Electrical Power and Propulsion System Architecture for a 75 Kg Microsatellite Hall-effect Thruster

Gedlu Solomon; Michael Ayele

doi:doi:10.11648/j.ijass.20251304.11

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Electrical Power and Propulsion System Architecture for a 75 Kg Microsatellite Hall-effect Thruster

Gedlu Solomon^*

, Michael Ayele

Published in International Journal of Astrophysics and Space Science (Volume 13, Issue 4)

Received: 4 December 2025 Accepted: 15 December 2025 Published: 29 December 2025

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Abstract

This paper presents a comprehensive system-level design for the electrical power and electric propulsion subsystems in microsatellites. The study begins with an overview of the subsystems typically integrated into microsatellite platforms, before focusing in greater detail on electrical power distribution and electric propulsion. Particular attention is given to the Hall Effect Thruster (HET), including its operating principle, advantages, and inherent limitations. A three-year mission scenario is considered to estimate annual velocity changes and corresponding power requirements, providing a realistic operational framework. The analysis incorporates orbital mechanics by examining the relationship between the Sun and satellite in terms of Earth’s radius, gravitational constant, mass, and eclipse duration. Satellite velocity is calculated across different orbital geometries, with additional consideration of drag forces that may arise in low Earth orbit. Building on this foundation, the paper concentrates on the design of a miniaturized HET tailored for a 75 kg satellite operating in a 1000 km circular orbit. Key design parameters such as thrust requirements, power demands, propellant selection, and component sizing are systematically evaluated. The proposed system enables small-scale orbital maneuvers through continuous monitoring of orbital velocity and feedback-based corrections. Furthermore, the paper details strategies for power distribution among subsystems and identifies the fundamental components required for implementation. By integrating propulsion and power considerations at the system level, the study demonstrates a viable pathway for enhancing the autonomy and maneuverability of microsatellites in extended missions.

Published in	International Journal of Astrophysics and Space Science (Volume 13, Issue 4)
DOI	10.11648/j.ijass.20251304.11
Page(s)	113-126
Creative Commons	This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.
Copyright	Copyright © The Author(s), 2025. Published by Science Publishing Group

Keywords

Microsatellite, Hall Effect Trust, Velocity Maneuvers, Eclipse Cycles, Xenon

References

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[2]	Sandau (2010) – Acta Astronautica R. Sandau, “Status and trends of small satellite missions for Earth observation,” Acta Astronautica, vol. 66, no. 1–2, pp. 1–12, 2010, https://doi.org/10.1016/j.actaastro.2009.06.008
[3]	Bouwmeester & Guo (2010) – Acta Astronautica J. Bouwmeester and J. Guo, “Survey of worldwide pico- and nanosatellite missions, distributions and subsystems,” Acta Astronautica, vol. 67, no. 7–8, pp. 854–862, 2010, https://doi.org/10.1016/j.actaastro.2010.06.004
[4]	Kim et al. (2012) – Acta Astronautica H. Kim, J. Park, H. Lee, J. Lee, and M. Cho, “Electrical power system design for a micro-satellite: Solar array, battery, and power management considerations,” Acta Astronautica, vol. 81, no. 2, pp. 618–627, 2012, https://doi.org/10.1016/j.actaastro.2012.05.005
[5]	Babu, Raj & Menon (2017) – Journal of Spacecraft and Rockets S. Babu, B. Raj, and R. Menon, “Design and development of an electrical power system for small satellites,” Journal of Spacecraft and Rockets, vol. 54, no. 4, pp. 879–888, 2017, https://doi.org/10.2514/1.A34043
[6]	Messenger et al. (1997) – Progress in Photovoltaics S. R. Messenger, R. J. Walters, G. P. Summers, and B. E. Anspaugh, “Modeling solar cell degradation in space: A comparison of methods,” Progress in Photovoltaics: Research and Applications, vol. 5, no. 1, pp. 55–66, 1997, https://doi.org/10.1002/(SICI)1099-159X(199701/02)5:1
[7]	Choueiri (2001) – Journal of Plasma Physics E. Y. Choueiri, “Fundamental aspects of the Hall thruster,” Journal of Plasma Physics, vol. 67, no. 6, pp. 581–607, 2001, https://doi.org/10.1017/S0022377801006069
[8]	Wertz & Larson (2011) – Space Mission Engineering: The New SMAD J. R. Wertz and W. J. Larson, Space Mission Engineering: The New SMAD, Microcosm Press, 2011.
[9]	Sumanth (2019) – International Journal of Aviation, Aeronautics and Aerospace S. R. M. Sumanth, “Computation of eclipse time for low Earth orbiting small satellites,” International Journal of Aviation, Aeronautics and Aerospace, vol. 6, no. 5, 2019.
[10]	Kim et al. (2009 IEPC) – IEPC Proceedings Y. Kim et al., “Development of Xenon feed system for a 300 W Hall effect Thruster,” in 31st International Electric Propulsion Conference, Ann Arbor, MI, USA, Sept. 2009.
[11]	AST Advanced Space Technologies (2013) AST Advanced Space Technologies GmbH, “µFCU – A miniaturized flow control unit for xenon,” IEPC 2013-227, 33rd International Electric Propulsion Conference, 2013.
[12]	Nguyen & Fraction (2016 SmallSat) H. Nguyen and J. Fraction, “Robust, radiation tolerant command and data handling and power system electronics for small satellites,” Proceedings of the SmallSat Conference, NASA Goddard, 2016.
[13]	Bekhti, Bensaada & Beldjehem (2020) – The Aeronautical Journal M. Bekhti, M. Bensaada, and M. Beldjehem, “Design and implementation of a power distribution system adopting over-current protection,” The Aeronautical Journal, vol. 124, no. 1281, pp. 1789–1797, Nov. 2020, https://doi.org/10.1017/S0001924000016273
[14]	Sun, Han & Chen (2017) – arXiv Preprint C. Sun, C. Han, and P. Chen, “Real-time kinematic positioning of LEO satellites using a single frequency GPS receiver,” arXiv: 1704. Apr. 2017. (Preprint — use arXiv identifier once confirmed.)
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APA Style

Solomon, G., Ayele, M. (2025). Electrical Power and Propulsion System Architecture for a 75 Kg Microsatellite Hall-effect Thruster. International Journal of Astrophysics and Space Science, 13(4), 113-126. https://doi.org/10.11648/j.ijass.20251304.11

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ACS Style

Solomon, G.; Ayele, M. Electrical Power and Propulsion System Architecture for a 75 Kg Microsatellite Hall-effect Thruster. Int. J. Astrophys. Space Sci. 2025, 13(4), 113-126. doi: 10.11648/j.ijass.20251304.11

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AMA Style

Solomon G, Ayele M. Electrical Power and Propulsion System Architecture for a 75 Kg Microsatellite Hall-effect Thruster. Int J Astrophys Space Sci. 2025;13(4):113-126. doi: 10.11648/j.ijass.20251304.11

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@article{10.11648/j.ijass.20251304.11,
  author = {Gedlu Solomon and Michael Ayele},
  title = {Electrical Power and Propulsion System Architecture for a 75 Kg Microsatellite Hall-effect Thruster},
  journal = {International Journal of Astrophysics and Space Science},
  volume = {13},
  number = {4},
  pages = {113-126},
  doi = {10.11648/j.ijass.20251304.11},
  url = {https://doi.org/10.11648/j.ijass.20251304.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijass.20251304.11},
  abstract = {This paper presents a comprehensive system-level design for the electrical power and electric propulsion subsystems in microsatellites. The study begins with an overview of the subsystems typically integrated into microsatellite platforms, before focusing in greater detail on electrical power distribution and electric propulsion. Particular attention is given to the Hall Effect Thruster (HET), including its operating principle, advantages, and inherent limitations. A three-year mission scenario is considered to estimate annual velocity changes and corresponding power requirements, providing a realistic operational framework. The analysis incorporates orbital mechanics by examining the relationship between the Sun and satellite in terms of Earth’s radius, gravitational constant, mass, and eclipse duration. Satellite velocity is calculated across different orbital geometries, with additional consideration of drag forces that may arise in low Earth orbit. Building on this foundation, the paper concentrates on the design of a miniaturized HET tailored for a 75 kg satellite operating in a 1000 km circular orbit. Key design parameters such as thrust requirements, power demands, propellant selection, and component sizing are systematically evaluated. The proposed system enables small-scale orbital maneuvers through continuous monitoring of orbital velocity and feedback-based corrections. Furthermore, the paper details strategies for power distribution among subsystems and identifies the fundamental components required for implementation. By integrating propulsion and power considerations at the system level, the study demonstrates a viable pathway for enhancing the autonomy and maneuverability of microsatellites in extended missions.},
 year = {2025}
}

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TY  - JOUR
T1  - Electrical Power and Propulsion System Architecture for a 75 Kg Microsatellite Hall-effect Thruster
AU  - Gedlu Solomon
AU  - Michael Ayele
Y1  - 2025/12/29
PY  - 2025
N1  - https://doi.org/10.11648/j.ijass.20251304.11
DO  - 10.11648/j.ijass.20251304.11
T2  - International Journal of Astrophysics and Space Science
JF  - International Journal of Astrophysics and Space Science
JO  - International Journal of Astrophysics and Space Science
SP  - 113
EP  - 126
PB  - Science Publishing Group
SN  - 2376-7022
UR  - https://doi.org/10.11648/j.ijass.20251304.11
AB  - This paper presents a comprehensive system-level design for the electrical power and electric propulsion subsystems in microsatellites. The study begins with an overview of the subsystems typically integrated into microsatellite platforms, before focusing in greater detail on electrical power distribution and electric propulsion. Particular attention is given to the Hall Effect Thruster (HET), including its operating principle, advantages, and inherent limitations. A three-year mission scenario is considered to estimate annual velocity changes and corresponding power requirements, providing a realistic operational framework. The analysis incorporates orbital mechanics by examining the relationship between the Sun and satellite in terms of Earth’s radius, gravitational constant, mass, and eclipse duration. Satellite velocity is calculated across different orbital geometries, with additional consideration of drag forces that may arise in low Earth orbit. Building on this foundation, the paper concentrates on the design of a miniaturized HET tailored for a 75 kg satellite operating in a 1000 km circular orbit. Key design parameters such as thrust requirements, power demands, propellant selection, and component sizing are systematically evaluated. The proposed system enables small-scale orbital maneuvers through continuous monitoring of orbital velocity and feedback-based corrections. Furthermore, the paper details strategies for power distribution among subsystems and identifies the fundamental components required for implementation. By integrating propulsion and power considerations at the system level, the study demonstrates a viable pathway for enhancing the autonomy and maneuverability of microsatellites in extended missions.
VL  - 13
IS  - 4
ER  -

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Author Information

Gedlu Solomon

Department ofAerospace Engineering, Space Science and Geospatial Institute, Addis Ababa, Ethiopia

Contact Email

http://orcid.org/0009-0001-6024-0685
Michael Ayele

Department ofAerospace Engineering, Addis Ababa Science and Technology University, Addis Ababa, Ethiopia

Contact Email

http://orcid.org/0009-0008-1432-036X

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APA Style

Solomon, G., Ayele, M. (2025). Electrical Power and Propulsion System Architecture for a 75 Kg Microsatellite Hall-effect Thruster. International Journal of Astrophysics and Space Science, 13(4), 113-126. https://doi.org/10.11648/j.ijass.20251304.11

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ACS Style

Solomon, G.; Ayele, M. Electrical Power and Propulsion System Architecture for a 75 Kg Microsatellite Hall-effect Thruster. Int. J. Astrophys. Space Sci. 2025, 13(4), 113-126. doi: 10.11648/j.ijass.20251304.11

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AMA Style

Solomon G, Ayele M. Electrical Power and Propulsion System Architecture for a 75 Kg Microsatellite Hall-effect Thruster. Int J Astrophys Space Sci. 2025;13(4):113-126. doi: 10.11648/j.ijass.20251304.11

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@article{10.11648/j.ijass.20251304.11,
  author = {Gedlu Solomon and Michael Ayele},
  title = {Electrical Power and Propulsion System Architecture for a 75 Kg Microsatellite Hall-effect Thruster},
  journal = {International Journal of Astrophysics and Space Science},
  volume = {13},
  number = {4},
  pages = {113-126},
  doi = {10.11648/j.ijass.20251304.11},
  url = {https://doi.org/10.11648/j.ijass.20251304.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijass.20251304.11},
  abstract = {This paper presents a comprehensive system-level design for the electrical power and electric propulsion subsystems in microsatellites. The study begins with an overview of the subsystems typically integrated into microsatellite platforms, before focusing in greater detail on electrical power distribution and electric propulsion. Particular attention is given to the Hall Effect Thruster (HET), including its operating principle, advantages, and inherent limitations. A three-year mission scenario is considered to estimate annual velocity changes and corresponding power requirements, providing a realistic operational framework. The analysis incorporates orbital mechanics by examining the relationship between the Sun and satellite in terms of Earth’s radius, gravitational constant, mass, and eclipse duration. Satellite velocity is calculated across different orbital geometries, with additional consideration of drag forces that may arise in low Earth orbit. Building on this foundation, the paper concentrates on the design of a miniaturized HET tailored for a 75 kg satellite operating in a 1000 km circular orbit. Key design parameters such as thrust requirements, power demands, propellant selection, and component sizing are systematically evaluated. The proposed system enables small-scale orbital maneuvers through continuous monitoring of orbital velocity and feedback-based corrections. Furthermore, the paper details strategies for power distribution among subsystems and identifies the fundamental components required for implementation. By integrating propulsion and power considerations at the system level, the study demonstrates a viable pathway for enhancing the autonomy and maneuverability of microsatellites in extended missions.},
 year = {2025}
}

Copy | Download

TY  - JOUR
T1  - Electrical Power and Propulsion System Architecture for a 75 Kg Microsatellite Hall-effect Thruster
AU  - Gedlu Solomon
AU  - Michael Ayele
Y1  - 2025/12/29
PY  - 2025
N1  - https://doi.org/10.11648/j.ijass.20251304.11
DO  - 10.11648/j.ijass.20251304.11
T2  - International Journal of Astrophysics and Space Science
JF  - International Journal of Astrophysics and Space Science
JO  - International Journal of Astrophysics and Space Science
SP  - 113
EP  - 126
PB  - Science Publishing Group
SN  - 2376-7022
UR  - https://doi.org/10.11648/j.ijass.20251304.11
AB  - This paper presents a comprehensive system-level design for the electrical power and electric propulsion subsystems in microsatellites. The study begins with an overview of the subsystems typically integrated into microsatellite platforms, before focusing in greater detail on electrical power distribution and electric propulsion. Particular attention is given to the Hall Effect Thruster (HET), including its operating principle, advantages, and inherent limitations. A three-year mission scenario is considered to estimate annual velocity changes and corresponding power requirements, providing a realistic operational framework. The analysis incorporates orbital mechanics by examining the relationship between the Sun and satellite in terms of Earth’s radius, gravitational constant, mass, and eclipse duration. Satellite velocity is calculated across different orbital geometries, with additional consideration of drag forces that may arise in low Earth orbit. Building on this foundation, the paper concentrates on the design of a miniaturized HET tailored for a 75 kg satellite operating in a 1000 km circular orbit. Key design parameters such as thrust requirements, power demands, propellant selection, and component sizing are systematically evaluated. The proposed system enables small-scale orbital maneuvers through continuous monitoring of orbital velocity and feedback-based corrections. Furthermore, the paper details strategies for power distribution among subsystems and identifies the fundamental components required for implementation. By integrating propulsion and power considerations at the system level, the study demonstrates a viable pathway for enhancing the autonomy and maneuverability of microsatellites in extended missions.
VL  - 13
IS  - 4
ER  -

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