SDS-1
| Mission type | Technology |
|---|---|
| Operator | JAXA |
| COSPAR ID | 2009-002F |
| SATCAT no. | 33497 |
| Mission duration | 18 months |
| Spacecraft properties | |
| Spacecraft type | SDS |
| Launch mass | 100 kilograms (220 lb) |
| Start of mission | |
| Launch date | 23 January 2009, 03:54 UTC |
| Rocket | H-IIA 202 |
| Launch site | Tanegashima Yoshinobu 1 |
| Contractor | Mitsubishi |
| End of mission | |
| Disposal | Decommissioned |
| Deactivated | 8 September 2010 |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | low Earth |
| Perigee | 671 kilometres (417 mi) |
| Apogee | 671 kilometres (417 mi) |
| Inclination | 98.13 degrees |
| Period | 98.03 minutes |
| Epoch | 2 January 2014, 04:04:20 UTC |
The Small Demonstration Satellite (SDS) is a spacecraft or satellite which is built as part of a JAXA programme to develop and demonstrate technology for and through small satellites. One of the mid-term goals is also to demonstrate formation flying. SDS-1 launched aboard an H-IIA rocket on 23 January 2009, as a secondary payload to GOSAT.[1] The operation finished successfully on September 8, 2010.[2]
The programme started in spring 2006, and continues on from the MicroLabSat spacecraft, which was launched on 14 December 2002, and ceased operations on 27 September 2006.
The following experiments were aboard:
- MTP (Multi-mode integrated Transponder)
- SWIM (SpaceWire demonstration Module)
- AMI (Advanced Micro processing In-orbit experiment equipment)
- TFC (Thin Film Solar Cell)
- DOS (Small Dosimeter)
- Small satellite bus technology experiment.
Total mass of the satellite is 100 kg.
References
- ↑ http://www.jaxa.jp press release dated 23 January 2009
- ↑ "小型実証衛星1型（SDS-1）成果概要と運用終了" (PDF) (in Japanese). September 22, 2010. Retrieved September 23, 2010.
External links
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