The problem of attitude optimal control a spacecraft as solid body with the energy spent on maneuvering taken quadratic functional, and fixed transition time, is investigated. dynamic configuration boundary conditions an angular velocity are arbitrary; function not limited. According to Poinsot concept from theoretical mechanics interpretation motion around point help Pontryagin maximum princip...

New approach for modelling a physical hysteresis damping the flexible spacecraft structure oscillations, is developed. New results on communication satellite attitude guidance and digital robust control with precise pointing the large-scale flexible antennas, are presented.

New approach for modelling a physical hysteresis damping the flexible spacecraft structure oscillations, is developed. New results on communication satellite attitude guidance and digital robust control with precise pointing the large-scale flexible antennas, are presented.

In this article, anti-unwinding attitude maneuver control for rigid spacecraft is considered. First, in order to avoid the unwinding phenomenon when system states are restricted switching surface, a novel function designed by hyperbolic sine such that surface contains two equilibriums. Then, sliding mode controller developed based on proposed ensure robustness of closed-loop disturbance and ine...