Comparison of orbital rocket engines

Short description: none

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

## Contents

* 1 Current, upcoming, and in-development rocket engines
* 2 Retired and cancelled rocket engines
* 3 See also
* 4 Notes
* 5 References

## 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

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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

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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

* Comparison of orbital launch systems
* Comparison of orbital launchers families
* Comparison of crewed space vehicles
* Comparison of space station cargo vehicles
* Comparison of solid-fuelled orbital launch systems
* List of space launch system designs
* List of orbital launch systems

## 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 Data Sheets 9.13.19.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-alcântara.
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 data sheet Feb 2016.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 2 General Description.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/.

* v
* t
* e

Rocket engines and solid motors for orbital launch vehicles

* Comparison of orbital rocket engines

Liquid fuel|

| Cryogenic (hydrolox)
(LH2 / LOX)|

* China
* YF-73
* YF-75
* YF-75D
* YF-77
* Europe
* HM7B
* Vinci
* Vulcain
* India
* CE-7.5
* CE-20
* Japan
* LE-5
* LE-7
* LE-9
* Russia
* KVD-1 (RD-56)
* RD-0120
* RD-0146
* USA
* BE-3U
* BE-7
* J-2
* RL10
* RS-25 (SSME)
* RS-68

|

Cryogenic (methalox)
(CH4 / LOX)|

* USA
* BE-4
* Raptor
* Europe
* Prometheus
* Italy (with Russia)
* Mira (LM-10)

Semi-cryogenic (kerolox)
(RP-1 / LOX)|

* China
* YF-100
* YF-115
* India
* SCE-200
* Russia
* NK-15
* NK-33 NK-44
* RD-58
* RD-0105, 0109
* RD-0107, 0108, 0110
* RD-0110R
* RD-0124
* RD-107, 108, 117, 118
* RD-120
* RD-170, 171
* RD-180
* RD-191, 151, 181
* RD-193
* S1.5400
* Ukraine
* RD-8
* RD-801
* RD-810
* USA
* F-1
* H-1
* Kestrel
* LR-79
* LR-89
* LR-105
* LR70-NA , S-3D
* Merlin 1
* RS-27
* RS-27A
* RS-56
* S-3D
* Rutherford
* XLR50

Storable (hypergolic)
(UDMH, UH 25,
Aerozine or MMH
reacting with NTO N2O4,
MON or HNO3)|

* China
* YF-1, 2, 3
* YF-20, 21, 22, 24, 25
* YF-23
* YF-40
* YF-50D
* Europe
* Aestus
* Astris
* Vexin
* Viking
* India
* PS4
* Vikas
* Israel
* LK-4
* North Korea
* Paektusan LRE along other LREs
* Russia
* 17D61
* RD-0202 to 0206, 0208 to 0213
* RD-0207, 0214
* RD-0216, 0217, 0235
* RD-0233, 0234
* RD-0236
* RD-0237
* RD-0243 to 0245
* RD-0255 to 0257
* RD-215, 216
* RD-250 to 252, 261, 262
* RD-253, 275
* RD-263, 268, 273
* RD-270
* RD-854, 861
* RD-855
* RD-856
* RD-864, 869
* S5.92
* S5.98M
* Ukraine
* RD-843
* USA
* AJ10
* LR-87
* LR-91
* TR-201

Other propellants|

* Europe
* Gamma
* Russia
* RD-109, 119
* RD-211 to 214
* USA
* XLR81
* Curie

Solid fuel|

* China
* FG-02
* FG-36
* FG-46
* FG-47
* SpaB-65
* SpaB-140C
* Europe
* Mage 1
* P-4
* P-6
* PAP
* P80
* P120
* P230
* Topaze
* Waxwing
* Zefiro 9
* Zefiro 23
* Zefiro 40
* India
* S7
* S9
* S12
* S139
* S200
* Israel
* LK-1
* RSA-3
* Japan
* KM-V1
* KM-V2b
* M-14
* M-24
* M-34
* M-34c
* SRB-A
* USA
* AJ-60A
* Algol
* Castor 30
* GEM
* Orbus-6
* Orbus-21
* Orion
* Space Shuttle SRB
* Star 37
* Star 48
* UA120
* SRMU
* X-248
* X-254

* Engines under development are in italics.

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