Design of micro momentum wheel controller for micro-nano satellite

Micro-nano satellite has a small moment of inertia, which can be affected by gravity gradient torque, solar wind radiation torque, and thermal radiation torque caused by uneven temperature of the satellite during the orbit flight. These slight disturbance torques can be accumulated, cause the attitude of the satellite to deviate from its ideal state, and finally affect the performance of the satellite´s task. In addition, high inertia ratio should be adopted to provide the satellite with attitude maneuvering allowance. Momentum wheel which is a quick response, zero steady error and strong robust actuator is critical to stabilize the attitude of the satellite. This research gives a self-adaption fuzzy controller which can adjust operation parameters of the micro momentum wheel timely based on the fuzzy strategy. This controller shows that it can make the momentum wheel tend to the ideal state and meet higher deign qualification with ultrafast response (≤0.2s), super small steady error (0.00166%) and high disturbance rejection.