A nonlinear attitude control law for a satellite with flexible appendages

The paper deals with the wide angle attitude control problem for a satellite with flexible appendages. On the basis of the model specified by the kinematic equations, in the unitary quaternions parametrization, and by the dynamical equations, which result from the hybrid coordinates approach, it is proposed a static state feedback control law for the problem under study. The similations implemented are characterized by the effort of overcoming some obvious problems which arise in the practical implementation of the proposed control law