Satellite Specifications
| Item | Specification |
|---|---|
| Imager | NER < 0.6% with a forward motion compensation (FMC) factor of 4:1 |
| Operational MTF: >= 5% over the full field (excluding orbit motion effects) | |
| GSD = 6.25m @ an orbit altitude of 500 km | |
| 6 spectral band (visible range) line scanner | |
| Matrix sensor included for "snapshot" pictures | |
| Image quantisation: 12-bit (data for each pixel stored as 2 bytes) | |
| Image modes | Default scan mode with FMC = 4:1 but system can operate with FMC = 1:1 with consequent degradation in NER |
| In FMC = 4:1 mode, non-contiguous scenes of 45 km x 45 km can be imaged (max 10 scenes in 6 spectral bands before data downloading is required) | |
| In FMC = 1:1 mode, a contiguous strip with 45 km swath can be imaged (max track length of 450 km can be imaged in 6 spectral bands before data downloading is required) | |
| Imager data store | 24 Gbyte |
| Image data downlink | Expected frequency to be implemented on satellite exploration S-band |
| Link margin: 3dB @ 10° (calculated with 0dBi satellite antenna; 5W Tx power and SAC GS parameters) | |
| Data rate sufficient to download full image data store during two night passes | |
| No real-time downloading of images (all images stored on-board the satellite) | |
| Viewfinder | Live downlinking of PAL video images during TT&C ground station passes |
| PAL images selectable between B&W (narrow FOV) and two wider FOV colour PAL cameras | |
| Satellite bore-sight steerable with "joystick" interface | |
| Viewfinder mode can be interrupted with either image snapshot or image linescan modes upon ground command | |
| The bore-sight direction of the viewfinder is the same as the main imager | |
| ADCS system | The satellite is 3-axis stabilised |
| System performance is sufficient to maintain pointing accuracy for image downloading | |
| ADCS performance shall not degrade image quality | |
| The satellite bore-sight can be controlled to within 3 km on the ground | |
| The intended system implementation will use a combination of the following actuators and sensors: Horizon, fine-sun, coarse-sun sensors; star camera; magnetometer(s); fibre-optic gyros; reaction wheels and magneto torquers | |
| A satellite slew manoeuvre from one stabilised position to another stabilised position, through an angle of 30°, can be completed in less than 1 minute | |
| Propulsion System | Sufficient propellant included to maintain a satisfactory orbit for 3–4 years |
| System will demonstrate orbit constellation deployment as well as orbit maintenance | |
| TT&C Communication Link | Expected frequencies to be implemented on commercial VHF uplink and UHF downlink |
| Link margin: 6dB @ 5° (calculated with -12dBi satellite antenna null; 5W Tx power and 12dBi GS antenna gain) | |
| Satellite Housekeeping | One TT&C GS pass per 24h will be sufficient for the purpose of monitoring telemetry and uploading of new command sets and SW |
| Power | Energy source: solar panel with 65W (EOL) capacity |
| Mission planning will dictate energy requirements per orbit | |
| Experiments | Provision is made for two 1-kg experiments |
| SU will certify the space environmental readiness of the experiments at MC level prior to integration | |
| Average power available per experiment: 1.2W (TBC) | |
| Peak power available per experiment: 10W (TBC) | |
| Orbit lifetime | Design lifetime of 3 years at an orbit altitude of 500 km (subject to average sun activity) |
| Given the ultimate unpredictability of the space environment, the operational life can vary from the design lifetime |
* Courtesy of SunSpace
Read more about this topic: Sumbandila Sat
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