Three-axes attitude determination and control system based on magnetorquers for small satellites

In this TFM the attitude determination and control system for the 3Cat-2 nanosatellite will be implemented, including the sun sensors, 3 axes magnetometers and 3 axes gyroscopes to determine the satellite's attitude, and three axes magnetorquers as actuators. Algorithms will be tested in a Matlab-based simulation environment and then converted into C, to be executed in the Nanomind (on board computer) of 3Cat-2. Algorithm performance should be evaluated in an air bearing in the center of a 3 axes Helmholtz coils.