| 摘要 |
<p>An attitude control actuator, particularly for spacecrafts, includes a frame (3), two flywheels (7,9) driven by respective motors with opposite and equal spins, and supported by gimbals journaled on the frame about respective parallel axes at right angles to the axes of the flywheels, and motors for rotating the gimbals through desired angular displacements about their journal axes. The frame is pivoted to a support member (5) rigidly associated to the spacecraft and is capable of a rotation of 90 DEG in order to control the attitude of the spacecraft, with respect to any desired direction, with just one dual flywheel frame. <IMAGE></p> |
