Method and device for controlling satellite attitude and...

Details Method and device for controlling satellite attitude and... Method and device for controlling satellite attitude and...

2007-01-30

2007-01-30

Zanelli, Michael J. (Department: 3661)

Data processing: vehicles, navigation, and relative location

Vehicle control, guidance, operation, or indication

Aeronautical vehicle

C244S164000

Reexamination Certificate

active

10482031

ABSTRACT:
In order to control the attitude of a satellite having at least four gyroscopic actuators with respective spinners mounted on gimbals steerable about axes parallel to one or the other of only two different directions that are fixed relative to the satellite, the attitude of the satellite is measured using sensors on board the satellite, the control torque required to perform an attitude-changing maneuver is calculated, local linearization calculation is performed based on pseudo-inversion of the Jacobean matrix of the function associating the orientations of the actuator gimbals with the total angular momentum of the cluster in order to determine a new gimbal orientation, and precession speeds of at least one of the gimbals of the actuators are controlled to deliver the control torque for reaching the desired configuration.

REFERENCES:
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patent: 6305647 (2001-10-01), Defendini et al.
patent: 6682019 (2004-01-01), Bailey
patent: 2 773 775 (1998-01-01), None
Lagadec et al; “Low Cost CMG-Based AOCS Designs”; XP-008003434; Proceedings 4thESA International Conference on Spacecraft Guidance, Navigation and Control Systems, ESTEC; Oct. 18-21, 1999; pp. 393-398.

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