Abstract
This paper addresses small-satellite attitude control in the presence of external disturbance torques using internal rotating-mass actuators. Unlike reaction wheels, these rotating-mass actuators cannot perform complete rotations. Instead, their stroke is limited to a radians of total rotation. We present a setpoint tracking control algorithm that uses feedback of the satellite's attitude and angular velocity to determine the control signals, which are the angles of the rotating-mass actuators relative to the satellite's body. This feedback algorithm yields control signals that are continuous but only piecewise-continuously differentiable sinusoids. We analyze the stability and performance of the closed-loop system for the case where no external torque is acting on the satellite. We present three numerical simulations to demonstrate the setpoint tracking attitude controller: i) a satellite in low-Earth orbit neglecting aerodynamic moment; ii) a satellite in low-Earth orbit including aerodynamic moment; and iii) a satellite on an air-bearing on Earth, which results in a moment due to gravity.
Original language | English |
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Title of host publication | 2021 American Control Conference, ACC 2021 |
Pages | 2974-2979 |
Number of pages | 6 |
ISBN (Electronic) | 9781665441971 |
DOIs | |
State | Published - May 25 2021 |
Event | 2021 American Control Conference, ACC 2021 - Virtual, New Orleans, United States Duration: May 25 2021 → May 28 2021 |
Publication series
Name | Proceedings of the American Control Conference |
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Volume | 2021-May |
ISSN (Print) | 0743-1619 |
Conference
Conference | 2021 American Control Conference, ACC 2021 |
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Country/Territory | United States |
City | Virtual, New Orleans |
Period | 5/25/21 → 5/28/21 |
Bibliographical note
Publisher Copyright:© 2021 American Automatic Control Council.
ASJC Scopus subject areas
- Electrical and Electronic Engineering