Supriya Ghosh (Editor)

BT 4 (rocket engine)

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Country of origin
  
Japan

Associated L/V
  
HTV, Cygnus

Propellant
  
N2O4 / Hydrazine

Designer
  
IHI Aerospace

Status
  
In production

Mixture ratio
  
1.69

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.

Contents

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. 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.

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. 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).

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.

On March 9, 2006, IHI Aerospace announced that the AEHF-2 BT-4 engine had successfully performed its mission, unlike AEHF-1's. 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.

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.

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.

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 weights 4 kg (8.8 lb) and is 65 cm (26 in) tall.
  • 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.
  • 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 weights 4 kg (8.8 lb) and is 80 cm (31 in) tall.
  • 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.
  • 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.
  • 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).

    • References

    BT-4 (rocket engine) Wikipedia
    (Text) CC BY-SA


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