Research on Attitude Control of Zero-Momentum Spinning Satellite

A thruster-based attitude control method for zero momentum spinning satellite is proposed in this paper. For the spinning satellite rotating synchronously with the long baseline rotating payload, if the satellite spin axis is required to point to the earth's center in real time, the gyroscopic moment generated by the angular momentum and precession angular velocity of the spinning satellite is difficult to overcome. Therefore, a zero-momentum spinning satellite scheme is proposed to make the large flywheel angular momentum offset the satellite spin angular momentum, making the whole satellite a zero-momentum system. The influence of the whole satellite dynamic unbalance disturbance torque on the attitude stability is analyzed. The attitude control of the spinning satellite is transformed into a three-axis stability control problem by defining the semi fixed reference coordinate system. The effectiveness of the proposed method is verified by mathematical simulation.