Comparison of orbital rocket engines

This page exposes an incomplete list of orbital rocket engines.

Legend for below table:   [under development] — [retired,canceled] — [operational,inactive]

Engine Origin Manufacturer Vehicle Stage Propellant Specific Impulse, Vac (s) Specific Impulse, SL (s) Thrust, Vac (N) Thrust, SL (N) Mass (kg) Thrust-to-weight ratio Combustion chamber pressure (bar) Status Engine
Vulcain[1][2]

HM-60

  Europe Snecma Ariane 5 1st LH2/LOX 439[2] 326[1] 1,113,000[2] 773,200[1] 1,300[1] 84.318[1] 109[2] Retired Vulcain
Vulcain 2[3][4]  Europe Snecma Ariane 5 1st LH2/LOX 429[4] 318[3] 1,359,000[4] 939,500[3] 1,800[3] 76.99?[note 1] 117.3[4] Operational Vulcain 2
P230[5]  Europe SNPE (Societe Nationale des Poudres et Explosifs) Ariane 5 Booster HTPB(68/18) 286[5] 259[5] 6,472,300[5] 5,861,300[5] 269,000 with fuel[5] Operational P230
HM7B[6][7]  Europe Snecma Ariane 5 ECA Upper LH2/LOX 446[7] 310[6] 64,800[7] 43,600[6] 165[7] 40.05?[note 2] 37[7] Operational HM7B
Vinci[8][9]  Europe Snecma Ariane 6 Upper LH2/LOX 465[8] 180,000[8] 280[9] 65.55[note 3] 60.8[8] Development Vinci
RD-180[10]  Russia NPO Energomash Atlas V
Atlas III		 1st RP-1/LOX 338.4[10] 311.9[10] 4,152,136[10] 3,826,555[10] 5,480[10] 71.2[note 4] 261.7[10] Operational RD-180
RD-191[11]  Russia NPO Energomash Angara 1st RP-1/LOX 337.5[11] 311.2[11] 2,084,894[11] 1,922,103[11] 2,200[11] 89.09[note 5] 262.6[11] Operational RD-191
RD-0124[12]

14Д23

  Russia TsSKB Progress Soyuz-2.1b
Soyuz-2-1v
Angara		 2nd,3rd RP-1/LOX 359[12] 294,300[12] 520[12] 57.7[note 6] 160[12] Operational RD-0124
NK-33-1 (AJ26-58)[13]

11Д111

  Soviet Union Kuznetsov Design Bureau
Aerojet		 Antares
Soyuz-2.1v		 1st RP-1/LOX 331[13] 1,638,000[13] 1,222[13] 136.8[13] 145[13] Operational NK-33-1 (AJ26-58)
Gamma 8[14]  UK Bristol Siddeley Black Arrow 1st H2O2/Kerosene 265[14] 234,800[14] 342[14] 70.01[14] 47.40[14] Retired Gamma 8
Gamma 2[15]  UK Bristol Siddeley Black Arrow 2nd H2O2/Kerosene 265[15] 68,200[15] 173[15] 40.22[15] Retired Gamma 2
Waxwing[16]  UK Bristol Aerojet Black Arrow Upper Solid 278[16] 29,400[16] 87[16] Retired Waxwing
Merlin 1C  United States SpaceX Falcon 9
Falcon 1		 1st,2nd RP-1/LOX 304[17] 266[18] 480,408[17] 422,581[17] 630 92[17] 67.7 Retired Merlin 1C
Merlin Vacuum 1C  United States SpaceX Falcon 9
Falcon 1		 2nd RP-1/LOX 336[18] 413,644[18] 92 Retired Merlin Vacuum 1C
Merlin 1D  United States SpaceX Falcon 9 v1.1 1st RP-1/LOX 311 [19] 282 [19] 723,000[20] 470[20] 158[20] 97 Retired Merlin 1D
Merlin 1D FT  United States SpaceX Falcon 9 v1.1 FT
Falcon Heavy		 1st RP-1/LOX 311 [19] 282 [19] 825,000[21] 470[20] 180[20] 97 Operational Merlin 1D FT
Merlin Vacuum 1D  United States SpaceX Falcon 9
Falcon Heavy		 2nd RP-1/LOX 348[22] 934,000[22] Operational Merlin Vacuum 1D
Raptor[23]  United States SpaceX 1st Methane/LOX[23] 363[23] 2,300,000[24] Development Raptor
RD-171M[25]

Most powerful liquid-fuel rocket engine in the world

  Russia NPO Energomash Zenit-3SL
Zenit-3SLB		 1st RP-1/LOX 337.2[25] 309.5[25] 7,904,160[25] 7,256,921[25] 9,300[25] 79.57[note 7] 250[25] Operational RD-171M
RD-107A[26]

14Д22

  Russia NPO Energomash Soyuz-FG
Soyuz-2		 1st RP-1/LOX 320.2[26] 263.3[26] 1,019,892[26] 839,449[26] 1,090[26] 78.53[note 8] 61.2[26] Operational RD-107A
RD-108A[26]

14Д21

  Russia NPO Energomash Soyuz-FG
Soyuz-2		 2nd RP-1/LOX 320.6[26] 257.7[26] 921,825[26] 792,377[26] 1,075[26] 75.16[note 9] 55.5[26] Operational RD-108A
RD-117[27]

11Д511

  Soviet Union NPO Energomash Soyuz-U 1st RP-1/LOX 316[27] 253[27] 978,000[28] 778,648[27] 1,100[27] 72.18[note 10] 54.2[27] Operational RD-117
RD-118[27]

11Д512

  Soviet Union NPO Energomash Soyuz-U 2nd RP-1/LOX 314[27] 257[27] 1,000,278[27] 818,855[27] 1,100[27] 75.91[note 11] 59.7[27] Operational RD-118
LE-5  Japan Mitsubishi Heavy Industries
NASDA		 H-I Upper LH2/LOX 450[29] 103,000[29] 245[29] 42.87[note 12] 36.0[29] Retired LE-5
LE-5A  Japan Mitsubishi Heavy Industries
NASDA		 H-II Upper LH2/LOX 452[30] 121,500[30] 242[30] 51.19[note 13] 40.0[30] Retired LE-5A
LE-5B  Japan Mitsubishi Heavy Industries
JAXA		 H-IIA
H-IIB		 Upper LH2/LOX 447[31] 137,000[31] 269[31] 51.93[note 14] 36.0[31] Operational LE-5B
LE-7  Japan Mitsubishi Heavy Industries
NASDA		 H-II 1st LH2/LOX 446[32] 1,078,000[32] 843,500[32] 1,714[32] 64.13[32] 127[32] Retired LE-7
LE-7A  Japan Mitsubishi Heavy Industries
JAXA		 H-IIA
H-IIB		 1st LH2/LOX 438[33] 338[33] 1,098,000[33] 1,800[33] 62.2[note 15] 121[33] Operational LE-7A
SRB-A  Japan IHI Aerospace
JAXA		 H-IIA Booster HTPB 280[34] 2,250,000[34] 76,400 with fuel[34] 118[34] Operational SRB-A
SRB-A3  Japan IHI Aerospace
JAXA		 H-IIB Booster BP-207J[35] 283.6[35] 2,305,000[35] 2,150,000[35] 76,600 with fuel[35] 111[35] Operational SRB-A3
RS-68A[36]

Most powerful hydrogen-fueled engine in the world

  United States Pratt & Whitney Rocketdyne Delta IV
Delta IV Heavy		 1st LH2/LOX 414[36] 3,560,000[36] 3,137,000[36] 6,747[36] 53.80[note 16] 196[36] Operational RS-68A
Atlas V SRB  United States Aerojet Atlas V Booster Solid 275[37] 1,270,000[37] Operational Atlas V SRB
F-1

Most powerful single-chamber liquid-fueled rocket engine ever developed

  United States Rocketdyne Saturn V 1st RP-1/LOX 263 7,770,000 6,770,000 8,391 82.27?[note 17] 70 Retired F-1
RS-25 - SSME  United States Pratt & Whitney Rocketdyne Space Shuttle 1st LH2/LOX 452.3 2,279,000 3,526 53.79[note 18] 206.4 Inactive since STS-135 RS-25
Space Shuttle Solid Rocket Booster

Largest solid-fuel rocket motor ever flown, and the first to be used for primary propulsion on human spaceflight missions

  United States Thiokol Space Shuttle
Ares I		 Booster APCP 268 14,000,000 12,500,000 590,000
with fuel		 Inactive since STS-135 Space Shuttle Solid Rocket Booster
UA1207[38]  United States United Technologies Titan IV Booster PBAN 272 245 7,116,000 6,410,400 319,330
with fuel		 Retired UA1207
J-2[39]  United States Rocketdyne Saturn V
Saturn IB		 2nd, 3rd LH2/LOX 421 1,033,100 1,438 73.18 30 Retired J-2
J-2X[40][41]  United States Pratt & Whitney Rocketdyne Space Launch System Upper LH2/LOX 448 1,310,000 2,430[41] 54.97?[note 19] 30 Development J-2X
RL-10B-2[42][43]  United States Pratt & Whitney Rocketdyne Delta III
Delta IV		 Upper LH2/LOX 462 109,890 277 41 44 Operational RL-10B-2
RL-10A-4-2[43][44]  United States Pratt & Whitney Rocketdyne Atlas V Upper LH2/LOX 451 99,100 167 59 39 Operational RL-10A-4-2
NSTAR[45][46]

First ever ion engine used as a main engine on an operational science spacecraft

  United States Hughes Electron Dynamics
Boeing		 Deep Space 1
Dawn		 Ion thruster Xenon 3,100 @2.3 kW 0.0920 @2.3 kW 8.2 Operational NSTAR
HiPEP

Most efficient inert gas ion thruster ever built

  United States NASA Jupiter Icy Moons Orbiter Ion thruster Xenon 9,620 @39.3 kW 0.670 @39.3 kW Canceled HiPEP
NEXT  United States NASA Ion thruster Xenon 4,100 @6.9 kW 0.236 @6.9 kW Development NEXT
VASIMR  United States Ad Astra Rocket Company Electro-magnetic thruster Argon 5,000 @200 kW 5.7 @200 kW Development VASIMR
PPS-1350  Russia
 Europe		 OKB Fakel
Snecma		 SMART-1 Hall thruster Xenon 1,650 @1.5 kW 0.088 @1.5 kW 5.3 Operational PPS-1350
SPT-100  Russia OKB Fakel LS-1300 satellites Hall thruster Xenon 1,500 @1.35 kW 0.083 @1.35 kW 3.5 Operational SPT-100
Boeing 601HP

First ever ion engine used as a main engine on an operational commercial satellite (PAS-5)

  United States Boeing Boeing 601HP satellites Ion thruster Xenon 2,568 @0.5 kW 0.018 @0.5 kW Operational Boeing 601HP
Boeing 702  United States Boeing Boeing 702 satellites Ion thruster Xenon 3,800 @4.5 kW 0.165 @4.5 kW Operational Boeing 702
KVD-1[47]

11Д56У

  Russia KBKhM GSLV Mk I Upper LH2/LOX 462[47] 69,626[47] 282[47] 25.17 55.9 Inactive KVD-1
CE-7.5[48][49]  India ISRO GSLV Mk II Upper LH2/LOX 454[49] 73,550[48] 445[49] 16.85?[note 20] 58 Operational CE-7.5
PSLV-1[50]  India ISRO PSLV 1st HTPB 269[50] 486,000[50] 160,200[50] 58[50] Operational PSLV-1
SLV-1[51]  India ISRO PSLV Booster HTPB 253[51] 502,600[51] 10,800[51] 43[51] Operational SLV-1
S200[52]  India ISRO LVM3 Booster HTPB 274.5[52] 5,150,000[53][54]

[55]

 207,000[52] Operational S200
RD-264[27]

11Д119

  Soviet Union NPO Energomash Dnepr-1 1st N2O4/UDMH 318.4[27] 293.3[27] 4,511,059[27] 4,158,020[27] 3,600[27] 117.77[note 21] 210[27] Operational RD-264
YF-21C  China CASC Long March 2,3 1st N2O4/UDMH 260.7[56] 2,961,600[56] Operational YF-21C
YF-24E  China CASC Long March 2,3 2nd N2O4/UDMH 298.0[56] 742,000[56] Operational YF-24E
YF-75  China CALT Long March 3 3rd LH2/LOX 438.0[56] 167,170[56] Operational YF-75
RD-275M[57]

14Д14М

  Russia NPO Energomash Proton-M 1st N2O4/UDMH 315.8[57] 288[57] 1,831,882[57] 1,671,053[57] 1,070[57] 159.25[note 22] 165.2[57] Operational RD-275M
RD-0120[58]

11Д122

  Soviet Union KBKhA Energia 1st LH2/LOX 455[58] 1,962,000[58] 3,450[58] 57.80 219 Retired RD-0120
RD-193[59][60]  Russia NPO Energomash Soyuz-2.1v 1st RP-1/LOX 337.5[60] 311.2[60] 2,084,894[60] 1,922,103[60] 1,900[59][60] 103.15[note 23] Development RD-193
RD-181  Russia NPO Energomash Antares 1st RP-1/LOX 337.5 Development RD-181
Aestus[61]  Europe Airbus Defence and Space Ariane 5 ES Upper N2O4/MMH 324[61] 30,000[61] 111[61] 27.6?[note 24] 11[61] Operational Aestus
Aestus II[62]  Europe Airbus Defence and Space Ariane 5 Upper N2O4/MMH 340[62] 55,400[62] 138[62] 40.9?[note 25] 60[62] Development Aestus II
BE-3  United States Blue Origin New Shepard 1st LH2/LOX Unknown 490,000 Operational BE-3
BE-4[63][64]  United States Blue Origin Atlas V
Vulcan		 1st Methane/LOX Unknown 2,400,000[63][64] Development BE-4
SLS Solid Rocket Booster

Largest, most powerful solid-fuel rocket motor ever built

  United States Orbital ATK SLS Booster PBAN 267 16,000,000 730,000
with fuel		 Development SLS Solid Rocket Booster

See also

References

  1. 1 2 3 4 5 "Vulcain". Encyclopedia Astronautica. Retrieved 27 December 2011.
  2. 1 2 3 4 EADS Astrium. "Vulcain Astrium". Airbus Defence and Space. Retrieved 27 December 2011.
  3. 1 2 3 4 "Vulcain 2". Encyclopedia Astronautica. Retrieved 27 December 2011.
  4. 1 2 3 4 EADS Astrium. "Vulcain 2 Astrium". Airbus Defence and Space. Retrieved 29 September 2015.
  5. 1 2 3 4 5 6 "P230". Encyclopedia Astronautica. Retrieved 27 December 2011.
  6. 1 2 3 "HM7-B". Encyclopedia Astronautica. Retrieved 27 April 2012.
  7. 1 2 3 4 5 EADS Astrium. "HM7-B Astrium". Airbus Defence and Space. Retrieved 1 November 2015.
  8. 1 2 3 4 EADS Astrium. "Vinci Astrium". Airbus Defence and Space. Retrieved 29 September 2015.
  9. 1 2 "Vinci". Encyclopedia Astronautica. Retrieved 1 November 2015.
  10. 1 2 3 4 5 6 7 "RD-180". NPO Energomash. Retrieved 30 June 2015.
  11. 1 2 3 4 5 6 7 "RD-191". NPO Energomash. Retrieved 30 June 2015.
  12. 1 2 3 4 5 "RD-0124 Engine". KBKha. Retrieved 7 January 2016.
  13. 1 2 3 4 5 6 "NK-33". Encyclopedia Astronautica. Archived from the original on 30 January 2014. Retrieved 30 January 2014.
  14. 1 2 3 4 5 6 "Gamma 8". Encyclopedia Astronautica. Archived from the original on 26 April 2013. Retrieved 26 April 2013.
  15. 1 2 3 4 5 "Gamma 2". Encyclopedia Astronautica. Archived from the original on 26 April 2013. Retrieved 26 April 2013.
  16. 1 2 3 4 "Black Arrow-3". Encyclopedia Astronautica. Archived from the original on 26 April 2013. Retrieved 26 April 2013.
  17. 1 2 3 4 "Updates: December 2007". SpaceX. Archived from the original on 2008-08-08.
  18. 1 2 3 "Falcon 9 Space Launch Report". SpaceLaunchReport. Retrieved 2015-11-01.
  19. 1 2 3 4 "Merlin section of Falcon 9 page". SpaceX. Archived from the original on 2013-07-15. Retrieved 2012-10-16.
  20. 1 2 3 4 5 "Is SpaceX's Merlin 1D's thrust-to-weight ratio of 150+ believable? - Quora". www.quora.com. Retrieved 2015-12-11.
  21. ↑ "Merlin 1D". SpaceX. Retrieved 1 November 2015.
  22. 1 2 "SpaceX Falcon 9 Product Page". Retrieved 2015-11-01.
  23. 1 2 3 "Spacex Raptor". NASA SpaceFlight. 7 March 2014. Retrieved 2 July 2015.
  24. ↑ Musk, Elon. "I am Elon Musk, CEO/CTO of a rocket company, AMA!". reddit.com. Retrieved 2015-06-01. Thrust to weight is optimizing for a surprisingly low thrust level, even when accounting for the added mass of plumbing and structure for many engines. Looks like a little over 230 metric tons (~500 klbf) of thrust per engine, but we will have a lot of them :)
  25. 1 2 3 4 5 6 7 "RD-171M". NPO Energomash. Retrieved 30 June 2015.
  26. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 "RD-107A and RD-108A". NPO Energomash. Retrieved 30 June 2015.
  27. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 "NPO Energomash Engines". NPO Energomash. Retrieved 30 June 2015.
  28. ↑ "RD-117". lpre.de. Archived from the original on 27 November 2012. Retrieved 27 November 2012.
  29. 1 2 3 4 "LE-5". Encyclopedia Astronautica. Retrieved 13 January 2016.
  30. 1 2 3 4 "LE-5A". Encyclopedia Astronautica. Retrieved 13 January 2016.
  31. 1 2 3 4 "LE-5B". Encyclopedia Astronautica. Retrieved 13 January 2016.
  32. 1 2 3 4 5 6 "LE-7". Encyclopedia Astronautica. Retrieved 13 January 2016.
  33. 1 2 3 4 5 "LE-7A". Encyclopedia Astronautica. Retrieved 13 January 2016.
  34. 1 2 3 4 "SRB-A". Encyclopedia Astronautica. Retrieved 13 January 2016.
  35. 1 2 3 4 5 6 "SRB-A3". Spaceflight101. Retrieved 13 January 2016.
  36. 1 2 3 4 5 6 "RS-68A - Delta IV Heavy". Spaceflight101.com. Retrieved 2 November 2015.
  37. 1 2 "Atlas V Solid Rocket Motor". Aerojet Rocketdyne. Retrieved 2015-06-02.
  38. ↑ "UA1207". Encyclopedia Astronautica. Archived from the original on 27 December 2015. Retrieved 27 December 2015.
  39. ↑ "J-2". Encyclopedia Astronautica. Archived from the original on 23 December 2011. Retrieved 23 December 2011.
  40. ↑ "J-2X Engine". Pratt & Whitney Rocketdyne. Archived from the original on 23 December 2011. Retrieved 23 December 2011.
  41. 1 2 "J-2X". Encyclopedia Astronautica. Archived from the original on 23 December 2011. Retrieved 23 December 2011.
  42. ↑ "RL-10B-2". Encyclopedia Astronautica. 23 December 2011. Archived from the original on 23 December 2011.
  43. 1 2 "RL-10 - Specifications". Spaceandtech. 23 December 2011. Archived from the original on 23 December 2011.
  44. ↑ "RL-10A-4-2". Encyclopedia Astronautica. 23 December 2011. Archived from the original on 23 December 2011.
  45. ↑ Sovey, J. S., Rawlin, V. K., and Patterson, M. J. (May–June 2001). "Ion Propulsion Development Projects in U. S.: Space Electric Rocket Test 1 to Deep Space 1.". Journal of Propulsion and Power 17 (3): 517–526.
  46. ↑ "Hughes' Ion Engine Serving as Primary Propulsion to NASA's Deep Space 1". www.boeing.com. 24 December 2011. Archived from the original on 24 December 2011.
  47. 1 2 3 4 "KVD1 Rocket Engine" Двигатель КВД1 (in Russian). КБХМ им. A.M. Исаева.
  48. 1 2 "Indigenous Cryogenic Engine and Stage". Retrieved 6 January 2014.
  49. 1 2 3 "GSLV Launch Vehicle Information". Retrieved 6 January 2014.
  50. 1 2 3 4 5 "PSLV-1". Retrieved 4 April 2014.
  51. 1 2 3 4 5 "SLV-1". Retrieved 4 April 2014.
  52. 1 2 3 "LVM3". Retrieved 21 December 2014.
  53. ↑ ISRO Press Release: S200 First Static Test (S-200-ST-01)
  54. ↑ "Isro successfully tests world's 3rd largest solid booster". dna. Retrieved 4 October 2014.
  55. ↑ "India to test world's third largest solid rocket booster". Science and Technology Section. The Hindu News Paper. 2009-12-07. Retrieved 2009-12-07.
  56. 1 2 3 4 5 6 "2.2 LM-3A Launch Vehicle". LM-3A Series Launch Vehicle User's Manual. Issue 2011 (pdf). CASC. 2011. p. 2–4. Retrieved 2016-01-16.
  57. 1 2 3 4 5 6 7 "RD-253 and RD-275M". NPO Energomash. Retrieved 30 June 2015.
  58. 1 2 3 4 "RD0120". KBKhA.
  59. 1 2 "Energomash Test Fires New RD-193 Engine". parabolicarc.com.
  60. 1 2 3 4 5 6 "Универсальный ракетный двигатель РД-193. Мнение инженера-разработчика". Журнал «Новости космонавтики».
  61. 1 2 3 4 5 "Aestus Rocket Engine". Airbus Defence and Space. Archived from the original on 29 January 2014. Retrieved 29 January 2014.
  62. 1 2 3 4 5 "Aestus Rocket Engine". Airbus Defence and Space. Archived from the original on 29 January 2014. Retrieved 29 January 2014.
  63. 1 2 Ferster, Warren (2014-09-17). "ULA To Invest in Blue Origin Engine as RD-180 Replacement". Space News. Retrieved 2014-09-19.
  64. 1 2 "BE-4". Blue Origin. Archived from the original on 17 September 2014. Retrieved 17 September 2014.

Notes

This article is issued from Wikipedia - version of the Tuesday, February 02, 2016. The text is available under the Creative Commons Attribution/Share Alike but additional terms may apply for the media files.