Solar Arrays and Battery Power Sources Conceptual Design for Low Earth Orbit Microsatellites

Mohammed Bekhti; Messaoud Bensaada

doi:doi:10.11648/j.eas.20200503.13

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Solar Arrays and Battery Power Sources Conceptual Design for Low Earth Orbit Microsatellites

Mohammed Bekhti, Messaoud Bensaada

Published in Engineering and Applied Sciences (Volume 5, Issue 3)

Received: 27 November 2019 Accepted: 31 March 2020 Published: 28 June 2020

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Abstract

The power system is a vital subsystem in a spacecraft. As long as the spacecraft has power, it can perform its mission. Almost all other failures can be worked out by ground operations from ground stations but a power loss is very fatal for the spacecraft. In the early years of spaceflight, the power system was also the limiting factor in any mission duration. Many studies show that solar cell power (short-circuit current and open-circuit voltage) are degraded by space environment radiation. The power system is designed such that the end of life (EOL) power is adequate for the mission’s requirements. Beginning of life (BOL) power is set by the estimate of the radiation damage over the spacecraft’s lifetime. It is well known in the literature, the radiation damage to solar cells is caused by high-energy protons from solar flares and from trapped electrons in the Van Allen belt. The purpose of this paper is to investigate the power system design trades involved in the mission analysis of a low earth orbit (LEO) satellite at an altitude of 700 km. Based on the power requirements of the payload and the constant power requirements for the remainder of the spacecraft (platform subsystems), the solar arrays and batteries for the spacecraft will be sized.

Published in	Engineering and Applied Sciences (Volume 5, Issue 3) This article belongs to the Special Issue Research on Emerging Technologies in Design and Manufacturing
DOI	10.11648/j.eas.20200503.13
Page(s)	66-70
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), 2024. Published by Science Publishing Group

Keywords

Eclipse Time, Solar Arrays, Battery, Battery Capacity, Nickel-Cadmium, Lithium Ion, Nickel Metal Hydride, Primary Source, Gallium Arsenide, Solar Cells Efficiency, Fill Factor

References

[1]	M. N. Ismail, A. Bakry, H. H. Selim, M. H. Shehata, ‘Eclipse intervals for satellites in circular orbit under the effects of earth’s oblateness and solar radiation pressure’, NRIAG Journal of Astronomy and Geophysics, Volume 4, Issue 1, June 2015, Pages 117-122. https://doi.org/10.1016/j.nrjag.2015.06.001
[2]	Jonas Holtstiege, Bsc. Thesis: Orbit analysis for the satellite mission BOOST March 16, 2016. ZARM/ University of Bremen.
[3]	Anigstein P. A. and Peña R. S., 1998. Analysis of Solar Panel Orientation in Low Altitude Satellites. IEEE Transactions on Aerospace and Electronic Systems, Vol. 34, No. 2, IEEE.
[4]	Kostolanskŷ E., 2002. On the Duration of the Total Eclipse of a Satellite of a Body. IMA Journal of Applied Mathematics, 67 (4), p. 401-410.
[5]	David G. Gilmore, Spacecraft Thermal Control Handbook-Second Edition AIAA (American Institute of Aeronautics and Astronautics); December 15, 2002.
[6]	Satellite Power Systems Solar Energy Used in Space Technology Programs, 2003. European Space Agency, ESA Publications Division, Netherlands, BR-202.
[7]	Pitchaimani M., Ganesh T. S., Soma P. and Shivakumar S. K., 2006. Strategies for Enhancing Power Generation in Satellites with Large Local Time Angles, SpaceOps 2006 Conference Paper, American Institute of Aeronautics and Astronautics, pp. 1-7.
[8]	Larson, W. J. and Wertz J. R., 1992. Space Mission Analysis and Design, 2nd Edition. Microcosm, Inc. Torrance, California.
[9]	Fortescue, P. W., Stark J. and Swinerd G., ‘Power System Design. Spacecraft System Engineering’, 3rd Edition, Wiley Intl, 2003.
[10]	Patel, M. R., ‘Spacecraft Power Systems’, CRC Press, Florida, 2005.
[11]	Pisacane, V. L, ‘Fundamentals of Space Systems’, 2nd Edition. Oxford University Press, NY, 2005.
[12]	Wenige, R., Schilbach, M., Weidner, P. F., ‘Power Storage for small satellites: Comparison of NiH₂ and Li Ion batteries’, IAA-B5-1103, pp. 395-399.
[13]	M. Bekhti, “Design and Qualification Tests of the Alsat-1 High Efficiency Solar Panels”, International Journal of Renewable Energy Research, Vol. 3, No. 1, 2013.
[14]	M. Bekhti, “Radiation Analysis of InGaP/GaAs/Ge and GaAs/Ge Solar Cell: A comparative Study”, International Journal of Renewable Energy Research, Vol. 3, No. 4, 2013.
[15]	M. Bekhti, “In Orbit Irradiation Effects Evaluation of the Alsat-1 Solar Panels’, International Journal of Energy Science and Engineering, Vol. 1, No. 1, 2015, pp. 24-30.
[16]	HadjDida, M. Bekhti, “Study, Modeling and Simulation of the Electrical Characteristics of Space Satellite Solar Cells”, 6^th International Conference on Renewable Energy Research and Applications, San Diego, November 5-8, 2017. 978-1-5386-2095-3/17/$31.00 ©2017 IEEE
[17]	Hadj Dida, M. Bourahla, H. B Ertan, M. Bekhti, “Analytical Modelling, Simulation and Comparative Study of Multi-Junction Solar Cells Efficiency, International Journal of Renewable Energy Research, Vol. 8, No. 4, December, 2018.

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APA Style

Mohammed Bekhti, Messaoud Bensaada. (2020). Solar Arrays and Battery Power Sources Conceptual Design for Low Earth Orbit Microsatellites. Engineering and Applied Sciences, 5(3), 66-70. https://doi.org/10.11648/j.eas.20200503.13

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ACS Style

Mohammed Bekhti; Messaoud Bensaada. Solar Arrays and Battery Power Sources Conceptual Design for Low Earth Orbit Microsatellites. Eng. Appl. Sci. 2020, 5(3), 66-70. doi: 10.11648/j.eas.20200503.13

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AMA Style

Mohammed Bekhti, Messaoud Bensaada. Solar Arrays and Battery Power Sources Conceptual Design for Low Earth Orbit Microsatellites. Eng Appl Sci. 2020;5(3):66-70. doi: 10.11648/j.eas.20200503.13

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@article{10.11648/j.eas.20200503.13,
  author = {Mohammed Bekhti and Messaoud Bensaada},
  title = {Solar Arrays and Battery Power Sources Conceptual Design for Low Earth Orbit Microsatellites},
  journal = {Engineering and Applied Sciences},
  volume = {5},
  number = {3},
  pages = {66-70},
  doi = {10.11648/j.eas.20200503.13},
  url = {https://doi.org/10.11648/j.eas.20200503.13},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.eas.20200503.13},
  abstract = {The power system is a vital subsystem in a spacecraft. As long as the spacecraft has power, it can perform its mission. Almost all other failures can be worked out by ground operations from ground stations but a power loss is very fatal for the spacecraft. In the early years of spaceflight, the power system was also the limiting factor in any mission duration. Many studies show that solar cell power (short-circuit current and open-circuit voltage) are degraded by space environment radiation. The power system is designed such that the end of life (EOL) power is adequate for the mission’s requirements. Beginning of life (BOL) power is set by the estimate of the radiation damage over the spacecraft’s lifetime. It is well known in the literature, the radiation damage to solar cells is caused by high-energy protons from solar flares and from trapped electrons in the Van Allen belt. The purpose of this paper is to investigate the power system design trades involved in the mission analysis of a low earth orbit (LEO) satellite at an altitude of 700 km. Based on the power requirements of the payload and the constant power requirements for the remainder of the spacecraft (platform subsystems), the solar arrays and batteries for the spacecraft will be sized.},
 year = {2020}
}

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TY - JOUR
T1 - Solar Arrays and Battery Power Sources Conceptual Design for Low Earth Orbit Microsatellites
AU - Mohammed Bekhti
AU - Messaoud Bensaada
Y1 - 2020/06/28
PY - 2020
N1 - https://doi.org/10.11648/j.eas.20200503.13
DO - 10.11648/j.eas.20200503.13
T2 - Engineering and Applied Sciences
JF - Engineering and Applied Sciences
JO - Engineering and Applied Sciences
SP - 66
EP - 70
PB - Science Publishing Group
SN - 2575-1468
UR - https://doi.org/10.11648/j.eas.20200503.13
AB - The power system is a vital subsystem in a spacecraft. As long as the spacecraft has power, it can perform its mission. Almost all other failures can be worked out by ground operations from ground stations but a power loss is very fatal for the spacecraft. In the early years of spaceflight, the power system was also the limiting factor in any mission duration. Many studies show that solar cell power (short-circuit current and open-circuit voltage) are degraded by space environment radiation. The power system is designed such that the end of life (EOL) power is adequate for the mission’s requirements. Beginning of life (BOL) power is set by the estimate of the radiation damage over the spacecraft’s lifetime. It is well known in the literature, the radiation damage to solar cells is caused by high-energy protons from solar flares and from trapped electrons in the Van Allen belt. The purpose of this paper is to investigate the power system design trades involved in the mission analysis of a low earth orbit (LEO) satellite at an altitude of 700 km. Based on the power requirements of the payload and the constant power requirements for the remainder of the spacecraft (platform subsystems), the solar arrays and batteries for the spacecraft will be sized.
VL - 5
IS - 3
ER -

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Author Information

Mohammed Bekhti

Algerian Space Agency, Centre for Satellites Development, Research Department in Space Instrumentation, Oran, Algeria
Messaoud Bensaada

Algerian Space Agency, Centre for Satellites Development, Research Department in Space Instrumentation, Oran, Algeria

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APA Style

Mohammed Bekhti, Messaoud Bensaada. (2020). Solar Arrays and Battery Power Sources Conceptual Design for Low Earth Orbit Microsatellites. Engineering and Applied Sciences, 5(3), 66-70. https://doi.org/10.11648/j.eas.20200503.13

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ACS Style

Mohammed Bekhti; Messaoud Bensaada. Solar Arrays and Battery Power Sources Conceptual Design for Low Earth Orbit Microsatellites. Eng. Appl. Sci. 2020, 5(3), 66-70. doi: 10.11648/j.eas.20200503.13

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AMA Style

Mohammed Bekhti, Messaoud Bensaada. Solar Arrays and Battery Power Sources Conceptual Design for Low Earth Orbit Microsatellites. Eng Appl Sci. 2020;5(3):66-70. doi: 10.11648/j.eas.20200503.13

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@article{10.11648/j.eas.20200503.13,
  author = {Mohammed Bekhti and Messaoud Bensaada},
  title = {Solar Arrays and Battery Power Sources Conceptual Design for Low Earth Orbit Microsatellites},
  journal = {Engineering and Applied Sciences},
  volume = {5},
  number = {3},
  pages = {66-70},
  doi = {10.11648/j.eas.20200503.13},
  url = {https://doi.org/10.11648/j.eas.20200503.13},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.eas.20200503.13},
  abstract = {The power system is a vital subsystem in a spacecraft. As long as the spacecraft has power, it can perform its mission. Almost all other failures can be worked out by ground operations from ground stations but a power loss is very fatal for the spacecraft. In the early years of spaceflight, the power system was also the limiting factor in any mission duration. Many studies show that solar cell power (short-circuit current and open-circuit voltage) are degraded by space environment radiation. The power system is designed such that the end of life (EOL) power is adequate for the mission’s requirements. Beginning of life (BOL) power is set by the estimate of the radiation damage over the spacecraft’s lifetime. It is well known in the literature, the radiation damage to solar cells is caused by high-energy protons from solar flares and from trapped electrons in the Van Allen belt. The purpose of this paper is to investigate the power system design trades involved in the mission analysis of a low earth orbit (LEO) satellite at an altitude of 700 km. Based on the power requirements of the payload and the constant power requirements for the remainder of the spacecraft (platform subsystems), the solar arrays and batteries for the spacecraft will be sized.},
 year = {2020}
}

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