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 canceled 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] | Oxidiser:​fuel ratio

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AJ-10-190  |  USA  | Aerojet | Space Shuttle, Orion, Apollo CSM  | Active  | Upper  | N2O4/MMH | Pressure-fed | 316[1] | 26,689[1] | 8.62[1] | 118[1] | 23.08 |
Archimedes  |  New Zealand  USA  | Rocket Lab | Neutron  | Development  | 1st  | CH4 / LOX | Staged, oxidizer-rich |  | 730,000 |  |  |  |
Aeon-R |  USA  | Relativity Space | Terran R  | Development  | 1st, 2nd  | CH4 / LOX | Gas generator |  |  |  |  |  |
BE-3  |  USA  | Blue Origin | New Shepard | Active  | 1st  | LH2 / LOX | Combustion tap-off |  | 490,000[2] |  |  |  |
BE-3U  |  USA  | Blue Origin | New Glenn | Development  | 2nd  | LH2 / LOX | Expander, open |  | 710,000[2] |  |  |  |
BE-4  |  USA  | Blue Origin | New Glenn, Vulcan  | Active[3] | 1st  | CH4 / LOX | Staged, oxidizer-rich | 339[4] | 2,400,000[5][6] | 134[7] |  |  |
CE-20  |  India  | LPSC | GSLV Mk III | Active  | Upper  | LH2 / LOX | Gas generator | 434 | 196,500 | 60.00 | 588 | 34.1 | 5.05
CE-7.5  |  India  | LPSC | GSLV Mk II  | Active  | Upper  | LH2 / LOX | Staged | 454[8] | 73,500 | 58 | 445 | 16.85 |
E2  |  USA  | ABL Space Systems | RS1  | Active  | 1st  | RP-1 / LOX | Gas generator |  | 53,800[9] |  |  |  |
E2 Vacuum  |  USA  | ABL Space Systems | RS1  | Active  | 2nd  | RP-1 / LOX | Gas generator |  | 57,800[9] |  |  |  |
Engine-2 |  USA  | Vast | TBA  | Development  | 1st  | RP-1 / LOX | Staged, oxidizer-rich | 327[10]
290 (SL) | 100,000[10] |  |  |  | 2.62
Engine-2 Vacuum |  USA  | Vast | TBA  | Development  | 2nd  | RP-1 / LOX | Staged, oxidizer-rich | 365[10] | 100,000[10] |  |  |  | 2.62
GEM 63 |  USA  | Northrop Grumman | Atlas V | Active  | Booster | HTPB  | Solid fuel  | 279.06 (Vac)[11] | 1,662,745[12] |  | 49,300 with fuel  |  |
GEM 63XL |  USA  | Northrop Grumman | Vulcan  | Active  | Booster | HTPB  | Solid fuel  | 280.3 (Vac)[13] | 2,025,720[12] |  | 53,400 with fuel  |  |
Hadley  |  USA  | Ursa Major Technologies | Rocket 4 | Active  | 2nd  | RP-1 / LOX | Staged, oxidizer-rich |  | 22,241 (SL)[14] |  |  |  |
Germany  | Rocket Factory Augsburg | RFA One | Development  | 1st, 2nd  | RP-1/LOX  | Staged combustion | 350,
325 (SL)[15] | 100,000[15] | 100[16] |  |  |
HM-7B  |  Europe  | Snecma  | Ariane 2, 3, 4, 5 ECA | Active  | Upper  | LH2 / LOX | Gas generator | 446[17]
310 (SL)[18] | 64,800[17]
43,600 (SL)[18] | 37[17] | 165[17] | 43.25 | 5
HyPER-15[19] |  South Korea  | Hanbit-Nano, -Micro, -Mini  | Development  | 1st  | Paraffin / LOX | Electric pump | 292 | 150,000[20] |  |  |  |
LE-5B  |  Japan  | Mitsubishi, JAXA  | H-IIA,
H-IIB | Active  | Upper  | LH2 / LOX | Expander, open | 447[21] | 137,000 | 36.0 | 269 | 51.93 | 5
LE-7A  |  Japan  | Mitsubishi, JAXA  | H-IIA,
H-IIB | Active  | 1st  | LH2 / LOX | Staged | 438[22]
338 (SL)[22] | 1,098,000
870,000 (SL) | 120 | 1,800 | 65.9 | 5.9
LE-9  |  Japan  | Mitsubishi, JAXA  | H-3 | Development  | 1st  | LH2 / LOX | Expander, open | 425[23] | 1,471,000 | 100 | 2,400 | 62.5 | 5.9
Lightning 1 |  USA  | Firefly Aerospace | Alpha | Active  | 2nd  | RP-1 / LOX | Combustion tap-off | 322[24] | 70,100[24] |  |  |  |
Merlin 1D FT  |  USA  | SpaceX | Falcon 9 B5, Heavy | Active  | 1st  | RP-1 / LOX | Gas generator | 311 | 914,000[25]
845,000 (SL)[25] | 108.0[26] | 470 | 194.5[25] |
Merlin Vacuum 1D  |  USA  | SpaceX | Falcon 9 B5, Heavy | Active  | 2nd  | RP-1 / LOX | Gas generator | 348[27] | 981,000[28] |  |  |  | 2.36
M10 |  EU  | Avio | Vega-E[29] | Development  | Upper[29] | CH4 / LOX[29] | Expander, closed | 362[29] | 98,000[29] |  |  |  | 3.4[29]
NK-33A (AJ26-62),
11Д111 / 14Д15 |  Soviet Union  | JSC Kuznetsov | Antares 100, Soyuz-2-1v | Active  | 1st  | RP-1 / LOX | Staged, oxidizer-rich | 331[30]
297 (SL) | 1,680,000
1,510,000 (SL) | 145 | 1,222 | 136.8 |
P80 |  Europe  | Avio | Vega | Active  | 1st  | HTPB  | Solid fuel  | 280[31] | 3,015,000[31] | 88 | 96,000 with fuel  |  |
P120 |  Europe  | Avio | Ariane 6,
Vega-C  | Active  | Booster, 1st  | HTPB  | Solid fuel  | 279[32] | 4,650,000[32] | 105 | 153,000 with fuel[32] |  |
S139 |  India  | SDSC | PSLV  | Active  | 1st  | HTPB  | Solid fuel  | 269[33] | 4,860,000 | 58 | 160,200
with fuel  |  |
Raptor[34] |  USA  | SpaceX | Starship | Development  | 1st, 2nd  | CH4 / LOX | Staged, full-flow | 350[35]
327 (SL) | 2,640,000 (SL)[36] | 350[36] | 1,600 est.[37] | 168 est.[36][37] | 3.6[38]
Raptor Vacuum[34] |  USA  | SpaceX | Starship  | Development  | 2nd  | CH4 / LOX | Staged, full-flow | 380[35] | >2,640,000 [36] | 350[36] | >1,600[37] | <120[39] | 3.6[38]
RD-0124,
14Д23 |  Russia  | KBKhA  | Soyuz-2.1b,
Soyuz-2-1v,
Angara | Active  | 2nd, 3rd  | RP-1 / LOX | Staged, oxidizer-rich | 359[40] | 294,300 | 160 | 520 | 57.7 |
RD-0146D  |  Russia  | KBKhA  | Angara | Development  | Upper  | LH2 / LOX | Expander, closed | 470[41] | 68,600 | 59 |  |  |
RD-107A,
14Д22 |  Russia  | NPO Energomash | Soyuz-FG, -2  | Active  | 1st  | RP-1 / LOX | Gas generator | 320.2[42]
263.3 (SL) | 1,019,892
839,449 (SL) | 61.2 | 1,090 | 78.53 |
RD-108A,
14Д21 |  Russia  | NPO Energomash | Soyuz-FG, -2  | Active  | 2nd  | RP-1 / LOX | Gas generator | 320.6[42]
257.7 (SL) | 921,825
792,377 (SL) | 55.5 | 1,075 | 75.16 |
RD-171M,[lower-alpha 3] 11Д520 |  Russia  | NPO Energomash | Soyuz-5, Zenit-2M, -3SL, -3SLB, -3SLBF  | Active  | 1st  | RP-1 / LOX | Staged, oxidizer-rich | 337.2[43]
309.5 (SL) | 7,904,160
7,256,921 (SL) | 250 | 9,300 | 79.57 |
RD-180  |  Russia  | NPO Energomash | Atlas V, III | Active  | 1st  | RP-1 / LOX | Staged, oxidizer-rich | 338.4[44]
311.9 (SL) | 4,152,136
3,826,555 (SL) | 261.7 | 5,480 | 71.2 | 2.72
RD-191  |  Russia  | NPO Energomash | Angara | Active  | 1st  | RP-1 / LOX | Staged, oxidizer-rich | 337.5[45]
311.2 (SL) | 2,084,894
1,922,103 (SL) | 262.6 | 2,200 | 89.09 |
RD-193  |  Russia  | NPO Energomash | Soyuz-2-1v | Development  | 1st  | RP-1 / LOX | Staged, oxidizer-rich | 337.5[46]
311.2 (SL) | 2,084,894
1,922,103 (SL) |  | 1,900 | 103.15 |
RD-276,
14Д14М |  Russia  | NPO Energomash | Proton-M | Active  | 1st  | N2O4 / UDMH  | Staged, oxidizer-rich | 315.8[47]
288 (SL) | 1,831,882
1,671,053 (SL) | 168.5 | 1,120 | 171.2 |
RD-801  |  Ukraine  | Pivdenne/​Pivdenmash | Mayak  | Development  | 1st  | RP-1 / LOX | Staged, oxidizer-rich | 336 [48]
300.7 (SL) | 1,339,255
1,198,608 (SL) | 180 | 1,630 |  | 2.65
RD-809K  |  Ukraine  | Pivdenne/​Pivdenmash | Mayak  | Development  | Upper  | RP-1 / LOX | Staged, oxidizer-rich | 352 [48] | 98,067 |  | 330 |  | 2.62
RD-810  |  Ukraine  | Pivdenne/​Pivdenmash | Mayak, Zenit | Development  | 1st  | RP-1 / LOX | Staged, oxidizer-rich | 335.5 [49]
299 (SL) | 2,104,890
1,876,149 (SL) | 180 | 2,800 |  | 2.65
RD-843  |  Ukraine  | Pivdenne/​Pivdenmash | Vega | Active  | upper  | N2O4 / UDMH  | Pressure-fed | 315.5 | 2,452 | 20.4 | 15.93 |  | 2.0
RD-861K  |  Ukraine  | Pivdenne/​Pivdenmash | Cyclone-4M  | Development  | 2nd  | N2O4 / UDMH  | Gas generator | 330 [50] | 77,629 |  | 207 |  | 2.41
RD-870  |  Ukraine  | Pivdenne/​Pivdenmash | Cyclone-4M  | Development  | 1st  | RP-1 / LOX | Staged, oxidizer-rich | 340 [51]
301.5 (SL) | 876,715
777,667 (SL) |  | 1,353 |  | 2.684
Reaver 1 |  USA  | Firefly Aerospace | Alpha | Active  | 1st  | RP-1 / LOX | Combustion tap-off | 295.6[24] | 184,000[24] |  |  |  |
RL-10A-4-2[52] |  USA  | Aerojet Rocketdyne | Atlas IIIB, V | Active  | Upper  | LH2 / LOX | Expander, closed | 451 | 99,195 | 42 | 168 | 60.27 | 5.5
RL-10B-2[52] |  USA  | Aerojet Rocketdyne | Delta III, IV, SLS | Active  | Upper  | LH2 / LOX | Expander, closed | 465.5 | 110,093 | 44 | 301 | 37.27 | 5.88
RL-10C-1[52] |  USA  | Aerojet Rocketdyne | Delta III, IV, SLS, Vulcan  | Active  | Upper  | LH2 / LOX | Expander, closed | 450 | 101,820 | 44 | 191 | 54.5 | 5.5
RS-25 |  USA  | Rocketdyne | Space Shuttle, SLS | Active  | 1st  | LH2 / LOX | Staged, fuel-rich | 452.3
366 (SL) | 2,279,000
1,860,000 (SL)[53] | 206.4 | 3,526 | 53.79 |
RS-68A[lower-alpha 4] |  USA  | Rocketdyne  | Delta IV, IV Heavy | Active  | 1st  | LH2 / LOX | Gas generator | 411[54]
362 (SL) | 3,558,577
3,135,996 (SL) | 109 | 6,686 | 54.31 | 5.97
Rutherford  |  New Zealand  USA  | Rocket Lab | Electron | Active  | 1st  | RP-1 / LOX | Electric pump | 311 | 24,900
25,000 (SL) |  | 35[55] | 72.8 (SL)  |
Rutherford Vacuum  |  New Zealand  USA  | Rocket Lab | Electron | Active  | 2nd  | RP-1 / LOX | Electric pump | 343 | 25,800[55] |  |  |  |
S200  |  India  | SDSC | GSLV Mk III  | Active  | Booster  | HTPB  | Solid fuel  | 274.5[56] | 5,150,000[57][58][59] |  | 207,000
with fuel[56] |  |
SCE-200  |  India  | LPSC | GSLV Mk III,
ULV  | Development  | Upper, main  | RP-1 / LOX | Staged, oxidizer-rich | 335
299 (SL) | 2,030,000
1,820,000 (SL) | 180 | 2,700 |  |
SLS Solid Rocket Booster[lower-alpha 5] |  USA  | Orbital ATK  | SLS | Active  | Booster  | PBAN | Solid fuel  | 267 | 16,000,000 |  | 730,000
with fuel  |  |
SLV-1 |  India  | Godrej & Boyce  | PSLV  | Active  | Booster  | HTPB  | Solid fuel  | 253[60] | 502,600 | 43 | 10,800
with fuel  |  |
SRB-A3  |  Japan  | IHI Aerospace,
JAXA  | H-IIA,
H-IIB,
Epsilon | Active  | Booster | HTPB  | Solid fuel  | 283.6[61] | 2,305,000
2,150,000 (SL) | 111 | 76,600
with fuel  |  |
TEPREL-B  |  Spain  | PLD Space | Miura 1 | Active  | 1st  | RP-1 / LOX | Pressure-fed |  | 30,200 (SL) |  |  |  |
TEPREL-C  |  Spain  | PLD Space | Miura 5 | Development  | 1st, 2nd  | RP-1 / LOX | Gas-generator |  | 190,000 (SL) |  |  |  |
TQ-12[62] |  China  | Landspace  | ZQ-2  | Active  | 1st  | CH4 / LOX | Gas generator | 284 | 667,000 (SL) | 101 |  |  |
Vikas (rocket engine)  |  India  | LPSC | PSLV, GSLV, GSLV Mk III  | Active  | 2nd, main, booster  | N2O4 / UDMH  | Gas generator | 262 | 680,500–804,500
600,500–756,500 (SL) | 53.0–58.5  |  |  |
Vinci  |  Europe  | Snecma  | Ariane 6 | Development  | Upper  | LH2 / LOX | Expander, closed[63] | 457[64] | 180,000 | 60 | 280 | 65.60 | 6.1
Vulcain 2.1 |  Europe  | Snecma  | Ariane 6 | Development  | 1st  | LH2 / LOX | Gas generator |  | 1,324,000 | 120.8 | 2,000 | 66.2 |
YF-21B  |  China  | AALPT | Long March 2E, 2F, 3 | Active  | Booster, 1st  | N2O4 / UDMH  | Gas generator | 260.66 (SL)[65] | 740,400 (SL)[65] |  |  |  |
YF-21C  |  China  | AALPT | Long March 2C, 2D, 3A, 3B, 3C, 4B, 4C | Active  | 1st  | N2O4 / UDMH  | Gas generator | 260.7 (SL)[65] | 740,400 (SL)[65] |  |  |  |
YF-25  |  China  | AALPT | Long March 3B, 3C | Active  | Booster  | N2O4 / UDMH  | Gas generator | 260.66 (SL)[65] | 740,400 (SL)[65] |  |  |  |
YF-22B  |  China  | AALPT | Long March 2E, 2F | Active  | 2nd  | N2O4 / UDMH  | Gas generator | 298.0[65] | 738,400 |  |  |  |
YF-22C  |  China  | AALPT | Long March 2C, 2D, 4B, 4C | Active  | 2nd  | N2O4 / UDMH  | Gas generator | 298.0[65] | 742,040 |  |  |  |
YF-22D  |  China  | AALPT | Long March 3 | Active  | 2nd  | N2O4 / UDMH  | Gas generator | 298.0[65] | 741,400 |  |  |  |
YF-22E  |  China  | AALPT | Long March 3A, 3B, 3C | Active  | 2nd  | N2O4 / UDMH  | Gas generator | 298.0[65] | 741,400 |  |  |  |
YF-40  |  China  | AALPT | Long March 4B, 4C | Active  | 3rd  | N2O4 / UDMH  | Gas generator | 303 | 103,000 |  |  |  |
YF-50D |  China  | AALPT | Long March 3B, 3C, 5, 7 | Active  | Upper  | N2O4 / UDMH  | Pressure-fed | 315.5 | 6,500 |  |  |  |
YF-73  |  China  | AALPT | Long March 3 | Active  | 3rd  | LH2 / LOX | Gas generator | 420.0 | 44,150 |  |  |  |
YF-75  |  China  | AALPT | Long March 3A, 3B, 3C | Active  | 3rd  | LH2 / LOX | Gas generator | 438.0[65] | 78,450 |  |  |  |
YF-75D  |  China  | AALPT | Long March 5 | Active  | 2nd  | LH2 / LOX | Expander, closed | 442.6 | 88,360 | 41 | 265 | 34 | 6.0
YF-77  |  China  | AALPT | Long March 5 | Active  | 1st  | LH2 / LOX | Gas generator | 428
316.7 (SL) | 700,000
518,000 (SL) | 102 | 1,054 | 50 | 5.5
YF-79  |  China  | AALPT | Long March 9 | Development  | 3rd  | LH2 / LOX | Expander, closed | 455.2 | 250,000 | 70 |  |  | 6.0
YF-90[66] |  China  | AALPT | Long March 9 | Development  | 2nd  | LH2 / LOX | Staged, fuel-rich | 453 | 2,200,000 | 183 | 4,800 | 46.74 | 6.0
YF-100  |  China  | AALPT | Long March 7, 5 | Active  | 1st  | RP-1/ LOX | Staged, oxidizer-rich | 335.1
300(SL) | 1,339,480
1,199,190 (SL) | 180 | 1,912 | 64 | 2.6
YF-115  |  China  | AALPT | Long March 6, 7 | Active  | 2nd  | RP-1/ LOX | Staged, oxidizer-rich | 341.5 | 182,400 | 120 |  |  | 2.5
YF-130  |  China  | AALPT | Long March 9 | Development  | 1st  | RP-1/ LOX | Staged, oxidizer-rich | 308 (SL) | ~5,000,000 (SL) | 220 | ~6,500 | 78 | 2.62
Zefiro 9A |  European Union  | Avio | Vega | Active  | 3rd  | HTPB  | Solid fuel  | 295.2[67] | 314,000[67] | 75 | 11,400 with fuel  |  |
Zefiro 23 |  European Union  | Avio | Vega | Active  | 2nd  | HTPB  | Solid fuel  | 287.5[68] | 1,122,000[68] | 94 | 25,935 with fuel  |  |
Zefiro 40 |  European Union  | Avio | Vega-C  | Active  | 3rd  | HTPB  | Solid fuel  | 293.5[69] | 1,304,000[69] | 115 | 39,206 with fuel  |  |

## Retired and canceled rocket engines

Engine  | Origin  | Designer  | Vehicle | Use | Propellant | Power cycle  | Specific impulse (s)[lower-alpha 1] | Thrust (N)[lower-alpha 1] | Chamber pressure (bar)  | Mass (kg)  | Thrust:​weight ratio[lower-alpha 6] | Oxidiser:​fuel ratio

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Aeon 1 |  USA  | Relativity Space | Terran 1  | 1st  | CH4 / LOX | Gas generator | 310 | 86,740 (SL)[70] |  |  |  |
Aeon 1 Vacuum |  USA  | Relativity Space | Terran 1  | 2nd  | CH4 / LOX | Gas generator | 360 | 100,085 (SL)[70] |  |  |  |
Aestus |  Europe | Airbus Defence and Space | Ariane 5 G, G+, ES  | Upper  | N2O4 / MMH | Pressure-fed | 324[71] | 30,000 | 11 | 111 | 27.6 | 1.9
Aestus II  |  Europe  | Airbus Defence and Space | Ariane 5 | Upper  | N2O4 / MMH | Gas generator | 340[72] | 55,400 | 60 | 138 | 41.0 | 1.9
Aether  |  USA  | Astra Space | Rocket 3.3 | 2nd  | RP-1/LOX[73] | Pressure-fed |  | 3,300[74] |  |  |  |
AJ-60A |  USA  | Aerojet | Atlas V | Booster | HTPB  | Solid fuel  | 275 | 1,270,000[75] |  |  |  |
AJ-260-2  |  USA  | Aerojet | S-I stage replacement (proposed)  | 1st  | PBAN | Solid fuel  | 263 | 26,183,755 |  | 831,345 with fuel  |  |
AR1  |  USA  | Aerojet Rocketdyne |  | 1st  | RP-1 / LOX | Staged, oxidizer-rich |  | 2,200,000 (SL)[76] |  |  |  | 2.72
Delphin  |  USA  | Astra Space | Rocket 3.3 | 1st  | RP-1/LOX[73] | Electric pump |  | 29,000[74] |  |  |  |
F-1[lower-alpha 7] |  USA  | Rocketdyne | Saturn V | 1st  | RP-1 / LOX | Gas generator | 304
263 (SL) | 7,770,000
6,770,000 (SL) | 70 | 8,391 | 82.27 | 2.27
F-1A[lower-alpha 8][77] |  USA  | Rocketdyne |  | 1st  | RP-1 / LOX | Gas generator | 303
270 (SL) | 8,989,000
8,007,000 (SL) | 80 | 9,015 | 90.6 | 2.27
Gamma 2  |  United Kingdom  | Bristol Siddeley  | Black Arrow  | 2nd  | RP-1 / H2O2 | Staged, decomposition and combustion  | 265[78] | 68,200 |  | 173 | 40.22 | 8
Gamma 8  |  United Kingdom  | Bristol Siddeley  | Black Arrow  | 1st  | RP-1 / H2O2 | Staged, decomposition and combustion  | 265[79] | 234,800 | 47.40 | 342 | 70.01 | 8
HM-7A  |  Europe  | Snecma  | Ariane 1 | 3rd  | LH2 / LOX | Gas generator | 443[80]
308 (SL) | 61,700 | 30 | 149 | 42.2 | 5
J-2  |  USA  | Rocketdyne | Saturn V, IB | 2nd, 3rd  | LH2 / LOX | Gas generator | 421[81]
200 (SL) | 1,033,100
486,200 (SL) | 52.6 | 1,438 | 73.18 | 5.5
J-2X  |  USA  | Pratt & Whitney Rocketdyne  | SLS (proposed)  | Upper  | LH2 / LOX | Gas generator | 448[82] | 1,310,000 | 95 | 2,470 | 58.41 | 5.5–4.5
Kestrel  |  USA  | SpaceX | Falcon 1 | Upper  | RP-1 / LOX | Pressure fed  | 317 | 31,000 | 9.3 | 52 | 65 |
LE-5  |  Japan  | Mitsubishi, NASDA  | H-I | Upper  | LH2 / LOX | Gas generator | 450[83] | 103,000 | 36.0 | 245 | 42.87 | 5.5
LE-5A  |  Japan  | Mitsubishi, NASDA  | H-II | Upper  | LH2 / LOX | Expander, open | 452[84] | 121,500 | 40.0 | 242 | 51.19 | 5
LE-7  |  Japan  | Mitsubishi, NASDA  | H-II | 1st  | LH2 / LOX | Staged combustion | 446[85] | 1,078,000
843,500 (SL) | 127 | 1,714 | 64.13 | 5.9
M-1  |  USA  | Aerojet |  | 1st, 2nd?  | LH2 / LOX | Gas generator | 428 (SL) | 6,670,000 |  | 9,068 | 60 |
Merlin 1D  |  USA  | SpaceX | Falcon 9 v1.1 | 1st  | RP-1 / LOX | Gas generator | 311[86]
282 (SL)[86] | 723,000 | 97 | 470 | 158 | 2.34
Merlin Vacuum 1C  |  USA  | SpaceX | Falcon 1, 9 | 2nd  | RP-1 / LOX | Gas generator | 336[87] | 413,644[87] |  |  | 92 |
NewtonThree |  USA  | Virgin Orbit | LauncherOne | Booster | RP-1 / LOX | Gas generator[88] |  | 266,893[89] |  |  |  |
NewtonFour |  USA  | Virgin Orbit | LauncherOne | 2nd  | RP-1 / LOX | Gas generator[88] |  | 22,241[89] |  |  |  |
P230 |  Europe  | Avio | Ariane 5 | Booster | HTPB  | Solid fuel  | 286[90]
259 (SL) | 6,996,000
5,860,000 (SL) | 69 | 269,000 with fuel[90] |
Polaris |  United States  | Exela Space Industries  | Aims-1, Aims-4  | 1st  | Propane/LOX | Pressure-fed | 23  | 2,000  | 25  | 5  | 40.8  | 0.8-1
RD-0120
11Д122 |  Soviet Union  | KBKhA  | Energia  | 1st  | LH2 / LOX | Staged, fuel-rich  | 455[91] | 1,962,000
1,526,000 (SL) | 219 | 3,450 | 57.80 |
RD-8,
11D513 |  Soviet Union  | Pivdenne/​Pivdenmash | Zenit | 2nd vernier  | RP-1 / LOX | Staged, oxidizer-rich | 342 | 78,450 | 77.47 | 356 |  | 2.4
RD-56 (KVD-1)
11Д56У |  Russia  | KBKhM  | GSLV Mk I  | Upper  | LH2 / LOX | Staged, fuel-rich  | 462[92] | 69,626 | 55.9 | 282 | 25.17 |
RD-117
11Д511 |  Soviet Union  | NPO Energomash | Soyuz-U | 1st  | RP-1 / LOX | Gas generator  | 316[93]
253 (SL) | 978,000
778,648 (SL) | 54.2 | 1,100 | 72.18 |
RD-118
11Д512 |  Soviet Union  | NPO Energomash | Soyuz-U | 2nd  | RP-1 / LOX | Gas generator  | 314[93]
257 (SL) | 1,000,278
818,855 (SL) | 59.7 | 1,100 | 75.91 |
RD-170[lower-alpha 9]11Д521[94] |  Soviet Union  | NPO Energomash | Energia  | 1st  | RP-1 / LOX | Staged, oxidizer-rich  | 337.2
309.5 (SL) | 7,904,160
7,256,921 (SL) | 250 | 9,300 | 79.57 |
RD-181  |  Russia  | NPO Energomash | Antares 200  | 1st  | RP-1 / LOX | Staged, oxidizer-rich | 339.2[95]
311.9 (SL) | 2,085,000
1,922,000 (SL) | 262.6 | 2,200 | 89 |
RD-264
11Д119 |  Soviet Union  | NPO Energomash | Dnepr  | 1st  | N2O4 / UDMH  | Staged, oxidizer-rich  | 318[96]
293 (SL) | 4,521,000 | 206 | 3,600 | 128.15 |
RD-270[lower-alpha 10]
8Д420 |  Soviet Union  | NPO Energomash | UR-700 (proposed), UR-900 (proposed)  | 1st  | N2O4 / UDMH  | Staged, full-flow  | 322[97]
301 (SL) | 6,710,000
6,270,000 (SL) | 261 | 3,370 | 189.91 |
RD-275
14Д14 |  Russia  | NPO Energomash | Proton-M | 1st  | N2O4 / UDMH  | Staged, oxidizer-rich  | 316[98]
287 (SL) | 1,831,882
1,671,053 (SL) | 160.0 | 1,070 | 171.2 |
RD-854
8D612 |  Soviet Union  | Pivdenne/​Pivdenmash | R-36ORB  | 3rd  | N2O4 / UDMH  | Gas generator  |  |  |  |  |  |
RD-855
8D68M |  Soviet Union  | Pivdenne/​Pivdenmash | Tsyklon-2, -3, R-36  | 1st vernier  | N2O4 / UDMH  | Gas generator  |  | 328,000 | 65.70 | 320 |  | 1.97
RD-856
8D69M |  Soviet Union  | Pivdenne/​Pivdenmash | Tsyklon-2, -3 (-4), R-36  | 2nd vernier  | N2O4 / UDMH  | Gas generator  |  | 54,230 | 71.60 | 112.5 |  | 1.98
RD-861
11D25 |  Soviet Union  | Pivdenne/​Pivdenmash | Tsyklon-2, -3 | 3rd  | N2O4 / UDMH  | Gas generator  |  | 78,710 | 88.8 | 123 |  | 2.1
RD-864
15D177 |  Soviet Union  | Pivdenne/​Pivdenmash | R-36 (missile), Dnipro  | 3rd  | N2O4 / UDMH  | Gas generator  | 298–309  | 8,450–20,200  | 17–41  | 199 |  | 1.8
RD-869
15D300 |  Soviet Union  | Pivdenne/​Pivdenmash | R-36M  | 3rd  | N2O4 / UDMH  | Gas generator  | 302.3–313  | 8,580–20,470  | 17–41  | 196 |  | 1.8
RS-27A  |  USA  | Rocketdyne | Delta | 1st  | RP-1 / LOX | Gas generator | 302[99]
255 (SL) | 1,054,200 | 49 | 1,091 | 102.5 | 2.245
Space Shuttle Solid Rocket Booster[lower-alpha 11] |  USA  | Thiokol | Space Shuttle, Ares I  | Booster  | PBAN / APCP  | Solid fuel  | 268 | 14,000,000
12,500,000 (SL) |  | 590,000
with fuel  |  |
SRB-A |  Japan  | IHI Aerospace, JAXA  | H-IIA | Booster | HTPB  | Solid fuel  | 280[100] | 2,250,000 |  | 76,400 with fuel  |  |
UA1207  |  USA  | United Technologies | Titan IV  | Booster  | PBAN | Solid fuel  | 272[101]
245 (SL) | 7,116,000
6,410,400 (SL) |  | 319,330
with fuel  |  |
Viking 2  |  Europe  | Snecma  | Ariane 1 | 1st  | N2O4 / UDMH  | Gas generator |  | 690,000
611,200 (SL) |  | 776 | 90.67 |
Viking 2B  |  Europe  | Snecma  | Ariane 2, 3 | 1st  | N2O4 / UH 25 | Gas generator |  | 643,000 (SL) |  | 776 | 84.5 |
Viking 4  |  Europe  | Snecma  | Ariane 1 | 2nd  | N2O4 / UDMH  | Gas generator |  | 713,000 |  | 826 | 88 |
Viking 4B  |  Europe  | Snecma  | Ariane 2, 3, 4 | 2nd  | N2O4 / UH 25 | Gas generator |  | 800,000 |  | 826 | 98.76 |
Viking 5C  |  Europe  | Snecma  | Ariane 4 | 1st  | N2O4 / UH 25 | Gas generator |  | 758,000
678,000 (SL) |  | 826 | 93.57 |
Viking 6  |  Europe  | Snecma  | Ariane 4 | Booster | N2O4 / UH 25 | Gas generator |  | 750,000 |  | 826 | 92.59 |
Vulcain
HM-60 |  Europe  | Snecma  | Ariane 5 | 1st  | LH2 / LOX | Gas generator | 439[102]
326 (SL)[103] | 1,113,000[102]
773,200 (SL)[103] | 109[102] | 1,300[103] | 84.38 |
Vulcain 2 |  Europe  | Snecma  | Ariane 5 | 1st  | LH2 / LOX | Gas generator | 429[104]
318 (SL)[105] | 1,359,000[104]
939,500 (SL)[105] | 117.3[104] | 1,800[104] | 77.04 |
Waxwing  |  United Kingdom  | Bristol Aerojet  | Black Arrow  | Upper  |  | Solid fuel  | 278[106]
245 (SL) | 29,400
25,900 (SL) |  | 87 | 34.48 |

## See also

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

## References

1. ↑ 1.0 1.1 1.2 1.3 "In-Space Product Data Sheets". September 13, 2019. https://www.rocket.com/sites/default/files/documents/In-Space Data Sheets 9.13.19.pdf.
2. ↑ 2.0 2.1 "BE-3". https://www.blueorigin.com/engines/be-3.
3. ↑ Belam, Martin (2024-01-08). "Nasa Peregrine 1 launch: Vulcan Centaur rocket carrying Nasa moon lander lifts off in Florida – live updates" (in en-GB). the Guardian. ISSN 0261-3077. https://www.theguardian.com/science/live/2024/jan/08/nasa-peregrine-1-launch-rocket-moon-latest-news-updates-live.
4. ↑ "Blue Origin's BE-4 Engine". https://forum.nasaspaceflight.com/index.php?topic=39674.msg1504802#msg1504802.
5. ↑ Ferster, Warren (2014-09-17). "ULA To Invest in Blue Origin Engine as RD-180 Replacement". Space News. http://www.spacenews.com/article/launch-report/41901ula-to-invest-in-blue-origin-engine-as-rd-180-replacement. Retrieved 2014-09-19.
6. ↑ "BE-4". Blue Origin. http://www.blueorigin.com/media/press_release/united-launch-alliance-and-blue-origin-announce-partnership-to-develop-new. Retrieved 17 September 2014.
7. ↑ Berger, Eric (2016-03-09). "Behind the curtain: Ars goes inside Blue Origin's secretive rocket factory". Ars Technica. https://arstechnica.com/science/2016/03/behind-the-curtain-ars-goes-inside-blue-origins-secretive-rocket-factory/. Retrieved 2016-03-09.
8. ↑ "GSLV Launch Vehicle Information". http://www.spaceflight101.com/gslv-launch-vehicle-information.html. Retrieved 6 January 2014.
9. ↑ 9.0 9.1 "RS1" (in en-US). https://ablspacesystems.com/rs1/.
10. ↑ 10.0 10.1 10.2 10.3 "Engine-2" (in en-US). https://launcherspace.com/engine-2.
11. ↑ "NG Prop Catalog". 2020-12-10. https://www.northropgrumman.com/wp-content/uploads/NG-Propulsion-Products-Catalog.pdf#page=43.
12. ↑ 12.0 12.1 "Developing Vulcan Centaur". April 4, 2019. https://www.ulalaunch.com/docs/default-source/evolution/190408_ulapanel_all_compressed.pdf/.
13. ↑ "NG Prop Catalog". 2020-12-10. https://www.northropgrumman.com/wp-content/uploads/NG-Propulsion-Products-Catalog.pdf#page=44.
14. ↑ "The Engines" (in en-US). https://www.ursamajortechnologies.com/engines.
15. ↑ 15.0 15.1 Arizaga, Monica (2022-03-18). ""Helix" - public names RFA engine" (in en-US). https://www.rfa.space/helix-public-names-rfa-engine/.
16. ↑ Arizaga, Monica (2022-07-13). "RFA successfully hot fires Helix engine for a total of 74 seconds" (in en-US). https://www.rfa.space/rfa-successfully-hot-fires-helix-engine-for-a-total-of-74-seconds/.
17. ↑ 17.0 17.1 17.2 17.3 "HM-7 and HM-7B Rocket Engine - Thrust Chamber". Airbus Defence and Space. http://cs.astrium.eads.net/sp/launcher-propulsion/rocket-engines/hm7b-rocket-engine.html.
18. ↑ 18.0 18.1 Wade, Mark. "HM7-B". Encyclopedia Astronautica. http://www.astronautix.com/h/hm7-b.html. Retrieved 10 June 2017.
19. ↑ https://www.spaceintel101.com/post/south-korea-s-innospace-will-launch-brazilian-payload-on-inaugural-flight-from-alcântara
20. ↑ "innospacecorp on Twitter: "Very proud and excited as we get ready to test the world's largest LOx/Paraffin Hybrid rocket engine developed for a smallsat Launcher.The HyPER-15, a 150kN Hybrid rocket engine, is scheduled to test this month at our Geumsan Engine Test Facility. Keep an eye out for our updates!"" (in en). https://twitter.com/innospacecorp/status/1410563047266033669.
21. ↑ "LE-5B". Encyclopedia Astronautica. http://www.astronautix.com/engines/le5b.htm. Retrieved 13 January 2016.
22. ↑ 22.0 22.1 "LE-7A". Encyclopedia Astronautica. http://www.astronautix.com/engines/le7a.htm. Retrieved 13 January 2016.
23. ↑ "LE-9". https://www.jaxa.jp/press/2016/06/files/20160614_h3_01_j.pdf.
24. ↑ 24.0 24.1 24.2 24.3 "Launch-alpha" (in en-US). https://firefly.com/launch-alpha/.
25. ↑ 25.0 25.1 25.2 "Merlin 1D". SpaceX. http://www.spacex.com/news/2013/03/26/merlin-engines. Retrieved 26 February 2016.
26. ↑ "Evolution of the SpaceX Merlin engine". http://www.b14643.de/Spacerockets_2/United_States_1/Falcon-9/Merlin/index.htm.
27. ↑ "SpaceX Falcon 9 Product Page". http://www.spacex.com/falcon9. Retrieved 2015-11-01.
28. ↑ "SpaceX" (in en). http://www.spacex.com/.
29. ↑ 29.0 29.1 29.2 29.3 29.4 29.5 "Motore M10" (in Italian). Avio. https://www.avio.com/it/m-10.
30. ↑ "NK-33". Encyclopedia Astronautica. http://www.astronautix.com/engines/nk33.htm. Retrieved 30 January 2014.
31. ↑ 31.0 31.1 "VEGA: 1° stage - P80 Motor" (in en-US). http://www.avio.com/en/vega/vega/vega-1-stadio-p80-motor/.
32. ↑ 32.0 32.1 32.2 Press release: Successful first test firing for the P120C solid rocket motor for Ariane 6 and Vega-C
33. ↑ "PSLV-1". http://www.astronautix.com/engines/pslv1.htm. Retrieved 4 April 2014.
34. ↑ 34.0 34.1 "Spacex Raptor". NASA SpaceFlight. 7 March 2014. http://www.nasaspaceflight.com/2014/03/spacex-advances-drive-mars-rocket-raptor-power/. Retrieved 2 July 2015.
35. ↑ 35.0 35.1 "Sea level Raptor’s vacuum Isp is ~350 sec, but ~380 sec with larger vacuum-optimized nozzle" (in en-US). 2019-09-09. https://twitter.com/elonmusk/status/1171118891671490560.
36. ↑ 36.0 36.1 36.2 36.3 36.4 "Raptor V3 just achieved 350 bar chamber pressure (269 tons of thrust). Congrats to @SpaceX propulsion team! Starship Super Heavy Booster has 33 Raptors, so total thrust of 8877 tons or 19.5 million pounds." (in en-US). 2023-05-13. https://twitter.com/elonmusk/status/1657249739925258240.
37. ↑ 37.0 37.1 37.2 Tim Dodd (14 July 2022). "Raptor 1 VS Raptor 2: What's New // What's Different". https://www.youtube.com/watch?v=ALiNmzoo1_E.
38. ↑ 38.0 38.1 "Draft Environmental Assessment for the SpaceX Starship and Super Heavy Launch Vehicle at Kennedy Space Center (KSC)" (in en). Space Exploration Technologies Corporation. 1 August 2019. p. 250. https://netspublic.grc.nasa.gov/main/20190801_Final_DRAFT_EA_SpaceX_Starship.pdf. Retrieved 5 August 2019.
39. ↑ Elon Musk on Twitter: Max thrust version of Raptor should achieve true T/W > 170\. Target is 1.5 ton engine with >260 t-F. Max Isp version should achieve ~380 sec, but T/W probably <120 due to big nozzle. These are just guesses for now.
40. ↑ "RD-0124 Engine". KBKha. http://www.kbkha.ru/?p=8&cat=8&prod=51. Retrieved 7 January 2016.
41. ↑ "ГКНПЦ имени М.В.Хруничева | Жидкостный ракетный двигатель РД - 0146". http://www.khrunichev.ru/main.php?id=304.
42. ↑ 42.0 42.1 "RD-107A and RD-108A". NPO Energomash. http://www.npoenergomash.ru/eng/dejatelnost/engines/rd107/. Retrieved 30 June 2015.
43. ↑ "RD-171M". NPO Energomash. http://www.npoenergomash.ru/eng/dejatelnost/engines/rd171m/. Retrieved 30 June 2015.
44. ↑ "RD-180". NPO Energomash. http://www.npoenergomash.ru/eng/dejatelnost/engines/rd180/. Retrieved 30 June 2015.
45. ↑ "RD-191". NPO Energomash. http://www.npoenergomash.ru/eng/dejatelnost/engines/rd191/. Retrieved 30 June 2015.
46. ↑ "Универсальный ракетный двигатель РД-193. Мнение инженера-разработчика". Журнал «Новости космонавтики». http://novosti-kosmonavtiki.ru/mag/2013/1004/13840/.
47. ↑ "RD-276 "Comrade"". NPO Energomash. http://www.engine.space/eng/dejatelnost/engines/rd-276/. Retrieved 14 October 2019.
48. ↑ 48.0 48.1 "RD-801". https://www.yuzhnoye.com/en/technique/rocket-engines/steering/rd-801/.
49. ↑ "RD-810". https://www.yuzhnoye.com/en/technique/rocket-engines/steering/rd-810/.
50. ↑ "RD-861K". https://www.yuzhnoye.com/en/technique/rocket-engines/marching/rd-861k/.
51. ↑ "RD-870". https://www.yuzhnoye.com/en/technique/rocket-engines/steering/rd-870/.
52. ↑ 52.0 52.1 52.2 "RL10 Data Sheet-1". Feb 2016. https://www.rocket.com/files/aerojet/documents/Capabilities/PDFs/RL10 data sheet Feb 2016.pdf.
53. ↑ Aerojet Rocketdyne, RS-25 Engine (accessed July 22, 2014)
54. ↑ "RS-68A". www.rocket.com. https://www.rocket.com/space/liquid-engines/rs-68a. Retrieved 19 January 2020.
55. ↑ 55.0 55.1 "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.
56. ↑ 56.0 56.1 "LVM3". http://isro.org/launchers/lvm3. Retrieved 21 December 2014.
57. ↑ "ISRO Press Release: S200 First Static Test (S-200-ST-01)". http://www.isro.org/pressrelease/contents/2010/pdf/S200_STATIC_TEST-01.pdf.
58. ↑ "Isro successfully tests world's 3rd largest solid booster". dna. http://www.dnaindia.com/scitech/report_isro-successfully-tests-world-s-3rd-largest-solid-booster_1338945. Retrieved 4 October 2014.
59. ↑ "India to test world's third largest solid rocket booster". Science and Technology Section. The Hindu News Paper. 2009-12-07. http://www.thehindu.com/sci-tech/article61220.ece. Retrieved 2009-12-07.
60. ↑ "SLV-1". http://www.astronautix.com/engines/slv1.htm. Retrieved 4 April 2014.
61. ↑ "SRB-A3". Spaceflight101. http://spaceflight101.com/spacerockets/epsilon/. Retrieved 13 January 2016.
62. ↑ “天鹊”80吨液氧甲烷发动机100%推力100秒试车圆满成功
63. ↑ "Vinci". Encyclopedia Astronautica. http://www.astronautix.com/v/vinci.html. Retrieved 10 June 2017.
64. ↑ "Vinci® engine". Ariane. https://www.ariane.group/wp-content/uploads/2020/06/VINCI_2020_04_DS_EN_Eng_Web.pdf.
65. ↑ 65.00 65.01 65.02 65.03 65.04 65.05 65.06 65.07 65.08 65.09 65.10 "2.2 LM-3A Launch Vehicle". LM-3A Series Launch Vehicle User's Manual. Issue 2011. CASC. 2011. pp. 2–4. http://www.cgwic.com/launchservices/download/manual/Chapter 2 General Description.pdf. Retrieved 2016-01-16.
66. ↑ 孙纪国,郑孟伟,龚杰峰,陶瑞峰 (2022-01-15). "220tf补燃循环氢氧发动机研制进展" (in zh-hans). 《火箭推进》2022年02期. http://hjtjnew.paperopen.com/upload/html/m/202202002.html. Retrieved 2022-06-05.
67. ↑ 67.0 67.1 "VEGA C: 3° stage - zefiro 9" (in en-US). http://www.avio.com/en/vega/vega-c/vega-c-3-stadio-zefiro-9/.
68. ↑ 68.0 68.1 "VEGA: 2° stage - zefiro 23" (in en-US). http://www.avio.com/en/vega/vega/vega-2-stadio-zefiro-23/.
69. ↑ 69.0 69.1 "Zefiro 40 Motor Main Characteristics" (in en-US). https://www.avio.com/zefiro-40/.
70. ↑ 70.0 70.1 "Terran 1 Technical Specifications". http://www.relativityspace.com/terran.
71. ↑ "Aestus Rocket Engine". Airbus Defence and Space. http://cs.astrium.eads.net/sp/launcher-propulsion/rocket-engines/aestus-rocket-engine.html. Retrieved 29 January 2014.
72. ↑ "Aestus Rocket Engine". Airbus Defence and Space. http://cs.astrium.eads.net/sp/launcher-propulsion/rocket-engines/aestus-rs72-rocket-engine.html. Retrieved 29 January 2014.
73. ↑ 73.0 73.1 "Astra Space Rocket". https://www.spacelaunchreport.com/astra.html.
74. ↑ 74.0 74.1 "Astra Media Kit LV0006". 28 August 2021. https://astra.com/wp-content/uploads/2021/08/Astra_MediaKit_LV0006.pdf.
75. ↑ "Atlas V Solid Rocket Motor". http://www.rocket.com/atlas-v-solid-rocket-motor. Retrieved 2015-06-02.
76. ↑ "AR1 Engine". http://www.rocket.com/ar1-booster-engine.
77. ↑ Alternate Propulsion Subsystem Concepts NAS8-39210 DCN 1-1-PP-02147
78. ↑ "Gamma 2". Encyclopedia Astronautica. http://www.astronautix.com/engines/gamma2.htm. Retrieved 26 April 2013.
79. ↑ "Gamma 8". Encyclopedia Astronautica. http://www.astronautix.com/engines/gamma8.htm. Retrieved 26 April 2013.
80. ↑ Wade, Mark. "HM7-A". Encyclopedia Astronautica. http://www.astronautix.com/h/hm7-a.html. Retrieved 10 June 2017.
81. ↑ Wade, Mark. "J-2". Encyclopedia Astronautica. http://www.astronautix.com/j/j-2.html. Retrieved 23 December 2011.
82. ↑ "J-2X Engine". Pratt & Whitney Rocketdyne. http://www.pw.utc.com/products/pwr/propulsion_solutions/j-2x.asp. Retrieved 23 December 2011.
83. ↑ "LE-5". Encyclopedia Astronautica. http://www.astronautix.com/engines/le5.htm. Retrieved 13 January 2016.
84. ↑ "LE-5A". Encyclopedia Astronautica. http://www.astronautix.com/engines/le5a.htm. Retrieved 13 January 2016.
85. ↑ "LE-7". Encyclopedia Astronautica. http://www.astronautix.com/engines/le7.htm. Retrieved 13 January 2016.
86. ↑ 86.0 86.1 "Merlin section of Falcon 9 page". SpaceX. http://www.spacex.com/falcon9.php#merlin_engine. Retrieved 2012-10-16.
87. ↑ 87.0 87.1 "Falcon 9 Space Launch Report". SpaceLaunchReport. http://www.spacelaunchreport.com/falcon9.html. Retrieved 2015-11-01.
88. ↑ 88.0 88.1 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.
89. ↑ 89.0 89.1 "LauncherOne Service Guide". http://www.virgingalactic.com/assets/uploads/2014/11/VG_LauncherOne_ServiceGuide_v0.2_OSR.pdf.
90. ↑ 90.0 90.1 "P230". Encyclopedia Astronautica. http://www.astronautix.com/engines/p230.htm. Retrieved 27 December 2011.
91. ↑ "RD0120". KBKhA. http://www.kbkha.ru/?p=8&cat=8&prod=34.
92. ↑ "KVD1 Rocket Engine" (in ru). КБХМ им. A.M. Исаева. http://kbhmisaeva.ru/main.php?id=54.
93. ↑ 93.0 93.1 "RD-117". Liquid Propellant Rocket Engines. http://www.lpre.de/energomash/RD-107/index.htm. Retrieved 27 November 2012.
94. ↑ "RD-170". Encyclopedia Astronautica. http://www.astronautix.com/r/rd-170.html. Retrieved 24 September 2019.
95. ↑ "Antares 200 Series – Rockets". http://spaceflight101.com/spacerockets/antares-200-series/.
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. ↑ "SRB-A". Encyclopedia Astronautica. http://www.astronautix.com/engines/srba.htm. Retrieved 13 January 2016.
101. ↑ "UA1207". Encyclopedia Astronautica. http://www.astronautix.com/engines/ua1207.htm. Retrieved 27 December 2015.
102. ↑ 102.0 102.1 102.2 "Vulcain Astrium". Airbus Defence and Space. http://cs.astrium.eads.net/sp/launcher-propulsion/rocket-engines/vulcain-rocket-engine.html. Retrieved 27 December 2011.
103. ↑ 103.0 103.1 103.2 "Vulcain". Encyclopedia Astronautica. http://www.astronautix.com/v/vulcain.html. Retrieved 27 December 2011.
104. ↑ 104.0 104.1 104.2 104.3 "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.
105. ↑ 105.0 105.1 "Vulcain 2". Encyclopedia Astronautica. http://www.astronautix.com/v/vulcain2.html. Retrieved 27 December 2011.
106. ↑ "Black Arrow-3". Encyclopedia Astronautica. http://www.astronautix.com/b/blackarrow-3.html. Retrieved 26 April 2013.

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