Research On Dynamics Modeling And Attitude Control Of Flexible Solar Sail Spacecraft

The traditional attitude control will not meet demand of the task of a solar sail,need to introduce new control solar sail attitude control system, because of solarsail’s characteristics: big flexible, big inertia. The size and direction of orbit thrustwill change with the change of attitude, therefore, the attitude control of a solar sailis key technology of the miss ion. In this context, this paper paid attention todynamic modeling and attitude control methods of solar sail with a universal joint.This paper includes the following several aspects:First of all, defines attitude of the sail, deduces transfor mation betweenattitude and parameters of orbit and quaternion us ing coordinate. The hybridcoordinate and virtual power princ iple is adopted to establish dynamic model ofsquare solar sail. In order to eliminate lever relative angular velocity of the threecomponents of independent effect, introducing the relative angular velocity ofuniversal joint. To deduce the sail vibration equation of the imp lementation ofregularization, apply of modal analysis.Secondly, this paper designs two kinds of different robust controller: the firststate feedback control law is designed to a dyna mic model which containsuncertainties system parameter and mode. The second state feedback control law isdesigned to cell LPV system according to quadratic stability theory.Finally, set up simulation platform based on the above controller and PDcontroller. It is shown that the controller designed by this paper can guarantee thesail closed-loop uncertainty system stability and restrain vibration of the system.