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Conference Paper/Proceeding/Abstract 357 views 91 downloads

Design and Thermal Analysis of Power Harvesting System of a Hexagonal Shaped Small Spacecraft

Mansa Radhakrishnan, Anwar Ali Orcid Logo, Muhammad Rizwan Mughal

World Academy of Science, Engineering and Technology, Volume: 19, Issue: 2

Swansea University Author: Anwar Ali Orcid Logo

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Abstract

Many universities around the world are working on modular and low budget architecture of small spacecraft to reduce the development cost of the overall system. This paper focuses on the design of a modular solar power harvesting system for a hexagonalshaped small satellite. The designed solar power...

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Published in: World Academy of Science, Engineering and Technology
Published: 2025
URI: https://cronfa.swan.ac.uk/Record/cronfa70060
first_indexed 2025-07-30T12:40:14Z
last_indexed 2025-09-05T06:12:38Z
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spelling 2025-09-04T15:16:40.2192660 v2 70060 2025-07-30 Design and Thermal Analysis of Power Harvesting System of a Hexagonal Shaped Small Spacecraft f206105e1de57bebba0fd04fe9870779 0000-0001-7366-9002 Anwar Ali Anwar Ali true false 2025-07-30 ACEM Many universities around the world are working on modular and low budget architecture of small spacecraft to reduce the development cost of the overall system. This paper focuses on the design of a modular solar power harvesting system for a hexagonalshaped small satellite. The designed solar power harvesting systems are composed of solar panels and power converter subsystems. Thesolar panel is composed of solar cells mounted on the external face of the printed circuit board (PCB), while the electronic components of power conversion are mounted on the interior side of the same PCB. The solar panel with dimensions 16.5 cm × 99 cm is composed of 36 solar cells (each solar cell is 4 cm × 7 cm) divided into four parallel banks where each bank consists of 9 solar cells. The output voltage of a single solar cell is 2.14V, and the combined output voltage of 9 series connected solar cells is around 19.3V. The output voltage of the solar panel is boosted to the satellite power distribution bus voltage level (28V) by a boost converter working on a constant voltage maximum power point tracking (MPPT) technique. The solar panel module is an eight-layer PCB having embedded coil in 4 internal layers. This coil is used to control the attitude of the spacecraft, which consumes power to generate a magnetic field and rotate the spacecraft. As power converter and distribution subsystem components are mounted on the PCB internal layer, therefore it is mandatory to do thermal analysis in order to ensure that the overall module temperature is within thermal safety limits. The main focus of the overall desig Conference Paper/Proceeding/Abstract World Academy of Science, Engineering and Technology 19 2 30 7 2025 2025-07-30 COLLEGE NANME Aerospace, Civil, Electrical, and Mechanical Engineering COLLEGE CODE ACEM Swansea University 2025-09-04T15:16:40.2192660 2025-07-30T13:28:56.6570059 Faculty of Science and Engineering School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Electronic and Electrical Engineering Mansa Radhakrishnan 1 Anwar Ali 0000-0001-7366-9002 2 Muhammad Rizwan Mughal 3 70060__34873__757b44353ea34943bee5a7ddc4165fe7.pdf 70060.pdf 2025-07-30T13:34:51.7820866 Output 969018 application/pdf Version of Record true Released under the terms of a Creative Commons Attribution 4.0 International License. true eng https://creativecommons.org/licenses/by/4.0/
title Design and Thermal Analysis of Power Harvesting System of a Hexagonal Shaped Small Spacecraft
spellingShingle Design and Thermal Analysis of Power Harvesting System of a Hexagonal Shaped Small Spacecraft
Anwar Ali
title_short Design and Thermal Analysis of Power Harvesting System of a Hexagonal Shaped Small Spacecraft
title_full Design and Thermal Analysis of Power Harvesting System of a Hexagonal Shaped Small Spacecraft
title_fullStr Design and Thermal Analysis of Power Harvesting System of a Hexagonal Shaped Small Spacecraft
title_full_unstemmed Design and Thermal Analysis of Power Harvesting System of a Hexagonal Shaped Small Spacecraft
title_sort Design and Thermal Analysis of Power Harvesting System of a Hexagonal Shaped Small Spacecraft
author_id_str_mv f206105e1de57bebba0fd04fe9870779
author_id_fullname_str_mv f206105e1de57bebba0fd04fe9870779_***_Anwar Ali
author Anwar Ali
author2 Mansa Radhakrishnan
Anwar Ali
Muhammad Rizwan Mughal
format Conference Paper/Proceeding/Abstract
container_title World Academy of Science, Engineering and Technology
container_volume 19
container_issue 2
publishDate 2025
institution Swansea University
college_str Faculty of Science and Engineering
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hierarchy_top_id facultyofscienceandengineering
hierarchy_top_title Faculty of Science and Engineering
hierarchy_parent_id facultyofscienceandengineering
hierarchy_parent_title Faculty of Science and Engineering
department_str School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Electronic and Electrical Engineering{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Electronic and Electrical Engineering
document_store_str 1
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description Many universities around the world are working on modular and low budget architecture of small spacecraft to reduce the development cost of the overall system. This paper focuses on the design of a modular solar power harvesting system for a hexagonalshaped small satellite. The designed solar power harvesting systems are composed of solar panels and power converter subsystems. Thesolar panel is composed of solar cells mounted on the external face of the printed circuit board (PCB), while the electronic components of power conversion are mounted on the interior side of the same PCB. The solar panel with dimensions 16.5 cm × 99 cm is composed of 36 solar cells (each solar cell is 4 cm × 7 cm) divided into four parallel banks where each bank consists of 9 solar cells. The output voltage of a single solar cell is 2.14V, and the combined output voltage of 9 series connected solar cells is around 19.3V. The output voltage of the solar panel is boosted to the satellite power distribution bus voltage level (28V) by a boost converter working on a constant voltage maximum power point tracking (MPPT) technique. The solar panel module is an eight-layer PCB having embedded coil in 4 internal layers. This coil is used to control the attitude of the spacecraft, which consumes power to generate a magnetic field and rotate the spacecraft. As power converter and distribution subsystem components are mounted on the PCB internal layer, therefore it is mandatory to do thermal analysis in order to ensure that the overall module temperature is within thermal safety limits. The main focus of the overall desig
published_date 2025-07-30T05:30:22Z
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