SERVIS-1
| Mission type | Technology |
|---|---|
| Operator | USEF |
| COSPAR ID | {{#property:P247}}Lua error in Module:EditAtWikidata at line 29: attempt to index field 'wikibase' (a nil value). |
| Website | USEF - Project SERVIS |
| Mission duration | 2 years |
| Spacecraft properties | |
| Manufacturer | Mitsubishi Electric |
| Launch mass | 840 kilograms (1,850 lb) |
| Dimensions | 2.5 by 10.2 metres (8.2 by 33.5 ft) |
| Power | 1,300 watts |
| Start of mission | |
| Launch date | 30 October 2003, 13:43:42 UTC[1] |
| Rocket | Rokot/Briz-KM |
| Launch site | Plesetsk 133/3 |
| Contractor | Eurockot |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Sun-synchronous |
| Perigee altitude | 984 kilometres (611 mi)[2] |
| Apogee altitude | 1,015 kilometres (631 mi)[2] |
| Inclination | 99.5 degrees[2] |
SERVIS-1, or Space Environment Reliability Verification Integrated System 1, is a Japanese satellite designed for testing the performance of commercial off-the-shelf products in the space environment. It has a mass of about 840 kg, and was launched on 30 October 2003 from the Plesetsk Cosmodrome by Eurockot, who used a Rokot rocket with a Briz-KM upper stage. The satellite was active for two years.[3] A second satellite, SERVIS-2, was launched in 2010.
Experiments
[edit | edit source]Nine experiments were being conducted by SERVIS-1.[3]
| Name | Full name | Description | Remarks |
|---|---|---|---|
| VTS | Vane-type Propellant Tank System | ||
| INU | Integrated Navigation Unit | ||
| PCDS | Power Control and Distribution Unit | ||
| APDM | Advanced Paddle Drive Mechanism | ||
| ATTC | Advanced Tracking Telemetry and Command Transponder | ||
| OBC | On Board Computer | ||
| SIS | Integrated Satellite Controller with Star Sensor | ||
| LIB | Lithium Ion Battery System | ||
| FOIRU | Fibre Optic Gyro Inertial Reference Unit |
Results from the mission
[edit | edit source]All the modules on the satellite worked as planned.[4] The mission tested a number of electronic components, and determined that the rate of single-event upsets at its 1000 km orbit was substantially less than had been expected from tests using heavy ion bombardment on the ground.[3]
See also
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References
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