
Over the years, Japan has launched a series of Engineering Test Satellites - ETS-I (KIKU-1) to ETS-VII (KIKU-7, Orihime/Hikoboshi). Each of these addressed the technological needs of its time. ETS-VIII was launched by the H-IIA launch vehicle No.11, with the main purpose of dealing with the increasing demand for digital communications, such as mobile phones and other mobile devices. The satellite, with a gross weight of around three tons and a diameter of 40 meters, has two Large Deployable Antenna Reflectors and two Solar Array paddles. One LDAR, about the size of a tennis court, is one of the world’s largest geostationary satellites. Its size will enable direct communications with a geostationary satellite that covers all of Japan, making mobile communications more reliable. Currently under development are Large Deployable Antenna Reflectors with metal-mesh, high-power transponders and on-board processors. The technologies used in the development of these LDARs will be applicable to other large space structures.
The mission of ETS-VIII is not only to improve the environment for mobile-phone-based communications, but also to contribute to the development of technologies for a satellite-based multimedia broadcasting system for mobile devices. It will play an important role in the provision of services and information, such as the transmission of CD-quality audio and video; more reliable voice and data communications; global positioning of and broadcasting to moving objects such as cars; faster disaster relief, etc. Experiments in the fundamental technology for satellite-positioning, using a high-precision clock system, will be conducted between ETS-VIII and GPS, through the reception of signals transmitted from the clock.
| International Designation Code | 2006-059A |
|---|---|
| Launch Date | 15:32, December 18, 2006 (JST) |
| Launch Vehicle | H-IIA Launch Vehicle No.11 |
| Location | Tanegashima Space Center |
| Shape | Main body is about 2.4m x 2.5m x 3.8m (With two large deployable antennas of 19m x 17m) |
| Weight | Mass at liftoff: Approx. 5,800kg |
| Orbiter | Geostationary orbit(GEO) (Longitude 146deg E (tentative)) |
| Altitude | Approx. 36,000km |
| Inclination | 0 degrees |
| Period | Approx. 24 hours |
| Attitude Control | Three-axis stabilization |