Function | Medium expendable Launch vehicle |
---|---|
Manufacturer | Galaxy Express (JAXA/ULA/IHI) |
Country of origin | Japan/United States |
Size | |
Height | 48 m (157 ft) |
Diameter | 3.3 m (11 ft) |
Mass | 190,500 kg (420,000 lb) |
Stages | 2 |
Capacity | |
Payload to LEO | |
Mass | 3,600 kg (7,900 lb) |
Payload to 800km SSO | |
Mass | 1,814 kg (3,999 lb) |
Launch history | |
Status | Cancelled 2010 |
Launch sites | Vandenberg SLC-3E |
First stage – Atlas CCB | |
Powered by | 1 RD-180 |
Maximum thrust | 4,152 kN (933,000 lbf) |
Specific impulse | 311 seconds (3.05 km/s) |
Burn time | 253 seconds |
Propellant | RP-1/LOX |
Second stage – GX | |
Powered by | 1 LE-8 |
Maximum thrust | 118 kN (27,000 lbf) |
Specific impulse | 323 seconds (3.17 km/s) |
Burn time | 480 seconds |
Propellant | LNG/LOX |
GX was a design for an expendable launch system intended to compete in the commercial satellite launch sector. The system had developed by Galaxy Express Corporation, a joint venture between IHI Corporation (IHI), the Japan Aerospace Exploration Agency (JAXA), United Launch Alliance (ULA), Lockheed Martin Corporation (LM) and several other Japanese companies.[1]
The GX design uses a two-stage rocket. The first stage would have been the Atlas Common Core Booster, currently used as the first stage of the Atlas V rocket, which would have been provided by United Launch Alliance.[2] The second stage was to be a newly designed stage produced by IHI, using liquefied natural gas as fuel and liquid oxygen as an oxidizer. The GX would have been the only space vehicle to use that combination of fuel and oxidizer.
The Japanese government finally abandoned the GX program in December 2009. Galaxy Express disbanded around March 2010.[3][4]