Developing a proposed satellite reaction wheel model with current mode control

The motivation for development of reaction wheel components model is to achieve a precise reaction wheel model for attitude control subsystem of spacecraft. Recent developments in spacecrafts manufacturing industry have heightened the need for accurate attitude control subsystems. Performance of spacecraft attitude control, as one of the complex subsystems of spacecrafts, is often reduced by both environmental and internal disturbances. Ideally, the output torque of reaction wheel should depend on the input current but in reality; various disturbances are operative as well. Most commonly, disturbance sources are flywheel imbalance, bearing frictions, bearing torque noise, motor torque ripple and cogging. This study proposes a precise reaction wheel model and these disturbance torques are considered inside the model. Then the results show how disturbance torques deteriorate the wheel speed, angular momentum, and reaction torque of the reaction wheel.