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), 2020. Published by Science Publishing Group |
Eclipse Time, Solar Arrays, Battery, Battery Capacity, Nickel-Cadmium, Lithium Ion, Nickel Metal Hydride, Primary Source, Gallium Arsenide, Solar Cells Efficiency, Fill Factor
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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
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
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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Download@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}
}
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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