Attitude Stabilization of a CubeSat Using Fuzzy Logic Controller

Abstract

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.