Abstract: Precision attitude control subsystems are now more essential than ever because of recent developments in the spacecraft manufacturing sector. One of the complex spaceship subsystems, attitude control, is frequently hampered by both internal and external disturbances. The output torque of a reaction wheel should, in theory, be proportional to the input current, even though there are numerous disturbances in practice. This proposal provides a technique to implement the change in the allocated torque to the wheel that takes disturbance torques into account. The results then demonstrate how disturbance torques affect the reaction torque and wheel speed of the reaction wheel.
Keywords: Reaction Wheel, Attitude Control System (ACS), Wheel Torque, Spacecraft Dynamics
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