The control moment gyro (CMG) is a key spacecraft attitude control actuator,
but it is also a major source of disturbances. Therefore, qualification
of the CMG disturbances is one of the most significant topics in designing
a highly accurate attitude control system. The properties of the measured
disturbances are useful in predicting their effects on attitude dynamics
as well as in checking the reliability of the CMG itself. Future space
missions will require much greater levels of CMG performance, including
less disturbance generation and greater reliability. Space missions requiring
highly accurate land or celestial observation will require better management
of disturbances at much wider frequency ranges than is possible with current
CMGs. Acceptable disturbances will also require much lower amplitudes at
all frequencies. Of the numerous key factors for developing new CMGs, we
focused on establishing a method to analyze and compensate measure disturbances.
control moment gyro (CMG)
