BT-4 (rocket engine)

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.

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 acquires and merges with the aerospace division of Nissan and becomes 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 had 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 Cygnus Orb-D1 mission, IHI announced that the propulsion was based on their 500N Delta-Velocity Engines.^[21]

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 lb_f). It weights 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 lb_f), 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 lb_f), a specific impulse of 329 s (3.23 km/s). It weights 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 lb_f) 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 lb_f). Used in HTV-3 and since HTV-5 onward.^[19][22]
• 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 lb_f) 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).^[23][24]

References

Orbital spacecraft rocket engines and motors that have flown
Liquid fuel engines	17D12 11D426 17D61 AJ10 BT-4 Draco KTDU-426 LEROS LMAE LMDE R-4D RS-25 S400 S5.4 S5.60 S5.79 S5.80 S5.92 SuperDraco TR-201 XLR81
Solid propellant motors	Star 37 Star 48 FG-15 FG-36 SpaB-65 SpaB-140C
Related articles	Spacecraft propulsion Spacecraft Satellite