Patent ID: 9745082
Date: 2017-08-29
CPC Classifications: B64G

Claim:
1. A satellite attitude control system for a satellite, the satellite attitude control system comprising: four hybrid control moment gyroscopes arranged in a pyramid configuration, each hybrid control moment gyroscope including a control moment gyroscope actuator and a reaction wheel actuator; and a retargeting controller for retargeting the satellite from an initial state through a desired slew and settle maneuver to a desired final state using path and endpoint constrained time-optimal control, the retargeting controller configured to determine a set of gimbal angular rate vectors based on the initial state, the desired final state, and a predetermined set of path and endpoint constraints selected to avoid control moment gyroscope actuator singularities and reaction wheel actuator singularities and to ensure that the hybrid control moment gyroscopes will complete the slew maneuver in a configuration capable of performing the settle maneuver using the reaction wheel actuators and to produce retargeting commands for the hybrid control moment gyroscopes based on the set of gimbal angular rate vectors.