This study investigates satellite attitude control during orbital separation, focusing on damping the angular velocity of separation and other disturbances. The transfer of the angular velocity co-axial to the thrusters is achieved using the Euler equations of satellite dynamics, and during the wheel momentum transfer phase, the satellite utilizes the wheel to fine-tune its attitude while maintaining angular momentum. A number of constraints are imposed during this precise control phase. These constraints ensure that the wheel’s thruster coaxial angular velocity remains zero, thus allowing the momentum to be redistributed without affecting the satellite’s stability. The summarized mathematical model demonstrates a controlled momentum transfer consistent with the principle of angular momentum conservation, ensuring a precise and stable orientation of the satellite. Simulations confirm the effectiveness of combining thrusters with reaction wheels.