 April 2014. 
  34. ↑ 34.0 34.1 "Spacex Raptor". NASA SpaceFlight. 7 March 2014. http://www.nasaspaceflight.com/2014/03/spacex-advances-drive-mars-rocket-raptor-power/. Retrieved 2 July 2015. 
  35. ↑ 35.0 35.1 "Sea level Raptor’s vacuum Isp is ~350 sec, but ~380 sec with larger vacuum-optimized nozzle" (in en-US). 2019-09-09. https://twitter.com/elonmusk/status/1171118891671490560. 
  36. ↑ 36.0 36.1 36.2 36.3 36.4 "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." (in en-US). 2023-05-13. https://twitter.com/elonmusk/status/1657249739925258240. 
  37. ↑ 37.0 37.1 37.2 Tim Dodd (14 July 2022). "Raptor 1 VS Raptor 2: What's New // What's Different". https://www.youtube.com/watch?v=ALiNmzoo1_E. 
  38. ↑ 38.0 38.1 "Draft Environmental Assessment for the SpaceX Starship and Super Heavy Launch Vehicle at Kennedy Space Center (KSC)" (in en). Space Exploration Technologies Corporation. 1 August 2019. p. 250. https://netspublic.grc.nasa.gov/main/20190801_Final_DRAFT_EA_SpaceX_Starship.pdf. Retrieved 5 August 2019. 
  39. ↑ Elon Musk on Twitter: 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.
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  41. ↑ "ГКНПЦ имени М.В.Хруничева | Жидкостный ракетный двигатель РД - 0146". http://www.khrunichev.ru/main.php?id=304. 
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  43. ↑ "RD-171M". NPO Energomash. http://www.npoenergomash.ru/eng/dejatelnost/engines/rd171m/. Retrieved 30 June 2015. 
  44. ↑ "RD-180". NPO Energomash. http://www.npoenergomash.ru/eng/dejatelnost/engines/rd180/. Retrieved 30 June 2015. 
  45. ↑ "RD-191". NPO Energomash. http://www.npoenergomash.ru/eng/dejatelnost/engines/rd191/. Retrieved 30 June 2015. 
  46. ↑ "Универсальный ракетный двигатель РД-193. Мнение инженера-разработчика". Журнал «Новости космонавтики». http://novosti-kosmonavtiki.ru/mag/2013/1004/13840/. 
  47. ↑ "RD-276 "Comrade"". NPO Energomash. http://www.engine.space/eng/dejatelnost/engines/rd-276/. Retrieved 14 October 2019. 
  48. ↑ 48.0 48.1 "RD-801". https://www.yuzhnoye.com/en/technique/rocket-engines/steering/rd-801/. 
  49. ↑ "RD-810". https://www.yuzhnoye.com/en/technique/rocket-engines/steering/rd-810/. 
  50. ↑ "RD-861K". https://www.yuzhnoye.com/en/technique/rocket-engines/marching/rd-861k/. 
  51. ↑ "RD-870". https://www.yuzhnoye.com/en/technique/rocket-engines/steering/rd-870/. 
  52. ↑ 52.0 52.1 52.2 "RL10 Data Sheet-1". Feb 2016. https://www.rocket.com/files/aerojet/documents/Capabilities/PDFs/RL10%20data%20sheet%20Feb%202016.pdf. 
  53. ↑ Aerojet Rocketdyne, RS-25 Engine (accessed July 22, 2014)
  54. ↑ "RS-68A". www.rocket.com. https://www.rocket.com/space/liquid-engines/rs-68a. Retrieved 19 January 2020. 
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  56. ↑ 56.0 56.1 "LVM3". http://isro.org/launchers/lvm3. Retrieved 21 December 2014. 
  57. ↑ "ISRO Press Release: S200 First Static Test (S-200-ST-01)". http://www.isro.org/pressrelease/contents/2010/pdf/S200_STATIC_TEST-01.pdf. 
  58. ↑ "Isro successfully tests world's 3rd largest solid booster". dna. http://www.dnaindia.com/scitech/report_isro-successfully-tests-world-s-3rd-largest-solid-booster_1338945. Retrieved 4 October 2014. 
  59. ↑ "India to test world's third largest solid rocket booster". Science and Technology Section. The Hindu News Paper. 2009-12-07. http://www.thehindu.com/sci-tech/article61220.ece. Retrieved 2009-12-07. 
  60. ↑ "SLV-1". http://www.astronautix.com/engines/slv1.htm. Retrieved 4 April 2014. 
  61. ↑ "SRB-A3". Spaceflight101. http://spaceflight101.com/spacerockets/epsilon/. Retrieved 13 January 2016. 
  62. ↑ “天鹊”80吨液氧甲烷发动机100%推力100秒试车圆满成功
  63. ↑ "Vinci". Encyclopedia Astronautica. http://www.astronautix.com/v/vinci.html. Retrieved 10 June 2017. 
  64. ↑ "Vinci® engine". Ariane. https://www.ariane.group/wp-content/uploads/2020/06/VINCI_2020_04_DS_EN_Eng_Web.pdf. 
  65. ↑ 65.00 65.01 65.02 65.03 65.04 65.05 65.06 65.07 65.08 65.09 65.10 "2.2 LM-3A Launch Vehicle". LM-3A Series Launch Vehicle User's Manual. Issue 2011. CASC. 2011. pp. 2–4. http://www.cgwic.com/launchservices/download/manual/Chapter%202%20General%20Description.pdf. Retrieved 2016-01-16. 
  66. ↑ 孙纪国,郑孟伟,龚杰峰,陶瑞峰 (2022-01-15). "220tf补燃循环氢氧发动机研制进展" (in zh-hans). 《火箭推进》2022年02期. http://hjtjnew.paperopen.com/upload/html/m/202202002.html. Retrieved 2022-06-05. 
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  69. ↑ 69.0 69.1 "Zefiro 40 Motor Main Characteristics" (in en-US). https://www.avio.com/zefiro-40/. 
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  71. ↑ "Aestus Rocket Engine". Airbus Defence and Space. http://cs.astrium.eads.net/sp/launcher-propulsion/rocket-engines/aestus-rocket-engine.html. Retrieved 29 January 2014. 
  72. ↑ "Aestus Rocket Engine". Airbus Defence and Space. http://cs.astrium.eads.net/sp/launcher-propulsion/rocket-engines/aestus-rs72-rocket-engine.html. Retrieved 29 January 2014. 
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  75. ↑ "Atlas V Solid Rocket Motor". http://www.rocket.com/atlas-v-solid-rocket-motor. Retrieved 2015-06-02. 
  76. ↑ "AR1 Engine". http://www.rocket.com/ar1-booster-engine. 
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  79. ↑ "Gamma 8". Encyclopedia Astronautica. http://www.astronautix.com/engines/gamma8.htm. Retrieved 26 April 2013. 
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  85. ↑ "LE-7". Encyclopedia Astronautica. http://www.astronautix.com/engines/le7.htm. Retrieved 13 January 2016. 
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