Optimized Design and Thermal Analysis of Printed Magnetorquer for Attitude Control of Reconfigurable Nanosatellites

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@article{291cdf3353844aa58092a45fc66b7692,
title = "Optimized Design and Thermal Analysis of Printed Magnetorquer for Attitude Control of Reconfigurable Nanosatellites",
abstract = "Attitude Control System (ACS) is one of the critical subsystems of any spacecraft and typically is in charge of de-tumbling, controlling and orienting the satellite after initial deployment and during the satellite operations. The magnetorquer is a core magnetic attitude control actuator and, therefore, a good choice for nanosatellite attitude stabilization. There are various methods to achieve control torque using the magnetorquer. An innovative design of printed magnetorquer has been proposed for the nanosatellites which is modular, scalable, cost effective, less prone to failure, with reduced harness and power consumption since the traces are printed either on top layer or inner layers of the printed circuit board. The analysis in terms of generated torque with a range of input applied voltages, trace widths, outer and inner-most trace lengths is presented to achieve the optimized design. The optimum operating voltage is selected to generate the desired torque while optimizing the torque to the power ratio. The results of analysis in terms of selection of optimized parameters including torque to power ratio, generated magnetic dipole moment and power consumption have been validated practically on a cubesat panel. The printed magnetorquer configuration is modular which is useful to achieve mission level stabilization requirements. For spin stabilized satellites, the rotation time analysis has been performed using the printed magnetorquer.",
keywords = "Magnetic moments, Attitude control, Magnetic separation, Magnetic cores, Torque, Magnetic multilayers, Space vehicles, printed magnetorquer, attitude control, small satellites, thermal analysis, nanosatellites",
author = "Mughal, {M. R.} and H. Ali and A. Ali and J. Praks and Reyneri, {L. M.}",
year = "2019",
doi = "10.1109/TAES.2019.2933959",
language = "English",
journal = "IEEE Transactions on Aerospace and Electronic Systems",
issn = "0018-9251",

}

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TY - JOUR

T1 - Optimized Design and Thermal Analysis of Printed Magnetorquer for Attitude Control of Reconfigurable Nanosatellites

AU - Mughal, M. R.

AU - Ali, H.

AU - Ali, A.

AU - Praks, J.

AU - Reyneri, L. M.

PY - 2019

Y1 - 2019

N2 - Attitude Control System (ACS) is one of the critical subsystems of any spacecraft and typically is in charge of de-tumbling, controlling and orienting the satellite after initial deployment and during the satellite operations. The magnetorquer is a core magnetic attitude control actuator and, therefore, a good choice for nanosatellite attitude stabilization. There are various methods to achieve control torque using the magnetorquer. An innovative design of printed magnetorquer has been proposed for the nanosatellites which is modular, scalable, cost effective, less prone to failure, with reduced harness and power consumption since the traces are printed either on top layer or inner layers of the printed circuit board. The analysis in terms of generated torque with a range of input applied voltages, trace widths, outer and inner-most trace lengths is presented to achieve the optimized design. The optimum operating voltage is selected to generate the desired torque while optimizing the torque to the power ratio. The results of analysis in terms of selection of optimized parameters including torque to power ratio, generated magnetic dipole moment and power consumption have been validated practically on a cubesat panel. The printed magnetorquer configuration is modular which is useful to achieve mission level stabilization requirements. For spin stabilized satellites, the rotation time analysis has been performed using the printed magnetorquer.

AB - Attitude Control System (ACS) is one of the critical subsystems of any spacecraft and typically is in charge of de-tumbling, controlling and orienting the satellite after initial deployment and during the satellite operations. The magnetorquer is a core magnetic attitude control actuator and, therefore, a good choice for nanosatellite attitude stabilization. There are various methods to achieve control torque using the magnetorquer. An innovative design of printed magnetorquer has been proposed for the nanosatellites which is modular, scalable, cost effective, less prone to failure, with reduced harness and power consumption since the traces are printed either on top layer or inner layers of the printed circuit board. The analysis in terms of generated torque with a range of input applied voltages, trace widths, outer and inner-most trace lengths is presented to achieve the optimized design. The optimum operating voltage is selected to generate the desired torque while optimizing the torque to the power ratio. The results of analysis in terms of selection of optimized parameters including torque to power ratio, generated magnetic dipole moment and power consumption have been validated practically on a cubesat panel. The printed magnetorquer configuration is modular which is useful to achieve mission level stabilization requirements. For spin stabilized satellites, the rotation time analysis has been performed using the printed magnetorquer.

KW - Magnetic moments

KW - Attitude control

KW - Magnetic separation

KW - Magnetic cores

KW - Torque

KW - Magnetic multilayers

KW - Space vehicles

KW - printed magnetorquer

KW - attitude control

KW - small satellites

KW - thermal analysis

KW - nanosatellites

U2 - 10.1109/TAES.2019.2933959

DO - 10.1109/TAES.2019.2933959

M3 - Article

JO - IEEE Transactions on Aerospace and Electronic Systems

JF - IEEE Transactions on Aerospace and Electronic Systems

SN - 0018-9251

ER -

ID: 36197402