DYNAMIC CMG ARRAY AND METHOD

摘要

Methods and apparatus are provided for reorienting control moment gyros (CMGs) (10) to compensate for CMG (10) failure or change in spacecraft (S/C) mass properties or mission. An improved CMG (10) comprises a drive means for rotating the CMG (10) around an axis (18) not parallel to the CMG gimbal axis. Releasable clamps lock the CMG (10) to the spacecraft except during CMG array reorientation. CMGs arrays (50) are combined with attitude sensors (102), a command module (104), memory (108) for storing data and programs, CMG drivers (112) and sensors (114) (preferably for each CMG axis (18, 22, 30)), and a controller (116) coupling these elements. The method comprises determining whether a CMG (10) has failed or the S/C properties of mission changed, identifying the working CMGs (10) of the array, determining a new array reorientation for improved spacecraft control, unlocking, reorienting and relocking the CMGs (10) in the array and updating the S/C control parameters for the new array orientation.