Attitude Control of Miniature Satellites Using Movable Masses

The present paper presents an attitude control scheme for a miniature satellite using movable masses. The system comprises of a rigid satellite and a movable mass actuator. The nonlinear equations of motion of the system are derived using the Lagrangian approach. The control laws for motion of the movable masses are designed based on the linear-quadratic regulator technique to achieve desired satellite attitude. In order to test the performance of the proposed actuator, the governing nonlinear system is numerically simulated in conjunction with the control laws for pico-class satellites (less than 1 kg). Results of the numerical simulation state that it is feasible to stabilize the attitude of a miniature satellite using movable masses. The proposed control actuator can be useful for future space missions involving miniature satellites.