Authors : A. Ogohi; I. C. Awe; Ali M. Mohammed; S. S. Wambai; M. A. Babayo

Volume/Issue : Volume 11 - 2026, Issue 4 - April

Google Scholar : https://tinyurl.com/3p7b36pv

Scribd : https://tinyurl.com/yaycf4tr

DOI : https://doi.org/10.38124/ijisrt/26apr1885

Note : A published paper may take 4-5 working days from the publication date to appear in PlumX Metrics, Semantic Scholar, and ResearchGate.

Abstract : Magnetorquers are essential components of CubeSat attitude determination and control systems (ADCS) due to their low mass, simplicity, and reliability. However, their effectiveness is strongly limited by the stringent power budgets typical of nanosatellite platforms, creating a trade-off between achievable magnetic moment and power consumption. This study addresses the challenge of improving the magnetic moment-to-power ratio in CubeSat magnetorquers through the use of ferromagnetic core enhancement. The goal is to design and optimize a magnetorquer capable of achieving a target magnetic moment of 0.25 A·m² under a strict power constraint of 0.8 W. The methodology combines analytical modeling of magnetic dipole generation with electrical power constraints and practical design considerations, including the use of AWG 32 enamel-coated copper wire, moderate coil turns, and a high-permeability soft ferromagnetic core. A prototype device was designed and evaluated to validate the theoretical model. Results show that the air-core configuration produces a magnetic moment of approximately 0.15 A·m² at an operating current of 0.12 A, while the introduction of a ferromagnetic core enhances the effective magnetic moment to between 0.28 and 0.32 A·m² without exceeding the specified power limit. This represents a significant improvement in magnetic efficiency. The scientific novelty of this work lies in the systematic optimization of the magnetic moment-to-power ratio under realistic CubeSat constraints, incorporating both electromagnetic and thermal considerations. The practical value is demonstrated through a low-cost, energy-efficient design suitable for deployment in resource-constrained small satellite missions, particularly in emerging space programs.

Keywords : CubeSat, Magnetorquer, Optimization, Magnetic Moment, Power Efficiency, Ferromagnetic Core, ADCS, Nanosatellite.

References :

1. J. R. Wertz, D. F. Everett, and J. J. Puschell, Space Mission Engineering: The New SMAD. Microcosm Press, 2011.
2. M. A. Peck and J. F. McNutt, “CubeSat-based science missions: A review and outlook,” Acta Astronautica, vol. 123, pp. 1–12, 2016.
3. S. B. Gabriel and R. C. Olsen, “Magnetorquer-based attitude control for small satellites,” IEEE Aerospace and Electronic Systems Magazine, vol. 29, no. 7, pp. 34–42, 2014.
4. P. Fortescue, G. Swinerd, and J. Stark, Spacecraft Systems Engineering, 4th ed. Wiley, 2011.
5. D. Wertz and W. Larson, Space Mission Analysis and Design, 3rd ed. Microcosm Press, 1999.
6. J. Puig-Suari, C. Turner, and W. Ahlgren, “Development of the CubeSat standard,” AIAA/USU Small Satellite Conference, 2001.
7. J. P. Wilken, “Magnetic materials for small satellite attitude control systems,” Journal of Spacecraft and Rockets, vol. 52, no. 3, pp. 845–852, 2015.
8. J. R. Wertz, Spacecraft Attitude Determination and Control. Springer, 1978.
9. P. C. Hughes, Spacecraft Attitude Dynamics. Dover Publications, 2004.
10. N. Lee and H. Bang, “Optimal design of magnetorquers for nanosatellite attitude control,” Aerospace Science and Technology, vol. 54, pp. 1–10, 2016.
11. M. Romano, S. Silvestrini, and G. S. Rossi, “Magnetic attitude control systems for CubeSats: A review,” Progress in Aerospace Sciences, vol. 91, pp. 1–20, 2017.
12. R. M. Miranda and M. R. R. Alves, “Design and testing of CubeSat magnetorquers,” Acta Astronautica, vol. 145, pp. 90–102, 2018.