Fuzzy attitude control for flexible satellite during orbit maneuver

Satellite with a large solar panel is taken as practical background. The dynamic model of the satellite is established via Lagrange equations. This model includes the orbit motion, the attitude motion and the flexible vibration of the solar panel. The coupling relations between the orbit control force, the attitude and the flexible vibration are studied. The orbit control force would stimulate the vibration of the flexible panel when the satellite takes orbital maneuver, and disturbance torque would also affect the attitude of the satellite. Attitude control law is designed based on fuzzy control theory considering the output character of the thrusters. Numerical simulation was carried out to testify the efficiency of the control system. The attitude angles are controlled within 0.6deg for all three axes and angular velocity is within 0.04deg/s during the orbit maneuver period.