# INSPIRE-SAT 7, a Second CubeSat to Measure the Earth's Energy Budget and to Probe the Ionosphere
## 3 Description of the INSPIRE-SAT 7 Mission and Mission Operations
### Inspire-SAT 7 Mission Concept of Operations and Calibration and Validation (Cal/Val)  
INSPIRE-SAT 7 mission concept of operations (ConOps) phases will be close to those used in UVSQ-SAT [1]. There are four distinct ConOps phases:  
* Operations before launch and launch,
* Launch early operations and satellite platform in-orbit verification,
* Instrument in-orbit verification and operations calibration/validation (Cal/Val) of the instruments payload,
* End of life of the INSPIRE-SAT 7 CubeSat. \begin{table}
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**Parameter** & **Requirements** \\ \hline IMU signal range & Accelerometer: \(\pm\)2.0 g \\  & Gyroscope: \(\pm\)250.0 deg \\  & Compass: \(\pm\)491.2 \(\mu\)T \\ IMU resolution & 16 bits \\ IMU noise detection & Accelerometer: \(<\)250 \(\mathrm{\SIUnitSymbolMicro\SIUnitSymbolMicro\SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro\SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbolMicro \SIUnitSymbolMicro\SIUnitSymbolMicro \SIUnitSymbol  
Based on our experience of the UVSQ-SAT mission, an automatic procedure will be programmed on board INSPIRE-SAT 7 for early operations. The following chronology will be implemented:  
* Separation of INSPIRE-SAT 7 from the launcher. Automatic platform start-up in 'INIT' mode. * T0 + 15 min: Sequence of deployment of telecommunication antennas (INSPIRE-SAT 7 platform). * T0 + 30 min: Sequence of deployment of the CUIONO1 payload antennas (INSPIRE-SAT 7 payload). * T0 + 40 min: Switch to 'Detumbling' mode--iMTQ board On during 5 min to stabilize the CubeSat. * T0 + 45 min: Switch to 'Stand-by mode' and waiting for the first tele-command (TC) from the LATMOS ground station. * If after 4 days, no TC is received by the CubeSat, the initialization procedure is restarted in 'debugging' mode (deployment of the telecommunication antennas). And this every 4 days until receipt of the first TC. * T0 + 4 days: Switch to 'Nominal mode' using a TC from LATMOS ground station. Three phases of cal/val are foreseen for INSPIRE-SAT 7:
* A pre-launch phase instruments characterizations and on-ground calibration. Several tests are planned to determine with accuracy the pre-flight absolute uncertainty of scientific variables of interest for the INSPIRE-SAT 7 mission (OSR, OLR, TSI, UV SSI).