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Effect of reaction wheel configurations on control performance in low earth orbit satellites
(İdris Karagöz, 2025) Kartal, Seda
This study involves a comprehensive modeling and analysis process for the attitude control of a satellite operating in low Earth orbit (LEO). Initially, a mathematical model representing the satellite's rotational motions along the x, y, and z axes—namely roll, pitch, and yaw—was derived. Subsequently, the electrical and mechanical properties of the reaction wheel systems employed for precise attitude control were examined in detail. The attitude control was achieved by driving each reaction wheel with a DC motor, and the torque and angular velocity parameters generated by the motors were regulated using Proportional-Integral-Derivative (PID) controllers. Three different reaction wheel configurations were investigated: the standard orthogonal three-wheel setup, the tetrahedral four-wheel configuration, and the pyramid four-wheel structure. For each configuration, a comparative analysis was conducted in terms of system performance, control stability, and energy efficiency. The findings indicate that pyramid four-wheel configuration exhibits the highest energy consumption. The results demonstrate that selecting an appropriate configuration in accordance with mission requirements plays a critical role in determining the overall performance of the attitude control system.