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.
|Title of host publication||2021 American Control Conference, ACC 2021|
|Number of pages||6|
|State||Published - May 25 2021|
|Event||2021 American Control Conference, ACC 2021 - Virtual, New Orleans, United States|
Duration: May 25 2021 → May 28 2021
|Name||Proceedings of the American Control Conference|
|Conference||2021 American Control Conference, ACC 2021|
|City||Virtual, New Orleans|
|Period||5/25/21 → 5/28/21|
Bibliographical noteFunding Information:
This work is supported in part by the National Aeronautics and Space Administration (80NSSC17M0040) and the National Science Foundation (CMMI-1538782).
© 2021 American Automatic Control Council.
ASJC Scopus subject areas
- Electrical and Electronic Engineering