Developing Cubesat Attitude Control: A Simulation of Reaction Wheels with Genetically Optimized Control System

The growing significance of attitude control for small satellites, particularly Cubesats, stems from their affordability and diverse applications. Various control algorithms can be tailored to the satellite's operational mode during its lifetime. This study presents the design and simulation of a Cubesat attitude control system employing a pyramidal configuration of four reaction wheels for actuation in both re-orientation and stabilization modes. The simulation incorporates realistic constraints such as reaction wheel saturation limit and maximum continuous torque. A quaternion Proportional Derivative (PD) controller regulates the attitude while accounting for disruptive torques like aerodynamic drag and gravitational torques. The controller gains are optimized using a genetic algorithm (GA) to enhance the system's resilience to disturbances. Simulation experiments evaluate the control system's effectiveness based on metrics like settling time, pointing accuracy, and robustness to external torques. The results were analyzed to identify areas for further improvement, paving the way for a high-performance Cubesat attitude control system.