| 摘要 |
<p>Method of satellite attitude control by control of 'control moment gyros' joint speed of a group of 'control moment gyros', having gyros, respectively mounted in frames, rotating on a satellite platform, around different orientated axes, from which: - is determined, from initial and final conditions in terms of attitude/angular speed/time, a group configuration remote from any singular configuration such that the kinetic moment exchange between the group of 'control moment gyros' and the satellite during an imparted period provoke the desired attitude maneuver; - bring, in a simultaneous and independent fashion, the orientation of each gyro into its ordered position by means of an angular position order sent by open loop local servo-control of the angular position of the gyros. An Independent claim is included for an attitude control device.</p> |
