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        Analysis of a magnetic three-axis stabilized attitude control system for the NPSAT1 spacecraft

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        Author
        Zirkle, Todd A.
        Date
        2001
        Advisor
        Spencer, Michael
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        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.
        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.
        URI
        http://hdl.handle.net/10945/1539
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        • 1. Thesis and Dissertation Collection, all items

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          Design and simulation of a three-axis stabilized satellite and Kalman filter rate estimator 

          Vitalich, John (Monterey, California. Naval Postgraduate School, 2003);
          Design requirements for a small satellite (NPSAT-1) Attitude Determination and Control Subsystem (ADCS) is a three-axis stabilized spacecraft which requires a control attitude of +/- 1.0 degrees and knowledge attitude of ...
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          Aerodynamic Three-Axis Attitude Stabilization of a Spacecraft by Center-of-Mass Shifting 

          Chesi, Simone; Gong, Qi; Romano, Marcello (American Institute of Aeronautics and Astronautics, Inc., 2017);
          This paper proposes a spacecraft attitude control technique based on the use of center-of-mass shifting. In particular, the position vector of the spacecraft’s center of pressure with respect to the center of mass is ...
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