Comparison of orbital rocket engines

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

## Current, upcoming, and in-development rocket engines

[edit]

Engine  | Origin  | Designer  | Vehicle | Status  | Use | Propellant | Power cycle  | Specific impulse (s)[a] | Thrust (N)[a] | Chamber pressure (bar)  | Mass (kg)  | Thrust:​weight ratio[b] | Oxidizer:​fuel ratio

|
|
|
|
|
|
|
|
|
|
|
|
|

Aeon-R |  USA | Relativity Space | Terran R | Development  | 1st, 2nd  | CH4 / LOX | Gas generator |  | 1,147,000 |  |  |  |
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 |
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] | 765,000[3] |  |  |  |
BE-4 |  USA | Blue Origin | New Glenn, Vulcan | Active[4] | 1st  | CH4 / LOX | Staged, oxidizer-rich | 340[3] | 2,400,000[5][6] | 138[3] |  |  |
BE-7 |  USA | Blue Origin | Blue Moon | Development  | 1st  | LH2 / LOX | Expander, open |  | 44,000 |  |  |  |
CE-20 |  India | LPSC | GSLV Mk III | Active  | Upper  | LH2 / LOX | Gas generator | 434 | 196,500 | 60.00 | 588 | 34.1 | 5.05
CE-7.5 |  India | LPSC | GSLV Mk II | Active  | Upper  | LH2 / LOX | Staged, fuel-rich | 454[7] | 73,500 | 58 | 445 | 16.85 |
E2 |  USA | ABL Space Systems | RS1 | Active  | 1st  | RP-1 / LOX // Jet-A / LOX  | Gas generator |  | 53,800[8] | 64  |  |  |
E2 Vacuum |  USA | ABL Space Systems | RS1 | Active  | 2nd  | RP-1 / LOX // Jet-A / LOX  | Gas generator |  | 57,800[8] |  |  |  |
Engine-2 |  USA | Vast | TBA | Development  | 1st  | RP-1 / LOX | Staged, oxidizer-rich | 327[9]
290 (SL) | 100,000[9] | 100  |  |  | 2.62
Engine-2 Vacuum |  USA | Vast | TBA | Development  | 2nd  | RP-1 / LOX | Staged, oxidizer-rich | 365[9] | 100,000[9] |  |  |  | 2.62
GEM 63 |  USA | Northrop Grumman | Atlas V | Active  | Booster | HTPB | Solid fuel  | 279.06 (Vac)[10] | 1,662,745[11] |  | 49,300 with fuel  |  |
GEM 63XL |  USA | Northrop Grumman | Vulcan | Active  | Booster | HTPB | Solid fuel  | 280.3 (Vac)[12] | 2,025,720[11] |  | 53,400 with fuel  |  |
Hadley |  USA | Ursa Major Technologies | Rocket 4 | Active  | 2nd  | RP-1 / LOX | Staged, oxidizer-rich |  | 22,241 (SL)[13] | 62  |  |  |
Helix |  Germany | Rocket Factory Augsburg | RFA One | Development  | 1st, 2nd  | RP-1 / LOX | Staged, oxidizer-rich | 350,
325 (SL)[14] | 100,000[14] | 100[15] |  |  |
HyPER-15[16] |  South Korea | Innospace | Hanbit-Nano, -Micro, -Mini  | Development  | 1st  | Paraffin / LOX | Electric pump | 292 | 150,000[17] |  |  |  |
LE-5B |  Japan | Mitsubishi, JAXA | H-IIA,
H-IIB | Active  | Upper  | LH2 / LOX | Expander, open | 447[18] | 137,000 | 36.0 | 269 | 51.93 | 5
LE-7A |  Japan | Mitsubishi, JAXA | H-IIA,
H-IIB | Active  | 1st  | LH2 / LOX | Staged, fuel-rich | 438[19]
338 (SL)[19] | 1,098,000
870,000 (SL) | 120 | 1,800 | 65.9 | 5.9
LE-9 |  Japan | Mitsubishi, JAXA | H-3 | Development  | 1st  | LH2 / LOX | Expander, open | 425[20] | 1,471,000 | 100 | 2,400 | 62.5 | 5.9
Lightning 1 |  USA | Firefly Aerospace | Alpha | Active  | 2nd  | RP-1 / LOX | Combustion tap-off | 322[21] | 70,100[21] |  |  |  |
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 |  Europe | 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,[c] 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] (Vac)

| 184,000[21] | 75  |  |  |
RL-10A-4-2[47] |  USA | Aerojet Rocketdyne | Atlas IIIB, V | Retired  | Upper  | LH2 / LOX | Expander, closed | 451 | 99,195 | 42 | 168 | 60.27 | 5.5
RL-10B-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
RL-10C-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 |
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 |  |
SLS Solid Rocket Booster[d] |  USA | Orbital ATK | SLS | Active  | Booster | PBAN | Solid fuel  | 267 | 16,000,000 |  | 730,000
with fuel  |  |
SLV-1 |  India | Godrej & Boyce | PSLV | Active  | Booster | HTPB | Solid fuel  | 253[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 |  Europe | Avio | Vega-C | Active  | 3rd  | HTPB | Solid fuel  | 295.2[62] | 314,000[62] | 75 | 11,400 with fuel  |  |
Zefiro 40 |  Europe | 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 canceled rocket engines

[edit]

Engine  | Origin  | Designer  | Vehicle | Status  | Use | Propellant | Power cycle  | Specific impulse (s)[a] | Thrust (N)[a] | Chamber pressure (bar)  | Mass (kg)  | Thrust:​weight ratio[e] | 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 |  Europe | 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 |  Europe | Airbus Defence and Space | 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
Delphin |  USA | Astra Space | Rocket 3.3 | Retired  | 1st  | RP-1 / LOX[68] | Electric pump |  | 29,000[69] | 31  |  |  |
F-1[f] |  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[g][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
HM-7A |  Europe | Snecma | Ariane 1 | Retired  | 3rd  | LH2 / LOX | Gas generator | 443[75]
308 (SL) | 61,700 | 30 | 149 | 42.2 | 5
HM-7B |  Europe | Snecma | Ariane 2, 3, 4, 5 ECA | 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 |
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-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
M-1 |  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[83]
282 (SL)[83] | 723,000 | 97 | 470 | 158 | 2.34
Merlin Vacuum 1C |  USA | SpaceX | Falcon 9 v1.0 | Retired  | 2nd  | RP-1 / LOX | Gas generator | 336[84] | 413,644[84] |  |  | 92 |
NewtonThree |  USA | Virgin Orbit | LauncherOne | Retired  | Booster | RP-1 / LOX | Gas generator[85] |  | 266,893[86] | 70  |  |  |
NewtonFour |  USA | Virgin Orbit | LauncherOne | Retired  | 2nd  | RP-1 / LOX | Gas generator[85] |  | 22,241[86] |  |  |  |
P80 |  Europe | Avio | Vega | Retired  | 1st  | HTPB | Solid fuel  | 280[87] | 3,015,000[87] | 88 | 96,000 with fuel  |  |
P230 |  Europe | Avio | Ariane 5 | Retired  | Booster | HTPB | Solid fuel  | 286[88]
259 (SL) | 6,996,000
5,860,000 (SL) | 69 | 269,000 with fuel[88] |  |
RD-0120
11Д122 |  Soviet Union | KBKhA | Energia | Retired  | 1st  | LH2 / LOX | Staged, fuel-rich | 455[89] | 1,962,000
1,526,000 (SL) | 219 | 3,450 | 57.80 |
RD-8,
11D513 |  Soviet Union | Pivdenne/​Pivdenmash | Zenit | 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[90] | 69,626 | 55.9 | 282 | 25.17 |
RD-117
11Д511 |  Soviet Union | NPO Energomash | Soyuz-U | Retired  | 1st  | RP-1 / LOX | Gas generator | 316[91]
253 (SL) | 978,000
778,648 (SL) | 54.2 | 1,100 | 72.18 |
RD-118
11Д512 |  Soviet Union | NPO Energomash | Soyuz-U | Retired  | 2nd  | RP-1 / LOX | Gas generator | 314[91]
257 (SL) | 1,000,278
818,855 (SL) | 59.7 | 1,100 | 75.91 |
RD-170[h]11Д521[92] |  Soviet Union | NPO Energomash | Energia | 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[93]
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[94]
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[95]
293 (SL) | 4,521,000 | 206 | 3,600 | 128.15 |
RD-270[i]
8Д420 |  Soviet Union | NPO Energomash | UR-700 (proposed), UR-900 (proposed)  | Tested, Cancelled  | 1st  | N2O4 / UDMH | Staged, full-flow | 322[96]
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[97]
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 |  |  |  |  |  |
RD-855
8D68M |  Soviet Union | Pivdenne/​Pivdenmash | Tsyklon-2, -3, R-36 | Retired  | 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 | Retired  | 2nd vernier  | N2O4 / UDMH | Gas generator |  | 54,230 | 71.60 | 112.5 |  | 1.98
RD-861
11D25 |  Soviet Union | Pivdenne/​Pivdenmash | Tsyklon-2, -3 | Retired  | 3rd  | N2O4 / UDMH | Gas generator |  | 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-27A |  USA | Rocketdyne | Delta | Retired  | 1st  | RP-1 / LOX | Gas generator | 302[98]
255 (SL) | 1,054,200 | 49 | 1,091 | 102.5 | 2.245
RS-68A[j] |  USA | Rocketdyne | Delta IV, IV Heavy | Retired  | 1st  | LH2 / LOX | Gas generator | 411[99]
362 (SL) | 3,558,577
3,135,996 (SL) | 109 | 6,686 | 54.31 | 5.97
Space Shuttle Solid Rocket Booster[k] |  USA | Thiokol | Space Shuttle, Ares I | Retired  | 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 | Retired  | Booster | HTPB | Solid fuel  | 280[100] | 2,250,000 |  | 76,400 with fuel  |  |
UA1207 |  USA | United Technologies | Titan IV | Retired  | 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 | Retired  | 1st  | N2O4 / UDMH | Gas generator |  | 690,000
611,200 (SL) |  | 776 | 90.67 |
Viking 2B |  Europe | Snecma | Ariane 2, 3 | Retired  | 1st  | N2O4 / UH 25 | Gas generator |  | 643,000 (SL) |  | 776 | 84.5 |
Viking 4 |  Europe | Snecma | Ariane 1 | Retired  | 2nd  | N2O4 / UDMH | Gas generator |  | 713,000 |  | 826 | 88 |
Viking 4B |  Europe | Snecma | Ariane 2, 3, 4 | Retired  | 2nd  | N2O4 / UH 25 | Gas generator |  | 800,000 |  | 826 | 98.76 |
Viking 5C |  Europe | Snecma | Ariane 4 | Retired  | 1st  | N2O4 / UH 25 | Gas generator |  | 758,000
678,000 (SL) |  | 826 | 93.57 |
Viking 6 |  Europe | 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[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 | Retired  | 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 | Retired  | Upper  |  | Solid fuel  | 278[106]
245 (SL) | 29,400
25,900 (SL) |  | 87 | 34.48 |
Zefiro 23 |  Europe | Avio | Vega | Retired  | 2nd  | HTPB | Solid fuel  | 287.5[107] | 1,122,000[107] | 94 | 25,935 with fuel  |  |

## See also

[edit]

* 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

[edit]

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

## References

[edit]

1. ^ a b c d "In-Space Product Data Sheets" (PDF). Aerojet Rocketdyne. September 13, 2019. Archived from the original (PDF) on January 11, 2020. Retrieved January 29, 2020.
2. ^ a b Parsonson, Andrew (September 22, 2022). "Everything you need to know about Isar Aerospace". European Spaceflight. Retrieved April 13, 2025.
3. ^ a b c d "First Look Inside Blue Origin's New Glenn Factory w/ Jeff Bezos!". YouTube. August 15, 2024. Retrieved August 16, 2024.
4. ^ Belam, Martin (January 8, 2024). "Nasa Peregrine 1 launch: Vulcan Centaur rocket carrying Nasa moon lander lifts off in Florida – live updates". the Guardian. ISSN 0261-3077. Retrieved January 8, 2024.
5. ^ Ferster, Warren (September 17, 2014). "ULA To Invest in Blue Origin Engine as RD-180 Replacement". Space News. Archived from the original on September 18, 2014. Retrieved September 19, 2014.
6. ^ "BE-4". Blue Origin. Archived from the original on September 17, 2014. Retrieved September 17, 2014.
7. ^ "GSLV Launch Vehicle Information". Spaceflight101.com. Archived from the original on January 6, 2014. Retrieved January 6, 2014.
8. ^ a b "RS1". ABL. Retrieved August 21, 2022.
9. ^ a b c d "Engine-2". LAUNCHER. Archived from the original on October 26, 2021. Retrieved November 9, 2019.
10. ^ "NG Prop Catalog" (PDF). December 10, 2020. Archived from the original (PDF) on December 10, 2020.
11. ^ a b "Developing Vulcan Centaur". ULA. April 4, 2019. Archived from the original on August 25, 2019.
12. ^ "NG Prop Catalog" (PDF). December 10, 2020. Archived from the original (PDF) on December 10, 2020.
13. ^ "The Engines". Ursa Major Technologies. Retrieved May 20, 2017.
14. ^ a b Arizaga, Monica (March 18, 2022). ""Helix" - public names RFA engine". Rocket Factory Augsburg. Retrieved September 28, 2023.
15. ^ Arizaga, Monica (July 13, 2022). "RFA successfully hot fires Helix engine for a total of 74 seconds". Rocket Factory Augsburg. Retrieved September 28, 2023.
16. ^ "South Korea's INNOSPACE will launch Brazilian payload on inaugural flight from Alcântara". May 7, 2022.
17. ^ "innospacecorp on Twitter: "Very proud and excited as we get ready to test the world's largest LOx/Paraffin Hybrid rocket engine developed for a smallsat Launcher.The HyPER-15, a 150kN Hybrid rocket engine, is scheduled to test this month at our Geumsan Engine Test Facility. Keep an eye out for our updates!"". Twitter. Retrieved July 26, 2021.
18. ^ "LE-5B". Encyclopedia Astronautica. Archived from the original on October 27, 2016. Retrieved January 13, 2016.
19. ^ a b "LE-7A". Encyclopedia Astronautica. Archived from the original on February 28, 2017. Retrieved January 13, 2016.
20. ^ "Request Rejected" (PDF).
21. ^ a b c d "Launch-alpha". Firefly Aerospace. Archived from the original on February 24, 2021. Retrieved February 2, 2020.
22. ^ a b c d e f "M10 Engine". Avio.
23. ^ a b c "Merlin 1D". SpaceX. Archived from the original on September 6, 2015. Retrieved February 26, 2016.
24. ^ "Evolution of the SpaceX Merlin engine". www.b14643.de. Retrieved May 8, 2022.
25. ^ "SpaceX Falcon 9 Product Page". Archived from the original on August 5, 2014. Retrieved November 1, 2015.
26. ^ "SpaceX". SpaceX. Retrieved September 24, 2020.
27. ^ a b "MLV". Retrieved August 16, 2024.
28. ^ "NK-33". Encyclopedia Astronautica. Archived from the original on June 25, 2002. Retrieved January 30, 2014.
29. ^ a b c "Press release: Successful first test firing for the P120C solid rocket motor for Ariane 6 and Vega-C" (PDF).
30. ^ a b "Spacex Raptor". NASA SpaceFlight. March 7, 2014. Retrieved July 2, 2015.
31. ^ a b c d e f g "Raptor 3 (sea level variant) Thrust: 280tf Specific impulse: 350s Engine mass: 1525kg Engine + vehicle-side commodities and hardware mass : 1720kg". August 3, 2024.
32. ^ "Raptor 1 vs Raptor 2: What did SpaceX change?". July 14, 2022.
33. ^ a b "Raptor V3 just achieved 350 bar chamber pressure (269 tons of thrust). Congrats to @SpaceX propulsion team! Starship Super Heavy Booster has 33 Raptors, so total thrust of 8877 tons or 19.5 million pounds". May 13, 2023.
34. ^ a b Katy Groom; Rebecca Bolt; Resa Cancro; Patrice Hall; Kandi Lawson; Mark Mercadante; Michelle Moore; Jane Provancha; Matthew Thompson; Don Dankert; James Brooks; Daniel Czelusnaik; Eva Long (August 1, 2019). "Draft Environmental Assessment for the SpaceX Starship and Super Heavy Launch Vehicle at Kennedy Space Center (KSC)" (PDF). netspublic.grc.nasa.gov. Space Exploration Technologies Corporation. p. 250\. Archived (PDF) from the original on August 2, 2019. Retrieved August 5, 2019.
35. ^ "In a few years, we will finally have a Raptor 3/4 vacuum version (giant nozzle) that has an Isp of 380". August 3, 2024.
36. ^ "RD-0124 Engine". KBKha. Retrieved January 7, 2016.
37. ^ "ГКНПЦ имени М.В.Хруничева | Жидкостный ракетный двигатель РД - 0146". www.khrunichev.ru. Archived from the original on December 29, 2021. Retrieved July 27, 2019.
38. ^ a b "RD-107A and RD-108A". NPO Energomash. Retrieved June 30, 2015.
39. ^ "RD-171M". NPO Energomash. Retrieved June 30, 2015.
40. ^ "RD-180". NPO Energomash. Retrieved June 30, 2015.
41. ^ "RD-191". NPO Energomash. Retrieved June 30, 2015.
42. ^ "RD-276 "Comrade"". NPO Energomash. Archived from the original on January 27, 2022. Retrieved October 14, 2019.
43. ^ a b "RD-801". www.yuzhnoye.com. Archived from the original on February 25, 2022. Retrieved January 19, 2020.
44. ^ "RD-810". www.yuzhnoye.com. Archived from the original on February 25, 2022. Retrieved January 19, 2020.
45. ^ "RD-861K". www.yuzhnoye.com. Archived from the original on February 25, 2022. Retrieved January 19, 2020.
46. ^ "RD-870". Yuzhnoye SDO. Archived from the original on February 25, 2022. Retrieved January 19, 2020.
47. ^ a b c "RL10 Data Sheet-1" (PDF). February 2016. Archived from the original (PDF) on July 5, 2016. Retrieved March 23, 2019.
48. ^ Aerojet Rocketdyne, RS-25 Engine Archived 2015-12-29 at the Wayback Machine (accessed July 22, 2014)
49. ^ a b "Rocket Lab Increases Electron Payload Capacity, Enabling Interplanetary Missions and Reusability". Rocket Lab. Retrieved October 26, 2020.
50. ^ "PSLV-1". Archived from the original on August 5, 2014. Retrieved April 4, 2014.
51. ^ a b "LVM3". Archived from the original on September 10, 2015. Retrieved December 21, 2014.
52. ^ "ISRO Press Release: S200 First Static Test (S-200-ST-01)" (PDF). Archived from the original (PDF) on March 11, 2013. Retrieved September 25, 2015.
53. ^ "Isro successfully tests world's 3rd largest solid booster". dna. Retrieved October 4, 2014.
54. ^ "India to test world's third largest solid rocket booster". Science and Technology Section. The Hindu News Paper. December 7, 2009. Retrieved December 7, 2009.
55. ^ "SLV-1". Archived from the original on August 5, 2014. Retrieved April 4, 2014.
56. ^ "SRB-A3". Spaceflight101. Retrieved January 13, 2016.
57. ^ ""天鹊"80吨液氧甲烷发动机100%推力100秒试车圆满成功". 微信公众平台.
58. ^ "Vinci". Encyclopedia Astronautica. Archived from the original on October 27, 2016. Retrieved June 10, 2017.
59. ^ "Vinci® engine" (PDF). Ariane. Retrieved October 10, 2022.
60. ^ a b c d e f g h i j k "2.2 LM-3A Launch Vehicle". LM-3A Series Launch Vehicle User's Manual. Issue 2011 (PDF). CASC. 2011. pp. 2–4. Retrieved January 16, 2016.
61. ^ 孙纪国; 郑孟伟; 龚杰峰; 陶瑞峰 (January 15, 2022). "220tf补燃循环氢氧发动机研制进展" (in Simplified Chinese). 《火箭推进》2022年02期. Retrieved June 5, 2022.
62. ^ a b "VEGA C: 3° stage - zefiro 9". Avio.com. Archived from the original on June 5, 2019. Retrieved January 20, 2020.
63. ^ a b "Zefiro 40 Motor Main Characteristics". Avio.com. Retrieved May 24, 2021.
64. ^ a b "Nova". Stoke Space / 100% reusable rockets / USA. Retrieved December 18, 2024.
65. ^ a b "Terran 1 Technical Specifications". Relativity. Retrieved October 5, 2019.
66. ^ "Aestus Rocket Engine". Airbus Defence and Space. Archived from the original on April 20, 2015. Retrieved January 29, 2014.
67. ^ "Aestus Rocket Engine". Airbus Defence and Space. Archived from the original on May 28, 2015. Retrieved January 29, 2014.
68. ^ a b "Astra Space Rocket". www.spacelaunchreport.com. Retrieved July 3, 2020.
69. ^ a b "Astra Media Kit LV0006" (PDF). August 28, 2021.
70. ^ "Atlas V Solid Rocket Motor". Aerojet Rocketdyne. Archived from the original on March 14, 2017. Retrieved June 2, 2015.
71. ^ "AR1 Engine". Aerojet Rocketdyne. Archived from the original on March 4, 2016. Retrieved October 26, 2016.
72. ^ Levack, Daniel (April 1, 1993). Advanced transportation system studies. Alternate propulsion subsystem concepts: Propulsion database (PDF) (Report) – via ntrs.nasa.gov.
73. ^ "Gamma 2". Encyclopedia Astronautica. Archived from the original on May 22, 2013. Retrieved April 26, 2013.
74. ^ "Gamma 8". Encyclopedia Astronautica. Archived from the original on May 22, 2013. Retrieved April 26, 2013.
75. ^ Wade, Mark. "HM7-A". Encyclopedia Astronautica. Archived from the original on December 21, 2016. Retrieved June 10, 2017.
76. ^ a b c d "HM-7 and HM-7B Rocket Engine - Thrust Chamber". Airbus Defence and Space. Archived from the original on March 18, 2015. Retrieved November 1, 2015.
77. ^ a b Wade, Mark. "HM7-B". Encyclopedia Astronautica. Archived from the original on December 27, 2016. Retrieved June 10, 2017.
78. ^ Wade, Mark. "J-2". Encyclopedia Astronautica. Archived from the original on July 19, 2016. Retrieved December 23, 2011.
79. ^ "J-2X Engine". Pratt & Whitney Rocketdyne. Archived from the original on January 3, 2012. Retrieved December 23, 2011.
80. ^ "LE-5". Encyclopedia Astronautica. Archived from the original on October 27, 2016. Retrieved January 13, 2016.
81. ^ "LE-5A". Encyclopedia Astronautica. Archived from the original on March 11, 2016. Retrieved January 13, 2016.
82. ^ "LE-7". Encyclopedia Astronautica. Archived from the original on March 11, 2016. Retrieved January 13, 2016.
83. ^ a b "Merlin section of Falcon 9 page". SpaceX. Archived from the original on July 15, 2013. Retrieved October 16, 2012.
84. ^ a b "Falcon 9 Space Launch Report". SpaceLaunchReport. Retrieved November 1, 2015.
85. ^ a b Sargent, Scott R.; Noall, Jeff; Becker, Matthew; MacKlin, Scott (2016). "Turbopump Design and Development for the Virgin Galactic Newton Three Engine System". 52nd AIAA/SAE/ASEE Joint Propulsion Conference. doi:10.2514/6.2016-4984. ISBN 978-1-62410-406-0.
86. ^ a b "LauncherOne Service Guide" (PDF). Archived from the original (PDF) on October 22, 2017.
87. ^ a b "VEGA: 1° stage - P80 Motor". Avio.com. Retrieved January 20, 2020.
88. ^ a b "P230". Encyclopedia Astronautica. Archived from the original on December 31, 2011. Retrieved December 27, 2011.
89. ^ "RD0120". KBKhA.
90. ^ "KVD1 Rocket Engine" Двигатель КВД1 (in Russian). КБХМ им. A.M. Исаева. Archived from the original on February 2, 2014. Retrieved May 31, 2013.
91. ^ a b "RD-117". Liquid Propellant Rocket Engines. Archived from the original on August 26, 2012. Retrieved November 27, 2012.
92. ^ "RD-170". Encyclopedia Astronautica. Archived from the original on August 8, 2016. Retrieved September 24, 2019.
93. ^ "Antares 200 Series – Rockets".
94. ^ "Универсальный ракетный двигатель РД-193. Мнение инженера-разработчика". Журнал «Новости космонавтики». Archived from the original on October 18, 2016. Retrieved January 6, 2016.
95. ^ Wade, Mark. "RD-264". Encyclopedia Astronautica. Archived from the original on October 14, 2016. Retrieved June 10, 2017.
96. ^ "RD-270 (8D420)". NPO Energomash. Retrieved February 6, 2023.
97. ^ "RD-253 and RD-275". NPO Energomash. Archived from the original on April 5, 2015. Retrieved June 30, 2015.
98. ^ "RS-27A". Encyclopedia Astronautica. Archived from the original on August 25, 2016. Retrieved November 2, 2021.
99. ^ "RS-68A". www.rocket.com. Retrieved January 19, 2020.
100. ^ "SRB-A". Encyclopedia Astronautica. Archived from the original on March 1, 2002. Retrieved January 13, 2016.
101. ^ "UA1207". Encyclopedia Astronautica. Archived from the original on March 4, 2016. Retrieved December 27, 2015.
102. ^ a b c "Vulcain Astrium". Airbus Defence and Space. Archived from the original on February 25, 2012. Retrieved December 27, 2011.
103. ^ a b c "Vulcain". Encyclopedia Astronautica. Archived from the original on December 28, 2016. Retrieved December 27, 2011.
104. ^ a b c d "Vulcain Astrium". Airbus Defence and Space. Archived from the original on March 27, 2012. Retrieved December 27, 2011.
105. ^ a b "Vulcain 2". Encyclopedia Astronautica. Archived from the original on December 28, 2016. Retrieved December 27, 2011.
106. ^ "Black Arrow-3". Encyclopedia Astronautica. Archived from the original on December 28, 2016. Retrieved April 26, 2013.
107. ^ a b "VEGA: 2° stage - zefiro 23". Avio.com. Retrieved January 20, 2020.

* 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
* YF-79
* YF-90
* 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
* United States
* BE-3U
* BE-7
* J-2
* RL10
* RS-25
* RS-68

|

Methalox
(CH4 / LOX)|

* China
* BF-20
* Lingyun
* Longyun
* TQ-11
* TQ-12
* TQ-15A
* YF-209
* YF-215
* United States
* BE-4
* Raptor
* Archimedes
* Aeon 1
* Aeon R
* Russia
* RD-0169
* Europe
* Prometheus
* M-10

Semi-
cryogenic|

| Kerolox
(RP-1 / LOX)|

* China
* TH-11
* TH-12
* YF-100
* YF-102
* YF-115
* YF-130
* Welkin
* India
* SCE-200
* Russia
* NK-15
* NK-33, 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
* Spain
* TEPREL
* Ukraine
* RD-8
* RD-801
* RD-810
* United States
* F-1
* H-1
* Kestrel
* LR-79
* LR89
* LR105
* LR70-NA , S-3D
* Merlin
* RS-27
* RS-27A
* RS-56
* S-3D
* Rutherford
* XLR50

|

Storable|

| Hypergolic (Aerozine,
UH 25, MMH, or UDMH
/ 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 to 219
* RD-250 to 252, 261, 262
* RD-253, 275
* RD-263, 268, 273
* RD-270
* S5.92
* S5.98M
* Ukraine
* RD-843
* RD-854, 861
* RD-855
* RD-856
* RD-864, 869
* United States
* AJ10
* LR-87
* LR-91
* RS-88*
* TR-201
* XLR81*

|

Other|

* Russia
* RD-109, 119
* RD-211 to 214
* UK
* Gamma
* United States
* Curie
* RS-88*
* XLR81*

Solid
fuel|

* China
* FG-02
* FG-36
* FG-46
* FG-47
* SpaB-65
* SpaB-140C
* Europe
* Mage 1
* P-4
* P-6
* PAP
* P80
* P120C
* P230
* Topaze
* Waxwing
* Zefiro 9
* Zefiro 23
* Zefiro 40
* India
* S7
* S9
* S12
* S139
* S200
* Iran
* Salman
* Rafe
* Israel
* LK-1
* RSA-3
* Japan
* KM-V1
* KM-V2b
* M-14
* M-24
* M-34
* M-34c
* SRB-A
* United States
* AJ-60A
* Algol
* Castor 30
* GEM
* Orbus-6
* Orbus-21
* Orion
* Space Shuttle SRB
* Star 37
* Star 48
* UA120
* SRMU
* X-248
* X-254

* * Different versions of the engine use different propellant combinations
* Engines in italics are under development

*[TBA]: To be announced
*[est.]: goal
*[v]: View this template
*[t]: Discuss this template
*[e]: Edit this template