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Modelling aerodynamic drag of a very low earth orbit 1U CubeSat utilising a Boltzmann-BGK approach

JOSEFF STURROCK, Ben Evans Orcid Logo, Zoran Jelic

Advances in Space Research, Volume: 75, Issue: 10, Pages: 7610 - 7623

Swansea University Authors: JOSEFF STURROCK, Ben Evans Orcid Logo, Zoran Jelic

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DOI (Published version): 10.1016/j.asr.2025.03.055

Abstract

The aerodynamic drag of a 1U CubeSat at various Very Low Earth Orbit (VLEO) altitudes and conditions have been investigated utilising an in-house Boltzmann-BGK solver. This region of space has numerous benefits, however significant drag can lead to short satellite lifespans. The analyses focus on de...

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Published in: Advances in Space Research
ISSN: 0273-1177 1879-1948
Published: Elsevier BV 2025
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URI: https://cronfa.swan.ac.uk/Record/cronfa69158
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last_indexed 2025-05-13T09:10:46Z
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spelling 2025-05-12T10:15:23.8177984 v2 69158 2025-03-27 Modelling aerodynamic drag of a very low earth orbit 1U CubeSat utilising a Boltzmann-BGK approach a03192b176ce931d0a1c52c2e2ac12e4 JOSEFF STURROCK JOSEFF STURROCK true false 3d273fecc8121fe6b53b8fe5281b9c97 0000-0003-3662-9583 Ben Evans Ben Evans true false 448489404aff5092df63279248ba3415 Zoran Jelic Zoran Jelic true false 2025-03-27 The aerodynamic drag of a 1U CubeSat at various Very Low Earth Orbit (VLEO) altitudes and conditions have been investigated utilising an in-house Boltzmann-BGK solver. This region of space has numerous benefits, however significant drag can lead to short satellite lifespans. The analyses focus on determining drag coefficients, as well as absolute drag values. Flow fields are illustrated. Monoatomic oxygen number density ratios on exposed surfaces were presented to help guide corrosion analysis. Material properties for satellite surface coatings have been analysed, including drag reduction performance. All atmospheric parameters were sourced from NASA’s NRLMSIS 2.0 atmospheric model. Altitudes investigated range from 50 km to 500 km. Periods of solar minima and maxima, seasonal variances and local day/night cases were investigated. Drag coefficients were evaluated and compared with corresponding Knudsen numbers. Although there are significant variations of the drag coefficient (CD) at very low altitudes, higher altitudes produced consistent values. Two CubeSat geometric orientations were studied, one settled to a consistent CD of around 1.24 for higher altitudes, while the other case settled to a CD of 1.60. The material property of specularlity was found to have a considerable impact on drag coefficients – altering this parameter could lead to significantly higher drag coefficients, in some cases exceeding values of 2.0. The drag coefficients computed can be coupled with other existing models to determine satellite lifespan, as well as to estimate expected drag at various orbital altitudes. This will be insightful for determining thrust values of drag compensation systems, serving to extend the lifespan of VELO operating satellites. Journal Article Advances in Space Research 75 10 7610 7623 Elsevier BV 0273-1177 1879-1948 CubeSat; Boltzmann-BGK; Rarefied Gas; Satellite Drag; Drag Compensation 15 5 2025 2025-05-15 10.1016/j.asr.2025.03.055 COLLEGE NANME COLLEGE CODE Swansea University SU Library paid the OA fee (TA Institutional Deal) Swansea University 2025-05-12T10:15:23.8177984 2025-03-27T11:17:49.1441812 Faculty of Science and Engineering School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering JOSEFF STURROCK 1 Ben Evans 0000-0003-3662-9583 2 Zoran Jelic 3 69158__34240__8b250b46af6f4cb99a644486cc9efa9c.pdf 69158.VOR.pdf 2025-05-12T10:12:00.2281260 Output 3759779 application/pdf Version of Record true © 2025 The Author(s). Published by Elsevier B.V. on behalf of COSPAR. This is an open access article under the CC BY-NC-ND license. true eng http://creativecommons.org/licenses/by-nc-nd/4.0/
title Modelling aerodynamic drag of a very low earth orbit 1U CubeSat utilising a Boltzmann-BGK approach
spellingShingle Modelling aerodynamic drag of a very low earth orbit 1U CubeSat utilising a Boltzmann-BGK approach
JOSEFF STURROCK
Ben Evans
Zoran Jelic
title_short Modelling aerodynamic drag of a very low earth orbit 1U CubeSat utilising a Boltzmann-BGK approach
title_full Modelling aerodynamic drag of a very low earth orbit 1U CubeSat utilising a Boltzmann-BGK approach
title_fullStr Modelling aerodynamic drag of a very low earth orbit 1U CubeSat utilising a Boltzmann-BGK approach
title_full_unstemmed Modelling aerodynamic drag of a very low earth orbit 1U CubeSat utilising a Boltzmann-BGK approach
title_sort Modelling aerodynamic drag of a very low earth orbit 1U CubeSat utilising a Boltzmann-BGK approach
author_id_str_mv a03192b176ce931d0a1c52c2e2ac12e4
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author_id_fullname_str_mv a03192b176ce931d0a1c52c2e2ac12e4_***_JOSEFF STURROCK
3d273fecc8121fe6b53b8fe5281b9c97_***_Ben Evans
448489404aff5092df63279248ba3415_***_Zoran Jelic
author JOSEFF STURROCK
Ben Evans
Zoran Jelic
author2 JOSEFF STURROCK
Ben Evans
Zoran Jelic
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department_str School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering
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description The aerodynamic drag of a 1U CubeSat at various Very Low Earth Orbit (VLEO) altitudes and conditions have been investigated utilising an in-house Boltzmann-BGK solver. This region of space has numerous benefits, however significant drag can lead to short satellite lifespans. The analyses focus on determining drag coefficients, as well as absolute drag values. Flow fields are illustrated. Monoatomic oxygen number density ratios on exposed surfaces were presented to help guide corrosion analysis. Material properties for satellite surface coatings have been analysed, including drag reduction performance. All atmospheric parameters were sourced from NASA’s NRLMSIS 2.0 atmospheric model. Altitudes investigated range from 50 km to 500 km. Periods of solar minima and maxima, seasonal variances and local day/night cases were investigated. Drag coefficients were evaluated and compared with corresponding Knudsen numbers. Although there are significant variations of the drag coefficient (CD) at very low altitudes, higher altitudes produced consistent values. Two CubeSat geometric orientations were studied, one settled to a consistent CD of around 1.24 for higher altitudes, while the other case settled to a CD of 1.60. The material property of specularlity was found to have a considerable impact on drag coefficients – altering this parameter could lead to significantly higher drag coefficients, in some cases exceeding values of 2.0. The drag coefficients computed can be coupled with other existing models to determine satellite lifespan, as well as to estimate expected drag at various orbital altitudes. This will be insightful for determining thrust values of drag compensation systems, serving to extend the lifespan of VELO operating satellites.
published_date 2025-05-15T05:23:55Z
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