Résumé:
This thesis focuses on the attitude stabilization of a 2U CubeSat in low Earth orbit. After
deployment, the satellite undergoes uncontrolled tumbling due to separation forces. To
mitigate this, a B-dot controller using magnetorquers is applied during the detumbling
phase. The results confirm the effectiveness of this approach in reducing angular velocities
and preparing the satellite for precise control.
Following detumbling, two attitude control strategies are compared: a classical PID
controller and a Fuzzy Logic Controller (FLC). Simulation results show that while the
PID controller offers acceptable performance, it is limited by overshoot and long settling
times. In contrast, the FLC demonstrates faster response, lower overshoot, and higher
robustness against disturbances and nonlinear dynamics.
This work highlights the potential of fuzzy logic-based control for small satellites,
providing a reliable, energy-efficient, and adaptive solution for precise attitude regulation.
