State feedback H8 control of a rigid spacecraft

In the present paper we address a state feedback H 1 suboptimal control problem for a rigid spacecraft with three control torques and disturbances. The state feedback H 1 suboptimal control problem on T SO(3) is transferred to a corresponding state feedback H 1 suboptimal control problem on T S 3 , and the Hamilton-Jacobi inequality associated with this problem is solved. We obtain a state feedback control law involving the Euler parameters which solves the problem formulated on T S 3 globally. This state feedback also solves the original problem on T SO(3) when the initial values of the Euler parameters are appropriately chosen.