Astronomy:Comparison of orbital rocket engines

From HandWiki
Short description: none

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] Oxidizer:​fuel ratio
Aeon-R  USA Relativity Space Terran R Development 1st, 2nd CH4 / LOX Gas generator 1,147,000
AJ10-190  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
Aquila SL  Germany Isar Aerospace Spectrum Development 1st C3H8 / LOX Gas generator[2] 75,000
Aquila VAC  Germany Isar Aerospace Spectrum Development 2nd C3H8 / LOX Gas generator[2] 94,000
Archimedes  New Zealand  USA Rocket Lab Neutron Development 1st, 2nd CH4 / LOX Staged, oxidizer-rich 730,000
BE-3U  USA Blue Origin New Glenn Active 2nd LH2 / LOX Expander, open 445[3] 941,500[4] >90[4]
BE-4  USA Blue Origin New Glenn, Vulcan Active[5] 1st CH4 / LOX Staged, oxidizer-rich 340[3] 2,846,900[6] 138[3]
BE-7  USA Blue Origin Blue Moon Development 1st LH2 / LOX Expander, open 44,500[7] 5.5-7.1[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, fuel-rich 454[8] 73,500 58 445 16.85
E2  USA ABL Space Systems RS1 Active 1st RP-1 / LOX // Jet-A / LOX Gas generator 53,800[9] 64
E2 Vacuum  USA ABL Space Systems RS1 Active 2nd RP-1 / LOX // Jet-A / 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] 100 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[11] 1,662,745[12] 49,300 with fuel
GEM 63XL  USA Northrop Grumman Vulcan Active Booster HTPB Solid fuel 280.3[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] 62
Helix  Germany Rocket Factory Augsburg RFA One Development 1st, 2nd RP-1 / LOX Staged, oxidizer-rich 350,
325 (SL)[15] 		100,000[15] 100[16]
HyPER-15[17]  South Korea Innospace Hanbit-Nano, -Micro, -Mini Development 1st Paraffin / LOX Electric pump 292 150,000[18]
LE-5B-3  Japan Mitsubishi, JAXA H-3 Active Upper LH2 / LOX Expander, open 447[19] 137,000 36.0 269 51.93 5
LE-9  Japan Mitsubishi, JAXA H-3 Active 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]
M10  Europe Avio Vega-E[22] Development Upper[22] CH4 / LOX[22] Expander, closed 362[22] 98,000[22] 3.4[22]
Merlin 1D FT  USA SpaceX Falcon 9 B5, Heavy Active 1st RP-1 / LOX Gas generator 311 914,000[23]
845,000 (SL)[23] 		108.0[24] 470 194.5[23]
Merlin Vacuum 1D  USA SpaceX Falcon 9 B5, Heavy Active 2nd RP-1 / LOX Gas generator 348[25] 981,000[26] 2.36
Miranda  USA Firefly Aerospace Antares 300 Series,
MLV 		Development 1st RP-1 / LOX Combustion tap-off 305[27] 1,023,000[27]
NK-33A (AJ26-62),
11Д111 / 14Д15 		 Soviet Union JSC Kuznetsov Antares 100, Soyuz-2-1v Retired 1st RP-1 / LOX Staged, oxidizer-rich 331[28]
297 (SL) 		1,680,000
1,510,000 (SL) 		145 1,222 136.8
P120  Italy  France Avio Ariane 6,
Vega-C 		Active Booster, 1st HTPB Solid fuel 279[29] 4,650,000[29] 105 153,000 with fuel[29]
Raptor[30]  USA SpaceX Starship Development 1st, 2nd CH4 / LOX Staged, full-flow 350[31]
327 (SL)[32] 		2,750,000 (SL)[31] 350[33] 1,525[31] 184[31] 3.6[34]
Raptor Vacuum[30]  USA SpaceX Starship Development 2nd CH4 / LOX Staged, full-flow 380 est.[35] >2,750,000[31] 350[33] >1,525[31] <184[31] 3.6[34]
RD-0124,
14Д23 		 Russia KBKhA Soyuz-2.1b,
Soyuz-2-1v,
Angara 		Active 2nd, 3rd RP-1 / LOX Staged, oxidizer-rich 359[36] 294,300 160 520 57.7
RD-0146D  Russia KBKhA Angara Development Upper LH2 / LOX Expander, closed 470[37] 68,600 59
RD-107A,
14Д22 		 Russia NPO Energomash Soyuz-FG, -2 Active 1st RP-1 / LOX Gas generator 320.2[38]
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[38]
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[39]
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[40]
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[41]
311.2 (SL) 		2,084,894
1,922,103 (SL) 		262.6 2,200 89.09
RD-276,
14Д14М 		 Russia NPO Energomash Proton-M Active 1st N2O4 / UDMH Staged, oxidizer-rich 315.8[42]
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[43]
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[43] 98,067 330 2.62
RD-810  Ukraine Pivdenne/​Pivdenmash Mayak, Zenit Development 1st RP-1 / LOX Staged, oxidizer-rich 335.5[44]
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[45] 77,629 207 2.41
RD-870  Ukraine Pivdenne/​Pivdenmash Cyclone-4M Development 1st RP-1 / LOX Staged, oxidizer-rich 340[46]
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]

184,000[21] 75
RL10A-4-2[47]  USA Aerojet Rocketdyne Atlas IIIB, V Retired Upper LH2 / LOX Expander, closed 451 99,195 42 168 60.27 5.5
RL10B-2[47]  USA Aerojet Rocketdyne Delta III, IV, SLS Active Upper LH2 / LOX Expander, closed 465.5 110,093 44 301 37.27 5.88
RL10C-1[47]  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)[48] 		206.4 3,526 53.79
RS-88 LAE  USA Rocketdyne Boeing Starliner Active Upper MMH / NTO Gas generator 176,600 (SL)
Rutherford  New Zealand  USA Rocket Lab Electron Active 1st RP-1 / LOX Electric pump 311 24,900
25,000 (SL) 		55 35[49] 72.8 (SL)
Rutherford Vacuum  New Zealand  USA Rocket Lab Electron Active 2nd RP-1 / LOX Electric pump 343 25,800[49]
S139  India SDSC PSLV Active 1st HTPB Solid fuel 269[50] 4,860,000 58 160,200
with fuel
S200  India SDSC GSLV Mk III Active Booster HTPB Solid fuel 274.5[51] 5,150,000[52][53][54] 207,000
with fuel[51]
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
Sirius  Australia Gilmour Space Eris Development Booster Hybrid 150,000
SLS Solid Rocket Booster[lower-alpha 4]  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[55] 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[56] 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[57]  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[58] 457[59] 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)[60] 740,400 (SL)[60]
YF-21C  China AALPT Long March 2C, 2D, 3A, 3B, 3C, 4B, 4C Active 1st N2O4 / UDMH Gas generator 260.7 (SL)[60] 740,400 (SL)[60]
YF-22B  China AALPT Long March 2E, 2F Active 2nd N2O4 / UDMH Gas generator 298.0[60] 738,400
YF-22C  China AALPT Long March 2C, 2D, 4B, 4C Active 2nd N2O4 / UDMH Gas generator 298.0[60] 742,040
YF-22D  China AALPT Long March 3 Active 2nd N2O4 / UDMH Gas generator 298.0[60] 741,400
YF-22E  China AALPT Long March 3A, 3B, 3C Active 2nd N2O4 / UDMH Gas generator 298.0[60] 741,400
YF-25  China AALPT Long March 3B, 3C Active Booster N2O4 / UDMH Gas generator 260.66 (SL)[60] 740,400 (SL)[60]
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[60] 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[61]  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  Italy Avio Vega-C Active 3rd HTPB Solid fuel 295.2[62] 314,000[62] 75 11,400 with fuel
Zefiro 40  Italy Avio Vega-C Active 3rd HTPB Solid fuel 293.5[63] 1,304,000[63] 115 39,206 with fuel
Zenith  USA Stoke Nova Development 1st CH4 / LOX Staged, full-flow ~345 [64] >444,822[64]

Retired and cancelled 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] Oxidizer:​fuel ratio
Aeon 1  USA Relativity Space Terran 1 Retired 1st CH4 / LOX Gas generator 310 86,740 (SL)[65]
Aeon 1 Vacuum  USA Relativity Space Terran 1 Retired 2nd CH4 / LOX Gas generator 360 100,085 (SL)[65]
Aestus  Germany Airbus Defence and Space Ariane 5 G, G+, ES Retired Upper N2O4 / MMH Pressure-fed 324[66] 30,000 11 111 27.6 1.9
Aestus II / RS-72  Germany  USA Airbus Defence and Space, Rocketdyne Ariane 5 Retired Upper N2O4 / MMH Gas generator 340[67] 55,400 60 138 41.0 1.9
Aether  USA Astra Space Rocket 3.3 Retired 2nd RP-1 / LOX[68] Pressure-fed 3,300[69]
AJ-60A  USA Aerojet Atlas V Retired Booster HTPB Solid fuel 275 1,270,000[70]
AJ-260-2  USA Aerojet S-I stage replacement (proposed) Tested, cancelled 1st PBAN Solid fuel 263 26,183,755 831,345 with fuel
AR1  USA Aerojet Rocketdyne Cancelled 1st RP-1 / LOX Staged, oxidizer-rich 2,200,000 (SL)[71] 2.72
Common Rocket Propulsion Unit  Germany OTRAG OTRAG Tested, cancelled 1st and upper N2O4 / Aerozine 50 297 29,960 150
1,500 with fuel
Delphin  USA Astra Space Rocket 3.3 Retired 1st RP-1 / LOX[68] Electric pump 29,000[69] 31
F-1[lower-alpha 5]  USA Rocketdyne Saturn V Retired 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 6][72]  USA Rocketdyne Saturn MLV Cancelled 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 Retired 2nd RP-1 / H2O2 Gas generator 265[73] 68,200 173 40.22 8
Gamma 8  United Kingdom Bristol Siddeley Black Arrow Retired 1st RP-1 / H2O2 Gas generator 265[74] 234,800 47.40 342 70.01 8
HM7A  France Snecma Ariane 1 Retired 3rd LH2 / LOX Gas generator 443[75]
308 (SL) 		61,700 30 149 42.2 5
HM7B  France Snecma Ariane 2, 3, 4, 5 ECA Retired 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 Retired 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 Ares I, Ares V, SLS (proposed) Tested, cancelled Upper LH2 / LOX Gas generator 448[79] 1,310,000 95 2,470 58.41 5.5–4.5
Kestrel  USA SpaceX Falcon 1 Retired Upper RP-1 / LOX Pressure-fed 317 31,000 9.3 52 65
Kiwi B  USA LANL Tested, retired Upper Liquid Hydrogen 834 245,000 34
LE-5  Japan Mitsubishi, NASDA H-I Retired Upper LH2 / LOX Gas generator 450[80] 103,000 36.0 245 42.87 5.5
LE-5A  Japan Mitsubishi, NASDA H-II Retired Upper LH2 / LOX Expander, open 452[81] 121,500 40.0 242 51.19 5
LE-5B  Japan Mitsubishi, JAXA H-IIA,
H-IIB 		Active Upper LH2 / LOX Expander, open 447[19] 137,000 36.0 269 51.93 5
LE-7  Japan Mitsubishi, NASDA H-II Retired 1st LH2 / LOX Staged, fuel-rich 446[82] 1,078,000
843,500 (SL) 		127 1,714 64.13 5.9
LE-7A  Japan Mitsubishi, JAXA H-IIA,
H-IIB 		Active 1st LH2 / LOX Staged, fuel-rich 438[83]
338 (SL)[83] 		1,098,000
870,000 (SL) 		120 1,800 65.9 5.9
M-1[lower-alpha 7]  USA Aerojet Cancelled 1st, 2nd? LH2 / LOX Gas generator 428 (SL) 6,670,000 9,068 60
Merlin 1C  USA SpaceX Falcon 9 v1.0 Retired 1st RP-1 / LOX Gas generator 311[84]
282 (SL)[84] 		723,000 97 470 158 2.34
Merlin Vacuum 1C  USA SpaceX Falcon 9 v1.0 Retired 2nd RP-1 / LOX Gas generator 336[85] 413,644[85] 92
NERVA  USA LANL Tested, retired Upper Liquid Hydrogen 841
710 (SL) 		246,663 18,144
NewtonThree  USA Virgin Orbit LauncherOne Retired Booster RP-1 / LOX Gas generator[86] 266,893[87] 70
NewtonFour  USA Virgin Orbit LauncherOne Retired 2nd RP-1 / LOX Gas generator[86] 22,241[87]
P80  Italy  France Avio Vega Retired 1st HTPB Solid fuel 280[88] 3,015,000[88] 88 96,000 with fuel
P230  Europe Avio Ariane 5 Retired Booster HTPB Solid fuel 286[89]
259 (SL) 		6,996,000
5,860,000 (SL) 		69 269,000 with fuel[89]
RD-0120
11Д122 		 Soviet Union KBKhA Energia Retired 1st LH2 / LOX Staged, fuel-rich 455[90] 1,962,000
1,526,000 (SL) 		219 3,450 57.80
RD-0410
11Б91 		 Soviet Union KBKhA Cancelled Upper Liquid Hydrogen 910 35,200 2,000
RD-8,
11D513 		 Soviet Union Pivdenne/​Pivdenmash Zenit Retired 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 Retired Upper LH2 / LOX Staged, fuel-rich 462[91] 69,626 55.9 282 25.17
RD-117
11Д511 		 Soviet Union NPO Energomash Soyuz-U Retired 1st RP-1 / LOX Gas generator 316[92]
253 (SL) 		978,000
778,648 (SL) 		54.2 1,100 72.18
RD-118
11Д512 		 Soviet Union NPO Energomash Soyuz-U Retired 2nd RP-1 / LOX Gas generator 314[92]
257 (SL) 		1,000,278
818,855 (SL) 		59.7 1,100 75.91
RD-170[lower-alpha 8]11Д521[93]  Soviet Union NPO Energomash Energia Retired 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 Retired 1st RP-1 / LOX Staged, oxidizer-rich 339.2[94]
311.9 (SL) 		2,085,000
1,922,000 (SL) 		262.6 2,200 89
RD-193  Russia NPO Energomash Soyuz-2-1v Cancelled 1st RP-1 / LOX Staged, oxidizer-rich 337.5[95]
311.2 (SL) 		2,084,894
1,922,103 (SL) 		1,900 103.15
RD-264
11Д119 		 Soviet Union NPO Energomash Dnepr Retired 1st N2O4 / UDMH Staged, oxidizer-rich 318[96]
293 (SL) 		4,521,000 206 3,600 128.15
RD-270[lower-alpha 6]
8Д420 		 Soviet Union NPO Energomash UR-700 (proposed), UR-900 (proposed) Tested, cancelled 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 Retired 1st N2O4 / UDMH Staged, oxidizer-rich 316[98]
287 (SL) 		1,831,882
1,671,053 (SL) 		160.0 1,070 171.2
RD-843  Ukraine Pivdenne/​Pivdenmash Vega Retired Upper N2O4 / UDMH Pressure-fed 315.5 2,452 20.4 15.93 2.0
RD-854
8D612 		 Soviet Union Pivdenne/​Pivdenmash R-36ORB Retired 3rd N2O4 / UDMH Gas generator 317 78,710 88.8 123
RD-855
8D68M 		 Soviet Union Pivdenne/​Pivdenmash Tsyklon-2, -3, R-36 Retired 1st vernier N2O4 / UDMH Gas generator 292
254 (SL) 		328,000
285,400 (SL) 		65.70 320 1.97
RD-856
8D69M 		 Soviet Union Pivdenne/​Pivdenmash Tsyklon-2, -3 (-4), R-36 Retired 2nd vernier N2O4 / UDMH Gas generator 280.5 54,230 71.60 112.5 1.98
RD-861
11D25 		 Soviet Union Pivdenne/​Pivdenmash Tsyklon-2, -3 Retired 3rd N2O4 / UDMH Gas generator 317 78,710 88.8 123 2.1
RD-864
15D177 		 Soviet Union Pivdenne/​Pivdenmash R-36 (missile), Dnipro Retired 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 Retired 3rd N2O4 / UDMH Gas generator 302.3–313 8,580–20,470 17–41 196 1.8
RS-2200  USA Rocketdyne VentureStar Tested, cancelled 1st LH2 / LOX Gas generator 455
347 (SL) 		2,201,000
1,917,000 (SL) 		155 83
RS-27A  USA Rocketdyne Delta Retired 1st RP-1 / LOX Gas generator 302[99]
255 (SL) 		1,054,200 49 1,091 102.5 2.245
RS-68A[lower-alpha 9]  USA Rocketdyne Delta IV, IV Heavy Retired 1st LH2 / LOX Gas generator 411[100]
362 (SL) 		3,558,577
3,135,996 (SL) 		109 6,686 54.31 5.97
RS-83  USA Rocketdyne Cancelled 1st LH2 / LOX Gas generator 446 3,300,000 6,686
RS-84  USA Rocketdyne Cancelled 1st RP-1 / LOX Staged, oxidizer rich[101] 324
305 (SL) 		5,036,000
4,732,000 (SL) 		177 6,783
Space Shuttle Solid Rocket Booster[lower-alpha 10]  USA Thiokol Space Shuttle, Ares I Retired Booster PBAN / APCP Solid fuel 268 14,000,000
12,500,000 (SL) 		590,000
with fuel
Sea Dragon first stage engine  USA Aerojet Sea Dragon Cancelled 1st RP-1 / LOX 242 355,800,000
Sea Dragon second stage engine  USA Aerojet Sea Dragon Cancelled 2nd LH2 / LOX 409 62,800,000
Sea Dragon vernier engine  USA Aerojet Sea Dragon Cancelled 2nd vernier LH2 / LOX 236,600
SRB-A  Japan IHI Aerospace, JAXA H-IIA Retired Booster HTPB Solid fuel 280[102] 2,250,000 76,400 with fuel
TR-106  USA TRW Tested, cancelled 1st LH2 / LOX 2,892,000 (SL)
TR-107  USA Northrop Grumman Cancelled 1st RP-1 / LOX 4,900,000 (SL) 177
TR-201  USA TRW Delta-P Retired 2nd N2O4 / Aerozine 50 Presssure-fed 301 41,900 6.9 113 31.4
UA1207  USA United Technologies Titan IV Retired Booster PBAN Solid fuel 272[103]
245 (SL) 		7,116,000
6,410,400 (SL) 		319,330
with fuel
Viking 2  France Snecma Ariane 1 Retired 1st N2O4 / UDMH Gas generator 690,000
611,200 (SL) 		776 90.67
Viking 2B  France Snecma Ariane 2, 3 Retired 1st N2O4 / UH 25 Gas generator 643,000 (SL) 776 84.5
Viking 4  France Snecma Ariane 1 Retired 2nd N2O4 / UDMH Gas generator 713,000 826 88
Viking 4B  France Snecma Ariane 2, 3, 4 Retired 2nd N2O4 / UH 25 Gas generator 800,000 826 98.76
Viking 5C  France Snecma Ariane 4 Retired 1st N2O4 / UH 25 Gas generator 758,000
678,000 (SL) 		826 93.57
Viking 6  France Snecma Ariane 4 Retired Booster N2O4 / UH 25 Gas generator 750,000 826 92.59
Vulcain
HM-60 		 Europe Snecma Ariane 5 Retired 1st LH2 / LOX Gas generator 439[104]
326 (SL)[105] 		1,113,000[104]
773,200 (SL)[105] 		109[104] 1,300[105] 84.38
Vulcain 2  Europe Snecma Ariane 5 Retired 1st LH2 / LOX Gas generator 429[106]
318 (SL)[107] 		1,359,000[106]
939,500 (SL)[107] 		117.3[106] 1,800[106] 77.04
VTR-10  USA TRW Apollo LM Retired Upper N2O4 / Aerozine 50 Presssure-fed 311 47,000 7.68 179
Waxwing  United Kingdom Bristol Aerojet Black Arrow Retired Upper Solid fuel 278[108]
245 (SL) 		29,400
25,900 (SL) 		87 34.48
XRS-2200  USA Rocketdyne X-33 Tested, cancelled 1st LH2 / LOX Gas generator 439
339 (SL) 		1,184,000
909,000 (SL) 		58
Zefiro 23  Italy Avio Vega Retired 2nd HTPB Solid fuel 287.5[109] 1,122,000[109] 94 25,935 with fuel

See also

Notes

  1. ↑ 1.0 1.1 1.2 1.3 At sea level if denoted SL, in vacuum otherwise
  2. ↑ 2.0 2.1 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. ↑ Most powerful single-chamber liquid-fueled rocket engine ever developed
  6. ↑ 6.0 6.1 Tested but never flown
  7. ↑ Most powerful Hydrogen-fueled engine ever conceived
  8. ↑ World's most powerful liquid fueled rocket engine
  9. ↑ Most powerful hydrogen-fueled engine ever flown
  10. ↑ 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 Parsonson, Andrew (2022-09-22). "Everything you need to know about Isar Aerospace" (in en-US). https://europeanspaceflight.com/everything-you-need-to-know-about-isar-aerospace/. 
  3. ↑ 3.0 3.1 3.2 "First Look Inside Blue Origin's New Glenn Factory w/ Jeff Bezos!". August 15, 2024. https://www.youtube.com/watch?v=rsuqSn7ifpU. 
  4. ↑ 4.0 4.1 Limp, Dave (November 17, 2025). "Dave Limp on X". https://x.com/davill/status/1990512346029306032. 
  5. ↑ 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. 
  6. ↑ Limp, Dave (November 21, 2025). "Dave Limp on X". https://x.com/davill/status/1991538235609326013. <
  7. ↑ 7.0 7.1 Limp, Dave (December 16, 2025). "Dave Limp on X". https://x.com/davill/status/2000665478411510196. 
  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. ↑ "South Korea's INNOSPACE will launch Brazilian payload on inaugural flight from Alcântara". May 7, 2022. https://www.spaceintel101.com/post/south-korea-s-innospace-will-launch-brazilian-payload-on-inaugural-flight-from-alc%C3%A2ntara. 
  18. ↑ "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. 
  19. ↑ 19.0 19.1 "LE-5B". Encyclopedia Astronautica. http://www.astronautix.com/engines/le5b.htm. Retrieved 13 January 2016. 
  20. ↑ "Request Rejected". https://www.jaxa.jp/press/2016/06/files/20160614_h3_01_j.pdf. 
  21. ↑ 21.0 21.1 21.2 21.3 "Launch-alpha" (in en-US). https://firefly.com/launch-alpha/. 
  22. ↑ 22.0 22.1 22.2 22.3 22.4 22.5 "M10 Engine". Avio. https://www.avio.com/m-10. 
  23. ↑ 23.0 23.1 23.2 "Merlin 1D". SpaceX. http://www.spacex.com/news/2013/03/26/merlin-engines. Retrieved 26 February 2016. 
  24. ↑ "Evolution of the SpaceX Merlin engine". https://b14643.eu/Spacerockets_2/United_States_1/Falcon-9/Merlin/index.htm. 
  25. ↑ "SpaceX Falcon 9 Product Page". http://www.spacex.com/falcon9. Retrieved 2015-11-01. 
  26. ↑ "SpaceX" (in en). http://www.spacex.com/. 
  27. ↑ 27.0 27.1 "MLV". https://fireflyspace.com/mlv/. Retrieved 16 August 2024. 
  28. ↑ "NK-33". Encyclopedia Astronautica. http://www.astronautix.com/engines/nk33.htm. Retrieved 30 January 2014. 
  29. ↑ 29.0 29.1 29.2 "Press release: Successful first test firing for the P120C solid rocket motor for Ariane 6 and Vega-C". https://www.ariane.group/wp-content/uploads/2018/07/P120C-successful-testfire.pdf. 
  30. ↑ 30.0 30.1 "Spacex Raptor". NASA SpaceFlight. 7 March 2014. http://www.nasaspaceflight.com/2014/03/spacex-advances-drive-mars-rocket-raptor-power/. Retrieved 2 July 2015. 
  31. ↑ 31.0 31.1 31.2 31.3 31.4 31.5 31.6 "Raptor 3 (sea level variant) Thrust: 280tf Specific impulse: 350s Engine mass: 1525kg Engine + vehicle-side commodities and hardware mass : 1720kg" (in en-US). 2024-08-03. https://x.com/SpaceX/status/1819772716339339664. 
  32. ↑ "Raptor 1 vs Raptor 2: What did SpaceX change?". 2022-07-14. https://everydayastronaut.com/spacex-raptor-engine-comparison/. 
  33. ↑ 33.0 33.1 "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. 
  34. ↑ 34.0 34.1 "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. 
  35. ↑ "In a few years, we will finally have a Raptor 3/4 vacuum version (giant nozzle) that has an Isp of 380" (in en-US). 2024-08-03. https://x.com/elonmusk/status/1819781279828636041. 
  36. ↑ "RD-0124 Engine". KBKha. http://www.kbkha.ru/?p=8&cat=8&prod=51. Retrieved 7 January 2016. 
  37. ↑ "ГКНПЦ имени М.В.Хруничева | Жидкостный ракетный двигатель РД - 0146". http://www.khrunichev.ru/main.php?id=304. 
  38. ↑ 38.0 38.1 "RD-107A and RD-108A". NPO Energomash. http://www.npoenergomash.ru/eng/dejatelnost/engines/rd107/. Retrieved 30 June 2015. 
  39. ↑ "RD-171M". NPO Energomash. http://www.npoenergomash.ru/eng/dejatelnost/engines/rd171m/. Retrieved 30 June 2015. 
  40. ↑ "RD-180". NPO Energomash. http://www.npoenergomash.ru/eng/dejatelnost/engines/rd180/. Retrieved 30 June 2015. 
  41. ↑ "RD-191". NPO Energomash. http://www.npoenergomash.ru/eng/dejatelnost/engines/rd191/. Retrieved 30 June 2015. 
  42. ↑ "RD-276 "Comrade"". NPO Energomash. http://www.engine.space/eng/dejatelnost/engines/rd-276/. Retrieved 14 October 2019. 
  43. ↑ 43.0 43.1 "RD-801". https://www.yuzhnoye.com/en/technique/rocket-engines/steering/rd-801/. 
  44. ↑ "RD-810". https://www.yuzhnoye.com/en/technique/rocket-engines/steering/rd-810/. 
  45. ↑ "RD-861K". https://www.yuzhnoye.com/en/technique/rocket-engines/marching/rd-861k/. 
  46. ↑ "RD-870". https://www.yuzhnoye.com/en/technique/rocket-engines/steering/rd-870/. 
  47. ↑ 47.0 47.1 47.2 "RL10 Data Sheet-1". Feb 2016. https://www.rocket.com/files/aerojet/documents/Capabilities/PDFs/RL10%20data%20sheet%20Feb%202016.pdf. 
  48. ↑ Aerojet Rocketdyne, RS-25 Engine (accessed July 22, 2014)
  49. ↑ 49.0 49.1 "Rocket Lab Increases Electron Payload Capacity, Enabling Interplanetary Missions and Reusability" (in en). https://www.rocketlabusa.com/about-us/updates/rocket-lab-increases-electron-payload-capacity-enabling-interplanetary-missions-and-reusability/. Retrieved 26 October 2020. 
  50. ↑ "PSLV-1". http://www.astronautix.com/engines/pslv1.htm. Retrieved 4 April 2014. 
  51. ↑ 51.0 51.1 "LVM3". http://isro.org/launchers/lvm3. Retrieved 21 December 2014. 
  52. ↑ "ISRO Press Release: S200 First Static Test (S-200-ST-01)". http://www.isro.org/pressrelease/contents/2010/pdf/S200_STATIC_TEST-01.pdf. 
  53. ↑ "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. 
  54. ↑ "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. 
  55. ↑ "SLV-1". http://www.astronautix.com/engines/slv1.htm. Retrieved 4 April 2014. 
  56. ↑ "SRB-A3". Spaceflight101. http://spaceflight101.com/spacerockets/epsilon/. Retrieved 13 January 2016. 
  57. ↑ ""天鹊"80吨液氧甲烷发动机100%推力100秒试车圆满成功". https://mp.weixin.qq.com/s/mNVv0Pe67Ls-_53Gy2seIg. 
  58. ↑ "Vinci". Encyclopedia Astronautica. http://www.astronautix.com/v/vinci.html. Retrieved 10 June 2017. 
  59. ↑ "Vinci engine". Ariane. https://www.ariane.group/wp-content/uploads/2020/06/VINCI_2020_04_DS_EN_Eng_Web.pdf. 
  60. ↑ 60.00 60.01 60.02 60.03 60.04 60.05 60.06 60.07 60.08 60.09 60.10 "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. 
  61. ↑ "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. 2022-01-15. http://hjtjnew.paperopen.com/upload/html/m/202202002.html. Retrieved 2022-06-05. 
  62. ↑ 62.0 62.1 "VEGA C: 3° stage - zefiro 9" (in en-US). http://www.avio.com/en/vega/vega-c/vega-c-3-stadio-zefiro-9/. 
  63. ↑ 63.0 63.1 "Zefiro 40 Motor Main Characteristics" (in en-US). https://www.avio.com/zefiro-40/. 
  64. ↑ 64.0 64.1 "Nova" (in en-US). https://www.stokespace.com/nova/. 
  65. ↑ 65.0 65.1 "Terran 1 Technical Specifications". http://www.relativityspace.com/terran. 
  66. ↑ "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. 
  67. ↑ "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. 
  68. ↑ 68.0 68.1 "Astra Space Rocket". https://www.spacelaunchreport.com/astra.html. 
  69. ↑ 69.0 69.1 "Astra Media Kit LV0006". 28 August 2021. https://astra.com/wp-content/uploads/2021/08/Astra_MediaKit_LV0006.pdf. 
  70. ↑ "Atlas V Solid Rocket Motor". http://www.rocket.com/atlas-v-solid-rocket-motor. Retrieved 2015-06-02. 
  71. ↑ "AR1 Engine". http://www.rocket.com/ar1-booster-engine. 
  72. ↑ Levack, Daniel (April 1, 1993). Advanced transportation system studies. Alternate propulsion subsystem concepts: Propulsion database (Report). https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19930019136.pdf. 
  73. ↑ "Gamma 2". Encyclopedia Astronautica. http://www.astronautix.com/engines/gamma2.htm. Retrieved 26 April 2013. 
  74. ↑ "Gamma 8". Encyclopedia Astronautica. http://www.astronautix.com/engines/gamma8.htm. Retrieved 26 April 2013. 
  75. ↑ Wade, Mark. "HM7-A". Encyclopedia Astronautica. http://www.astronautix.com/h/hm7-a.html. Retrieved 10 June 2017. 
  76. ↑ 76.0 76.1 76.2 76.3 "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. 
  77. ↑ 77.0 77.1 Wade, Mark. "HM7-B". Encyclopedia Astronautica. http://www.astronautix.com/h/hm7-b.html. Retrieved 10 June 2017. 
  78. ↑ Wade, Mark. "J-2". Encyclopedia Astronautica. http://www.astronautix.com/j/j-2.html. Retrieved 23 December 2011. 
  79. ↑ "J-2X Engine". Pratt & Whitney Rocketdyne. http://www.pw.utc.com/products/pwr/propulsion_solutions/j-2x.asp. Retrieved 23 December 2011. 
  80. ↑ "LE-5". Encyclopedia Astronautica. http://www.astronautix.com/engines/le5.htm. Retrieved 13 January 2016. 
  81. ↑ "LE-5A". Encyclopedia Astronautica. http://www.astronautix.com/engines/le5a.htm. Retrieved 13 January 2016. 
  82. ↑ "LE-7". Encyclopedia Astronautica. http://www.astronautix.com/engines/le7.htm. Retrieved 13 January 2016. 
  83. ↑ 83.0 83.1 "LE-7A". Encyclopedia Astronautica. http://www.astronautix.com/engines/le7a.htm. Retrieved 13 January 2016. 
  84. ↑ 84.0 84.1 "Merlin section of Falcon 9 page". SpaceX. http://www.spacex.com/falcon9.php#merlin_engine. Retrieved 2012-10-16. 
  85. ↑ 85.0 85.1 "Falcon 9 Space Launch Report". SpaceLaunchReport. http://www.spacelaunchreport.com/falcon9.html. Retrieved 2015-11-01. 
  86. ↑ 86.0 86.1 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. https://arc.aiaa.org/doi/pdfplus/10.2514/6.2016-4984. 
  87. ↑ 87.0 87.1 "LauncherOne Service Guide". http://www.virgingalactic.com/assets/uploads/2014/11/VG_LauncherOne_ServiceGuide_v0.2_OSR.pdf. 
  88. ↑ 88.0 88.1 "VEGA: 1° stage - P80 Motor" (in en-US). http://www.avio.com/en/vega/vega/vega-1-stadio-p80-motor/. 
  89. ↑ 89.0 89.1 "P230". Encyclopedia Astronautica. http://www.astronautix.com/engines/p230.htm. Retrieved 27 December 2011. 
  90. ↑ "RD0120". KBKhA. http://www.kbkha.ru/?p=8&cat=8&prod=34. 
  91. ↑ "KVD1 Rocket Engine" (in ru). КБХМ им. A.M. Исаева. http://kbhmisaeva.ru/main.php?id=54. 
  92. ↑ 92.0 92.1 "RD-117". Liquid Propellant Rocket Engines. http://www.lpre.de/energomash/RD-107/index.htm. Retrieved 27 November 2012. 
  93. ↑ "RD-170". Encyclopedia Astronautica. http://www.astronautix.com/r/rd-170.html. Retrieved 24 September 2019. 
  94. ↑ "Antares 200 Series – Rockets". http://spaceflight101.com/spacerockets/antares-200-series/. 
  95. ↑ "Универсальный ракетный двигатель РД-193. Мнение инженера-разработчика". Журнал «Новости космонавтики». http://novosti-kosmonavtiki.ru/mag/2013/1004/13840/. 
  96. ↑ Wade, Mark. "RD-264". Encyclopedia Astronautica. http://www.astronautix.com/r/rd-264.html. Retrieved 10 June 2017. 
  97. ↑ "RD-270 (8D420)". NPO Energomash. http://www.lpre.de/energomash/RD-270/index.htm. Retrieved 6 February 2023. 
  98. ↑ "RD-253 and RD-275". NPO Energomash. http://www.npoenergomash.ru/eng/dejatelnost/engines/rd253/. Retrieved 30 June 2015. 
  99. ↑ "RS-27A". Encyclopedia Astronautica. http://www.astronautix.com/r/rs-27a.html. Retrieved 2 November 2021. 
  100. ↑ "RS-68A". www.rocket.com. https://www.rocket.com/space/liquid-engines/rs-68a. Retrieved 19 January 2020. 
  101. ↑ "RS-84". Encyclopedia Astronautica. http://www.astronautix.com/r/rs-84.html. Retrieved February 4, 2026. 
  102. ↑ "SRB-A". Encyclopedia Astronautica. http://www.astronautix.com/engines/srba.htm. Retrieved 13 January 2016. 
  103. ↑ "UA1207". Encyclopedia Astronautica. http://www.astronautix.com/engines/ua1207.htm. Retrieved 27 December 2015. 
  104. ↑ 104.0 104.1 104.2 "Vulcain Astrium". Airbus Defence and Space. http://cs.astrium.eads.net/sp/launcher-propulsion/rocket-engines/vulcain-rocket-engine.html. Retrieved 27 December 2011. 
  105. ↑ 105.0 105.1 105.2 "Vulcain". Encyclopedia Astronautica. http://www.astronautix.com/v/vulcain.html. Retrieved 27 December 2011. 
  106. ↑ 106.0 106.1 106.2 106.3 "Vulcain Astrium". Airbus Defence and Space. http://cs.astrium.eads.net/sp/launcher-propulsion/rocket-engines/vulcain-2-rocket-engine.html. Retrieved 27 December 2011. 
  107. ↑ 107.0 107.1 "Vulcain 2". Encyclopedia Astronautica. http://www.astronautix.com/v/vulcain2.html. Retrieved 27 December 2011. 
  108. ↑ "Black Arrow-3". Encyclopedia Astronautica. http://www.astronautix.com/b/blackarrow-3.html. Retrieved 26 April 2013. 
  109. ↑ 109.0 109.1 "VEGA: 2° stage - zefiro 23" (in en-US). http://www.avio.com/en/vega/vega/vega-2-stadio-zefiro-23/. 



Retrieved from "https://handwiki.org/wiki/index.php?title=Astronomy:Comparison_of_orbital_rocket_engines&oldid=4341536"