Analysis of a magnetic three-axis stabilized attitude control system for the NPSAT1 spacecraft
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Authors
Zirkle, Todd A.
Subjects
Advisors
Spencer, Michael
Date of Issue
2001-09
Date
Publisher
Monterey, California. Naval Postgraduate School
Language
Abstract
The NPSAT1 satellite uses an active magnetic torque rod system, with a magnetometer for attitude determination, to maintain 3-axis stabilization, with a slightly gravity gradient friendly structure. This thesis will examine the performance of three combinations of programs and simulation models for the NPSAT1 satellite attitude control system. The models include a magnetic control law with a reduced order estimator to generate torque commands to achieve spacecraft nadir pointing and a magnetic rate (Bdot) control law to reduce spacecraft angular rates. The performances of two Bdot mode switching designs are compared. Also, a case is made for the benefits of priming the systemαs reduced estimator prior to mode switching. All of the control methods analyzed appear to be valid control methods to achieve three-axis attitude stabilization using only magnetic torquers for active control. The most efficient control method analyzed incorporates a hand-off method from a magnetic rate (Bdot) control loop to a magnetic control loop. The results of this analysis indicates that the best use of this method is to perform the Bdot hand-off following the achievement of a predetermined combined angular rate.
Type
Thesis
Description
Series/Report No
Department
Space Systems Operations
Organization
Identifiers
NPS Report Number
Sponsors
Funder
Format
xvi, 93 p. ;
Citation
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.