Résumé:
CubeSats often tumble uncontrollably after deployment due to uneven forces, requiring
stabilization before accurate orientation control. This work explores two control
strategies: a PID controller for initial detumbling and an LQR controller for precise
attitude regulation. The system uses magnetorquers with a B-Dot algorithm to reduce
spin, then employs reaction wheels for fine three-axis control. The spacecraft’s
motion is modeled using Euler’s equations and Keplerian orbital dynamics, with magnetic
field data provided by the IGRF model. Key hardware includes magnetorquers,
reaction wheels, gyroscopes, and magnetometers. Simulation results compare PID
and LQR performance, showing that PID is better suited for fast, simple detumbling,
while LQR excels in maintaining stable and accurate orientation with better energy
efficiency.
Keywords: CubeSat, stabilization, PID, LQR, Control, magnetic torque.
