Comparison of orbital rocket engines
Appearance
This page is an incomplete list of orbital rocket engine data and specifications.
Current, Upcoming, and In-Development rocket engines
[edit]Retired and canceled rocket engines
[edit]Engine | Origin | Designer | Vehicle | Use | Propellant | Power cycle | Specific impulse (s)[a] | Thrust (N)[a] | Chamber pressure (bar) | Mass (kg) | Thrust:weight ratio[e] | Oxidiser:fuel ratio |
---|---|---|---|---|---|---|---|---|---|---|---|---|
Aeon 1 | ![]() |
Relativity Space | Terran 1 | 1st | CH4 / LOX | Gas generator | 310 | 86,740 (SL)[67] | ||||
Aeon 1 Vacuum | ![]() |
Relativity Space | Terran 1 | 2nd | CH4 / LOX | Gas generator | 360 | 100,085 (SL)[67] | ||||
Aestus | ![]() |
Airbus Defence and Space | Ariane 5 G, G+, ES | Upper | N2O4 / MMH | Pressure-fed | 324[68] | 30,000 | 11 | 111 | 27.6 | 1.9 |
Aestus II | ![]() |
Airbus Defence and Space | Ariane 5 | Upper | N2O4 / MMH | Gas generator | 340[69] | 55,400 | 60 | 138 | 41.0 | 1.9 |
Aether | ![]() |
Astra Space | Rocket 3.3 | 2nd | RP-1/LOX[70] | Pressure-fed | 3,300[71] | |||||
AJ-60A | ![]() |
Aerojet | Atlas V | Booster | HTPB | Solid fuel | 275 | 1,270,000[72] | ||||
AJ-260-2 | ![]() |
Aerojet | S-I stage replacement (proposed) | 1st | PBAN | Solid fuel | 263 | 26,183,755 | 831,345 with fuel | |||
AR1 | ![]() |
Aerojet Rocketdyne | 1st | RP-1 / LOX | Staged, oxidizer-rich | 2,200,000 (SL)[73] | 2.72 | |||||
Delphin | ![]() |
Astra Space | Rocket 3.3 | 1st | RP-1/LOX[70] | Electric pump | 29,000[71] | 31 | ||||
F-1[f] | ![]() |
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[g][74] | ![]() |
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 | ![]() |
Bristol Siddeley | Black Arrow | 2nd | RP-1 / H2O2 | Staged, decomposition and combustion | 265[75] | 68,200 | 173 | 40.22 | 8 | |
Gamma 8 | ![]() |
Bristol Siddeley | Black Arrow | 1st | RP-1 / H2O2 | Staged, decomposition and combustion | 265[76] | 234,800 | 47.40 | 342 | 70.01 | 8 |
HM-7A | ![]() |
Snecma | Ariane 1 | 3rd | LH2 / LOX | Gas generator | 443[77] 308 (SL) |
61,700 | 30 | 149 | 42.2 | 5 |
HM-7B | ![]() |
Snecma | Ariane 2, 3, 4, 5 ECA | Upper | LH2 / LOX | Gas generator | 446[78] 310 (SL)[79] |
64,800[78] 43,600 (SL)[79] |
37[78] | 165[78] | 43.25 | 5 |
J-2 | ![]() |
Rocketdyne | Saturn V, IB | 2nd, 3rd | LH2 / LOX | Gas generator | 421[80] 200 (SL) |
1,033,100 486,200 (SL) |
52.6 | 1,438 | 73.18 | 5.5 |
J-2X | ![]() |
Pratt & Whitney Rocketdyne | SLS (proposed) | Upper | LH2 / LOX | Gas generator | 448[81] | 1,310,000 | 95 | 2,470 | 58.41 | 5.5–4.5 |
Kestrel | ![]() |
SpaceX | Falcon 1 | Upper | RP-1 / LOX | Pressure fed | 317 | 31,000 | 9.3 | 52 | 65 | |
LE-5 | ![]() |
Mitsubishi, NASDA | H-I | Upper | LH2 / LOX | Gas generator | 450[82] | 103,000 | 36.0 | 245 | 42.87 | 5.5 |
LE-5A | ![]() |
Mitsubishi, NASDA | H-II | Upper | LH2 / LOX | Expander, open | 452[83] | 121,500 | 40.0 | 242 | 51.19 | 5 |
LE-7 | ![]() |
Mitsubishi, NASDA | H-II | 1st | LH2 / LOX | Staged combustion | 446[84] | 1,078,000 843,500 (SL) |
127 | 1,714 | 64.13 | 5.9 |
M-1 | ![]() |
Aerojet | 1st, 2nd? | LH2 / LOX | Gas generator | 428 (SL) | 6,670,000 | 9,068 | 60 | |||
Merlin 1D | ![]() |
SpaceX | Falcon 9 v1.1 | 1st | RP-1 / LOX | Gas generator | 311[85] 282 (SL)[85] |
723,000 | 97 | 470 | 158 | 2.34 |
Merlin Vacuum 1C | ![]() |
SpaceX | Falcon 1, 9 | 2nd | RP-1 / LOX | Gas generator | 336[86] | 413,644[86] | 92 | |||
NewtonThree | ![]() |
Virgin Orbit | LauncherOne | Booster | RP-1 / LOX | Gas generator[87] | 266,893[88] | 70 | ||||
NewtonFour | ![]() |
Virgin Orbit | LauncherOne | 2nd | RP-1 / LOX | Gas generator[87] | 22,241[88] | |||||
P230 | ![]() |
Avio | Ariane 5 | Booster | HTPB | Solid fuel | 286[89] 259 (SL) |
6,996,000 5,860,000 (SL) |
69 | 269,000 with fuel[89] | ||
RD-0120 11Д122 |
![]() |
KBKhA | Energia | 1st | LH2 / LOX | Staged, fuel-rich | 455[90] | 1,962,000 1,526,000 (SL) |
219 | 3,450 | 57.80 | |
RD-8, 11D513 |
![]() |
Pivdenne/Pivdenmash | Zenit | 2nd vernier | RP-1 / LOX | Staged, oxidizer-rich | 342 | 78,450 | 77.47 | 356 | 2.4 | |
RD-56 (KVD-1) 11Д56У |
![]() |
KBKhM | GSLV Mk I | Upper | LH2 / LOX | Staged, fuel-rich | 462[91] | 69,626 | 55.9 | 282 | 25.17 | |
RD-117 11Д511 |
![]() |
NPO Energomash | Soyuz-U | 1st | RP-1 / LOX | Gas generator | 316[92] 253 (SL) |
978,000 778,648 (SL) |
54.2 | 1,100 | 72.18 | |
RD-118 11Д512 |
![]() |
NPO Energomash | Soyuz-U | 2nd | RP-1 / LOX | Gas generator | 314[92] 257 (SL) |
1,000,278 818,855 (SL) |
59.7 | 1,100 | 75.91 | |
RD-170[h]11Д521[93] | ![]() |
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 | ![]() |
NPO Energomash | Antares 200 | 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-264 11Д119 |
![]() |
NPO Energomash | Dnepr | 1st | N2O4 / UDMH | Staged, oxidizer-rich | 318[95] 293 (SL) |
4,521,000 | 206 | 3,600 | 128.15 | |
RD-270[i] 8Д420 |
![]() |
NPO Energomash | UR-700 (proposed), UR-900 (proposed) | 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 |
![]() |
NPO Energomash | Proton-M | 1st | N2O4 / UDMH | Staged, oxidizer-rich | 316[97] 287 (SL) |
1,831,882 1,671,053 (SL) |
160.0 | 1,070 | 171.2 | |
RD-854 8D612 |
![]() |
Pivdenne/Pivdenmash | R-36ORB | 3rd | N2O4 / UDMH | Gas generator | ||||||
RD-855 8D68M |
![]() |
Pivdenne/Pivdenmash | Tsyklon-2, -3, R-36 | 1st vernier | N2O4 / UDMH | Gas generator | 328,000 | 65.70 | 320 | 1.97 | ||
RD-856 8D69M |
![]() |
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 |
![]() |
Pivdenne/Pivdenmash | Tsyklon-2, -3 | 3rd | N2O4 / UDMH | Gas generator | 78,710 | 88.8 | 123 | 2.1 | ||
RD-864 15D177 |
![]() |
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 |
![]() |
Pivdenne/Pivdenmash | R-36M | 3rd | N2O4 / UDMH | Gas generator | 302.3–313 | 8,580–20,470 | 17–41 | 196 | 1.8 | |
RS-27A | ![]() |
Rocketdyne | Delta | 1st | RP-1 / LOX | Gas generator | 302[98] 255 (SL) |
1,054,200 | 49 | 1,091 | 102.5 | 2.245 |
RS-68A[j] | ![]() |
Rocketdyne | Delta IV, IV Heavy | 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] | ![]() |
Thiokol | Space Shuttle, Ares I | Booster | PBAN / APCP | Solid fuel | 268 | 14,000,000 12,500,000 (SL) |
590,000 with fuel |
|||
SRB-A | ![]() |
IHI Aerospace, JAXA | H-IIA | Booster | HTPB | Solid fuel | 280[100] | 2,250,000 | 76,400 with fuel | |||
UA1207 | ![]() |
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 | ![]() |
Snecma | Ariane 1 | 1st | N2O4 / UDMH | Gas generator | 690,000 611,200 (SL) |
776 | 90.67 | |||
Viking 2B | ![]() |
Snecma | Ariane 2, 3 | 1st | N2O4 / UH 25 | Gas generator | 643,000 (SL) | 776 | 84.5 | |||
Viking 4 | ![]() |
Snecma | Ariane 1 | 2nd | N2O4 / UDMH | Gas generator | 713,000 | 826 | 88 | |||
Viking 4B | ![]() |
Snecma | Ariane 2, 3, 4 | 2nd | N2O4 / UH 25 | Gas generator | 800,000 | 826 | 98.76 | |||
Viking 5C | ![]() |
Snecma | Ariane 4 | 1st | N2O4 / UH 25 | Gas generator | 758,000 678,000 (SL) |
826 | 93.57 | |||
Viking 6 | ![]() |
Snecma | Ariane 4 | Booster | N2O4 / UH 25 | Gas generator | 750,000 | 826 | 92.59 | |||
Vulcain HM-60 |
![]() |
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 | ![]() |
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 | ![]() |
Bristol Aerojet | Black Arrow | Upper | Solid fuel | 278[106] 245 (SL) |
29,400 25,900 (SL) |
87 | 34.48 |
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]- ^ a b c d At sea level if denoted SL, in vacuum otherwise
- ^ Weight is calculated at standard gravity.
- ^ Most powerful multi-chamber rocket engine in the world
- ^ Largest, most powerful solid-fuel rocket motor ever built
- ^ Weight is calculated at standard gravity.
- ^ Most powerful single-chamber liquid-fueled rocket engine ever developed
- ^ Tested but never flown
- ^ World's most powerful liquid fueled rocket engine
- ^ Tested but never flown
- ^ Most powerful hydrogen-fueled engine in the world
- ^ Largest solid-fuel rocket motor ever flown, and the first to be used for primary propulsion on human spaceflight missions
References
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