COMBINED USE OF CONTROL MOMENT GYROS AND MAGNETIC TORQUE RODS FOR SATELLITE ATTITUDE CONTROL

Date

2010-09-15

Author

Elmas, Tuba C.
Tekinalp, Ozan

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This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

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A new approach to the attitude control of an over actuated satellite is presented. A control moment gyroscopes cluster containing four actuators in a pyramid mounting configuration, and a set of three orthogonal magnetic torque rods are considered to steer the satellite. Two steering algorithms, Moore-Penrose pseudo inverse, and the recently developed blended-inverse, are considered. The success of the blended-inverse algorithm to select the desired actuators in the system is demonstrated. It is also shown through simulations that the blended-inverse algorithm successfully carries out the maneuver without getting trapped in singular configurations, while the classical Moore-Penrose pseudo inverse algorithm fails to realize.

Subject Keywords

Steering law

URI

https://hdl.handle.net/11511/53665

Collections

Department of Aerospace Engineering, Conference / Seminar

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Citation Formats

T. C. Elmas and O. Tekinalp, “COMBINED USE OF CONTROL MOMENT GYROS AND MAGNETIC TORQUE RODS FOR SATELLITE ATTITUDE CONTROL,” 2010, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/53665.