STARS-II
| Mission type | Technology |
|---|---|
| Operator | Kagawa University |
| COSPAR ID | 2014-009H |
| SATCAT № | 39579 |
| Website | stars |
| Spacecraft properties | |
| Manufacturer | Kagawa University |
| Launch mass | 9 kilograms (20 lb) |
| Start of mission | |
| Launch date | 27 February 2014, 18:37 UTC[1] |
| Rocket | H-IIA 202 |
| Launch site | Tanegashima Yoshinobu 1 |
| Contractor | Mitsubishi |
| End of mission | |
| Decay date | 26 April 2014 |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Low Earth |
| Semi-major axis | 6,745.00 kilometres (4,191.15 mi) |
| Eccentricity | 0.00103780 |
| Perigee | 367 kilometres (228 mi) |
| Apogee | 381 kilometres (237 mi) |
| Inclination | 65 degrees |
| Period | 92.02 minutes |
| Epoch | 28 February 2014[2] |
Space Tethered Autonomous Robotic Satellite II or STARS-II, was a nanosatellite built by Japan's Kagawa University to test an electrodynamic tether in low Earth orbit.
The satellite split into two parts, connected by a 300-metre (980 ft) tether, to conduct its experiments which consisted of recording a video of tether deployment and using the tether to deorbit the satellite. The spacecraft consisted of a 5-kilogram (11 lb) base vehicle, with dimensions of 160 by 160 by 253 millimetres (6.3 in × 6.3 in × 10.0 in) and a 4-kilogram (8.8 lb) vehicle at the end of the tether measuring 160 by 160 by 158 millimetres (6.3 in × 6.3 in × 6.2 in).
STARS-II was launched by an H-IIA rocket, flying in the 202 configuration, as a secondary payload aboard the launch of the GPM Core Observatory on 27 February 2014. After two months in orbit, STARS-II reentered the atmosphere on 26 April 2014.
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