A detailed description of the scope and motivation for this project, as well as any relevant resources
This is a small analysis project that calls for the investigation of FINCH’s orientation while in orbit. Specifically, when uncontrolled by ADCS. We want to know whether FINCH settles in a particular orientation, or tumbles randomly. This analysis is a stepping stone towards determining whether we will be able to comply with the FINCH-Spacecraft-DeorbitTime requirement, even in the scenario where our ADCS stops functioning altogether and the satellite ceases to be controlled.
The following orbital parameters are to be used in the analysis:
| Start Year | Jan 1, 2026 |
|---|---|
| Altitude | 500, 525, 550km |
| Inclination | 97.6° |
| R. A. of Ascending Node | 342.74° (12:00) |
| Argument of Perigee | 0° |
| Eccentricity | 1 (circular) |
The above are derived from FINCH-Spacecraft-OrbitalInjectionParameters
The following CAD model can be used as a reference of the FINCH spacecraft:
The rotational inertia for following mass cases were derived from the CAD model. The model assumes the mass is evenly distributed within the volume of the spacecraft. Because the model is symmetrical about the Z-axis, the inertia matrices are diagonal. Only the diagonal elements are shown. The rotational inertia matrices are computed using the FINCH Deorbit Body Model in Fusion 360.
| Mass [kg] | I_xx [kg m^2] | I_yy [kg m^2] | I_zz [kg m^2] |
|---|---|---|---|
| 3 | 0.035535547 | 0.035535547 | 0.004855033 |
| 3.5 | 0.041458138 | 0.041458138 | 0.005664205 |
| 4 | 0.047380729 | 0.047380729 | 0.006473377 |
A list of sequential tasks for the project. The project is complete when all tasks are complete