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BT-4 (rocket engine)

March 06, 2023

The BT-4 is a pressure-fed liquid rocket engine designed and manufactured by IHI Aerospace of Japan. It was originally developed for the LUNAR-A project, but it has been used as a liquid apogee engine in some geostationary communications satellite based on the Lockheed Martin A2100 and GEOStar-2 satellite buses. It has also been used on the HTV and Cygnus automated cargo spacecraft.

BT-4
Country of originJapan
DesignerIHI Aerospace
Associated LVHTV, Cygnus
StatusIn production
Liquid-fuel engine
PropellantN2O4 / Hydrazine
CyclePressure fed
Configuration
Chamber1
Performance
Thrust, vacuum500 N (110 lbf)
Dimensions
Length80 cm (31 in)
Dry weight4 kg (8.8 lb)

History

During the 1970s, Ishikawajima-Harima Heavy Industries had built under license the Rocketdyne MB-3 for the N-I rocket, for which it had also developed the second stage attitude control system.[1][2] In the 1980s it also developed the thrusters for ETS-4 (Kiku-3), the first to be built in Japan. In 2000 it acquired and merged with the aerospace division of Nissan and became IHI Aerospace.[2]

IHI Aerospace started developing the BT-4 for the later cancelled LUNAR-A mission to the moon. While the mission was cancelled, the thruster has seen success as a liquid apogee engine on the Lockheed Martin A2100 and Orbital ATK GEOStar-2 platforms.[3] Two other Orbital ATK products that use the BT-4 due to their leverage of the GEOStar-2 platform are the Cygnus spacecraft and the Antares Bi-propellant Third Stage (BTS).[4][5][6][7][8][9]

The use on the A2100 platform has allowed IHI to export the BT-4 even to American military programs such programs as the MUOS and AEHF.[10][11][12][13][14]

On March 9, 2006, IHI Aerospace announced that the AEHF-2 BT-4 engine had successfully performed its mission, unlike AEHF-1's.[14][15][16] On November 29, 2010 IHI Aerospace announced that it had received and order from Lockheed Martin of four BT-4 engines for AEHF-4, MUOS-4, MUOS-5 and Vinasat-2. With this order, it achieved its 100th-unit foreign engine export since it started selling abroad in 1999.[17][18]

For the HTV project, IHI developed a new version, the HBT-5, which enabled them to replace the American R-4D from the third flight onward.[19][20]

On October 3, 2013, with the successful berthing of the Cygnus Orb-D1 mission, IHI announced that the propulsion was based on their 500N Delta-Velocity Engines.[21]

In January 2018, a BT-4 kick motor was used on the GovSat-1 geosynchronous commsat flight.[22]

Versions

The BT-4 is a family that has been used as liquid apogee engine, orbital maneuvering engine and as a thruster. Known variations:

  • BT-4 (Cygnus): Used mainly as thruster, it burns MMH/N2O4 with a thrust of 450 N (100 lbf). It weighs 4 kg (8.8 lb) and is 65 cm (26 in) tall.[9][10]
  • BT-4 (450N): Used mainly as LAE, it burns Hydrazine/N2O4 in a 1.69 O/F ratio. It has a thrust of 450 N (100 lbf), a specific impulse of 329 s (3.23 km/s) and an input pressure of 1.62 MPa (235 psi). As of 2014, it had a demonstrated life of 32,850 seconds.[18]
  • BT-4 (500N): Used mainly as LAE, it burns Hydrazine/N2O4 with a thrust of 500 N (110 lbf), a specific impulse of 329 s (3.23 km/s). It weighs 4 kg (8.8 lb) and is 80 cm (31 in) tall.[14]
  • 490N MON Thruster: Burns MMH/MON-3 with a 478 N (107 lbf) nominal thrust, a specific impulse of 316 s (3.10 km/s) and an inlet pressure of 1.72 MPa (249 psi). As of 2014, it had a demonstrated life of 15,000 seconds.[18]
  • HBT-5: Developed for the HTV to crew-rated standards, it burns MMH/MON-3, and has a thrust of 500 N (110 lbf). Used in HTV-3 and since HTV-5 onward.[19][23]
  • SELENE OME: Based on the DRTS Liquid apogee engine, the SELENE Orbital Maneuvering Engine burned a Hydrazine/MON-3 mixture. It had a thrust of 547 ± 54 N (123 ± 12 lbf) and a specific impulse of 319.8 ± 5.1 s (3.136 ± 0.050 km/s) with an input pressure of 1.77 MPa (257 psi).[24][25]

References

  1. ^ Wade, Mark. . Astronautix.com. Archived from the original on September 15, 2016. Retrieved 2016-08-29.
  2. ^ a b IHI Aerospace. "IHI Corporate Profile" (PDF). pp. 6–7. (PDF) from the original on 2022-04-17. Retrieved 2016-08-29.
  3. ^ Krebs, Gunter Dirk (2016-04-17). "Lunar A". Gunter's Space Page. Retrieved 2016-08-29.
  4. ^ Krebs, Gunter Dirk (2016-04-17). "Cygnus-PCM". Gunter's Space Page. Retrieved 2016-08-29.
  5. ^ Krebs, Gunter Dirk (2016-08-19). "Cygnus-PCM (enhanced)". Gunter's Space Page. Retrieved 2016-08-29.
  6. ^ Krebs, Gunter Dirk (2016-08-12). "Antares (Taurus-2)". Gunter's Space Page. Retrieved 2016-08-29.
  7. ^ Brügge, Norbert. "Antares, Propulsion". B14643.DE. Retrieved 2015-08-29.
  8. ^ "Antares Fact Sheet" (PDF). Orbital ATK. Retrieved 2016-08-29.
  9. ^ a b . eoPortal Directory. Archived from the original on 2016-08-29. Retrieved 2016-08-29.
  10. ^ a b DeSantis, Dylan. "Satellite Thruster Propulsion-H2O2 Bipropellant Comparison with Existing Alternatives" (PDF). The Ohio State University. Retrieved 2016-08-29.
  11. ^ Wade, Mark. . Astronautix.com. Archived from the original on September 15, 2016. Retrieved 2016-08-29.
  12. ^ Krebs, Gunter Dirk (2016-06-24). "MUOS 1, 2, 3, 4, 5". Gunter's Space Page. Retrieved 2016-08-29.
  13. ^ Krebs, Gunter Dirk (2016-06-24). "AEHF 1, 2, 3, 4, 5, 6". Gunter's Space Page. Retrieved 2016-08-29.
  14. ^ a b c [Success in two successive flights for the engine with world's best performance] (in Japanese). IHI Aerospace. March 9, 2006. Archived from the original on 2010-09-24. Retrieved 2016-08-29.
  15. ^ Krebs, Gunter Dirk (2016-08-05). "OSC → Orbital ATK: StarBus → Star-2 → GeoStar-2". Gunter's Space Page. Retrieved 2016-08-29.
  16. ^ Krebs, Gunter Dirk (2016-04-17). "Telkom 2". Gunter's Space Page. Retrieved 2016-08-29.
  17. ^ . IHI Aerospace. November 29, 2010. Archived from the original on 2016-08-29. Retrieved 2016-08-29.
  18. ^ a b c (PDF). IHI Aerospace. December 2014. Archived from the original (PDF) on 2016-08-29. Retrieved 2016-08-29.
  19. ^ a b IHI Aerospace. "IHI Corporate Profile" (PDF). pp. 15–16. (PDF) from the original on 2022-04-17. Retrieved 2016-08-29.
  20. ^ Krebs, Gunter Dirk (2016-08-24). "HTV 1, ..., 9 (Kounotori 1, ..., 9)". Gunter's Space Page. Retrieved 2016-08-29.
  21. ^ . IHI Aerospace. October 3, 2013. Archived from the original on 2016-08-29. Retrieved 2016-08-29.
  22. ^ https://www.nasaspaceflight.com/2018/01/spacex-govsat-1-falcon-9-launch/
  23. ^ (PDF). JAXA. August 2, 2013. Archived from the original (PDF) on 2016-08-29. Retrieved 2016-08-29.
  24. ^ "On-orbit operation result of "KAGUYA" Lunar Explorer propulsion subsystem" (PDF). JAXA. 2008. Retrieved 2016-08-29.
  25. ^ Ideo Masuda (JAXA); Hideshi Kagawa (JAXA); Daisuke Goto (JAXA); Hiroyuki Minamino (JAXA); Kenichi Kajiwara (JAXA); Yoshihiro Kishino (IHI Aerospace); Masayuki Tamura (IHI Aerospace); Mamoru Takahashi (IHI Aerospace); Yosuke Iwayama (NEC Toshiba Space Systems); Shingo Ikegami (NEC Corporation); Makoto Miyata (NEC Corporation). (PDF). Archived from the original (PDF) on 2016-12-21. Retrieved 2016-08-29.

March 06, 2023
rocket, engine, pressure, liquid, rocket, engine, designed, manufactured, aerospace, japan, originally, developed, lunar, project, been, used, liquid, apogee, engine, some, geostationary, communications, satellite, based, lockheed, martin, a2100, geostar, sate. The BT 4 is a pressure fed liquid rocket engine designed and manufactured by IHI Aerospace of Japan It was originally developed for the LUNAR A project but it has been used as a liquid apogee engine in some geostationary communications satellite based on the Lockheed Martin A2100 and GEOStar 2 satellite buses It has also been used on the HTV and Cygnus automated cargo spacecraft BT 4Country of originJapanDesignerIHI AerospaceAssociated LVHTV CygnusStatusIn productionLiquid fuel enginePropellantN2O4 HydrazineCyclePressure fedConfigurationChamber1PerformanceThrust vacuum500 N 110 lbf DimensionsLength80 cm 31 in Dry weight4 kg 8 8 lb History EditDuring the 1970s Ishikawajima Harima Heavy Industries had built under license the Rocketdyne MB 3 for the N I rocket for which it had also developed the second stage attitude control system 1 2 In the 1980s it also developed the thrusters for ETS 4 Kiku 3 the first to be built in Japan In 2000 it acquired and merged with the aerospace division of Nissan and became IHI Aerospace 2 IHI Aerospace started developing the BT 4 for the later cancelled LUNAR A mission to the moon While the mission was cancelled the thruster has seen success as a liquid apogee engine on the Lockheed Martin A2100 and Orbital ATK GEOStar 2 platforms 3 Two other Orbital ATK products that use the BT 4 due to their leverage of the GEOStar 2 platform are the Cygnus spacecraft and the Antares Bi propellant Third Stage BTS 4 5 6 7 8 9 The use on the A2100 platform has allowed IHI to export the BT 4 even to American military programs such programs as the MUOS and AEHF 10 11 12 13 14 On March 9 2006 IHI Aerospace announced that the AEHF 2 BT 4 engine had successfully performed its mission unlike AEHF 1 s 14 15 16 On November 29 2010 IHI Aerospace announced that it had received and order from Lockheed Martin of four BT 4 engines for AEHF 4 MUOS 4 MUOS 5 and Vinasat 2 With this order it achieved its 100th unit foreign engine export since it started selling abroad in 1999 17 18 For the HTV project IHI developed a new version the HBT 5 which enabled them to replace the American R 4D from the third flight onward 19 20 On October 3 2013 with the successful berthing of the Cygnus Orb D1 mission IHI announced that the propulsion was based on their 500N Delta Velocity Engines 21 In January 2018 a BT 4 kick motor was used on the GovSat 1 geosynchronous commsat flight 22 Versions EditThe BT 4 is a family that has been used as liquid apogee engine orbital maneuvering engine and as a thruster Known variations BT 4 Cygnus Used mainly as thruster it burns MMH N2O4 with a thrust of 450 N 100 lbf It weighs 4 kg 8 8 lb and is 65 cm 26 in tall 9 10 BT 4 450N Used mainly as LAE it burns Hydrazine N2O4 in a 1 69 O F ratio It has a thrust of 450 N 100 lbf a specific impulse of 329 s 3 23 km s and an input pressure of 1 62 MPa 235 psi As of 2014 it had a demonstrated life of 32 850 seconds 18 BT 4 500N Used mainly as LAE it burns Hydrazine N2O4 with a thrust of 500 N 110 lbf a specific impulse of 329 s 3 23 km s It weighs 4 kg 8 8 lb and is 80 cm 31 in tall 14 490N MON Thruster Burns MMH MON 3 with a 478 N 107 lbf nominal thrust a specific impulse of 316 s 3 10 km s and an inlet pressure of 1 72 MPa 249 psi As of 2014 it had a demonstrated life of 15 000 seconds 18 HBT 5 Developed for the HTV to crew rated standards it burns MMH MON 3 and has a thrust of 500 N 110 lbf Used in HTV 3 and since HTV 5 onward 19 23 SELENE OME Based on the DRTS Liquid apogee engine the SELENE Orbital Maneuvering Engine burned a Hydrazine MON 3 mixture It had a thrust of 547 54 N 123 12 lbf and a specific impulse of 319 8 5 1 s 3 136 0 050 km s with an input pressure of 1 77 MPa 257 psi 24 25 References Edit Wade Mark MB 3 3 Astronautix com Archived from the original on September 15 2016 Retrieved 2016 08 29 a b IHI Aerospace IHI Corporate Profile PDF pp 6 7 Archived PDF from the original on 2022 04 17 Retrieved 2016 08 29 Krebs Gunter Dirk 2016 04 17 Lunar A Gunter s Space Page Retrieved 2016 08 29 Krebs Gunter Dirk 2016 04 17 Cygnus PCM Gunter s Space Page Retrieved 2016 08 29 Krebs Gunter Dirk 2016 08 19 Cygnus PCM enhanced Gunter s Space Page Retrieved 2016 08 29 Krebs Gunter Dirk 2016 08 12 Antares Taurus 2 Gunter s Space Page Retrieved 2016 08 29 Brugge Norbert Antares Propulsion B14643 DE Retrieved 2015 08 29 Antares Fact Sheet PDF Orbital ATK Retrieved 2016 08 29 a b ISS Utilization Cygnus eoPortal Directory Archived from the original on 2016 08 29 Retrieved 2016 08 29 a b DeSantis Dylan Satellite Thruster Propulsion H2O2 Bipropellant Comparison with Existing Alternatives PDF The Ohio State University Retrieved 2016 08 29 Wade Mark AS 2100 Astronautix com Archived from the original on September 15 2016 Retrieved 2016 08 29 Krebs Gunter Dirk 2016 06 24 MUOS 1 2 3 4 5 Gunter s Space Page Retrieved 2016 08 29 Krebs Gunter Dirk 2016 06 24 AEHF 1 2 3 4 5 6 Gunter s Space Page Retrieved 2016 08 29 a b c ロッキード マーチン社向け衛星用エンジンがフライトに成功 独自開発の世界最高性能のエンジンで２回連続のフライトに成功 Success in two successive flights for the engine with world s best performance in Japanese IHI Aerospace March 9 2006 Archived from the original on 2010 09 24 Retrieved 2016 08 29 Krebs Gunter Dirk 2016 08 05 OSC Orbital ATK StarBus Star 2 GeoStar 2 Gunter s Space Page Retrieved 2016 08 29 Krebs Gunter Dirk 2016 04 17 Telkom 2 Gunter s Space Page Retrieved 2016 08 29 IHI Aerospace Manufactured Engines Selected for AEHF 4 MUOS 4 MUOS 5 and Vinasat 2 Satellites by Lockheed Martin Space Systems Company IHI Aerospace November 29 2010 Archived from the original on 2016 08 29 Retrieved 2016 08 29 a b c IHI Aerospace Bipropellant Thrusters PDF IHI Aerospace December 2014 Archived from the original PDF on 2016 08 29 Retrieved 2016 08 29 a b IHI Aerospace IHI Corporate Profile PDF pp 15 16 Archived PDF from the original on 2022 04 17 Retrieved 2016 08 29 Krebs Gunter Dirk 2016 08 24 HTV 1 9 Kounotori 1 9 Gunter s Space Page Retrieved 2016 08 29 Orbital Sciences developed CygnusTM Spacecraft which uses IHI Aerospace s Delta Velocity Engine as its main engine successfully berthed to the International Space Station IHI Aerospace October 3 2013 Archived from the original on 2016 08 29 Retrieved 2016 08 29 https www nasaspaceflight com 2018 01 spacex govsat 1 falcon 9 launch HTV4 KOUNOTORI 4 Mission Press Kit PDF JAXA August 2 2013 Archived from the original PDF on 2016 08 29 Retrieved 2016 08 29 On orbit operation result of KAGUYA Lunar Explorer propulsion subsystem PDF JAXA 2008 Retrieved 2016 08 29 Ideo Masuda JAXA Hideshi Kagawa JAXA Daisuke Goto JAXA Hiroyuki Minamino JAXA Kenichi Kajiwara JAXA Yoshihiro Kishino IHI Aerospace Masayuki Tamura IHI Aerospace Mamoru Takahashi IHI Aerospace Yosuke Iwayama NEC Toshiba Space Systems Shingo Ikegami NEC Corporation Makoto Miyata NEC Corporation Final Operations of Kaguya PDF Archived from the original PDF on 2016 12 21 Retrieved 2016 08 29 Retrieved from https en wikipedia org w index php title BT 4 rocket engine amp oldid 1084018515, wikipedia, wiki, book, books, library,

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