State feedback H/sub /spl infin// control of a rigid spacecraft

In the present paper we address a state feedback H/sub /spl infin// suboptimal control problem for a rigid spacecraft with three control torques and disturbances. The state feedback H/sub /spl infin// suboptimal control problem on TSO(3) is transferred to a corresponding state feedback H/sub /spl infin// suboptimal control problem on TS/sup 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 TS/sup 3/ globally. This state feedback also solves the original problem on TSO(3) when the initial values of the Euler parameters are appropriately chosen.