MFDs of Spinning Satellite and Attitude Control Using Gyrotorquers

Document Type

Article

Publication Date

9-1989

Publication Title

IEEE Transactions on Aerospace and Electronic Systems

Volume

25

Issue

5

First page number:

611

Last page number:

620

Abstract

Questions related to the matrix fraction descriptions (MFDs) and the minimal realizations of the transfer matrix of a spinning satellite system and control system design using output feedback are considered. The control torques are generated using gyrotorquers, and the output variables are the attitude angles. Two minimal state-space representations of the system, namely, a controller-form and an observer-form realization, are obtained from a right and left MFD of the transfer matrix, respectively. Using these canonical realizations, analytical expression for the feedback matrices of the controller and the observer as functions of the system parameters are obtained. The poles of the closed-loop system are invariant with respect to the spin rate of the satellite. Simulation results are presented to show that precise attitude control is accomplished in the closed-loop system using output feedback.

Keywords

Artificial satellites--Attitude control systems; Control theory; Feedback control systems; Gyrostabilizers

Disciplines

Aerospace Engineering | Controls and Control Theory | Electrical and Computer Engineering | Navigation, Guidance, Control and Dynamics

Language

English

Permissions

Use Find in Your Library, contact the author, or interlibrary loan to garner a copy of the item. Publisher policy does not allow archiving the final published version. If a post-print (author's peer-reviewed manuscript) is allowed and available, or publisher policy changes, the item will be deposited.

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