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.
A nonlinear attitude control law for a satellite with flexible appendages / Monaco, Salvatore; Stornelli, S.. - STAMPA. - 1:(1985), pp. 1654-1659. (Intervento presentato al convegno 24th IEEE Conference on Decision and Control tenutosi a Fort Lauderdale, Florida nel 11.13 December 1985) [10.1109/CDC.1985.268797].
A nonlinear attitude control law for a satellite with flexible appendages
MONACO, Salvatore;
1985
Abstract
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.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
