Method and apparatus for contingency guidance of a CMG-actuated spacecraft
Ross, Isaac Michael
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Methods and apparatus are presented for spacecraft operation using non-Eigen axis attitude transitions via control momentum gyroscopes (CM Gs) to avoid or mitigate singularities by providing a time-varying attitude command vector including a plurality of time-varying attitude command signals or values representing a plurality of spacecraft states and control trajectories as a guidance command input to an attitude controller of the spacecraft without modifying the spacecraft feedback control law.
Patent Number: 9,038,958 B1
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