Preliminary thermal design of CubeSat
Berckmans, Nicolas
Promotor(s) : Kerschen, Gaëtan
Date of defense : 21-Aug-2017 • Permalink : http://hdl.handle.net/2268.2/3201
Details
Title : | Preliminary thermal design of CubeSat |
Translated title : | [fr] Design thermique préliminaire d'un CubeSat |
Author : | Berckmans, Nicolas |
Date of defense : | 21-Aug-2017 |
Advisor(s) : | Kerschen, Gaëtan |
Committee's member(s) : | Jacques, Lionel
Loicq, Jerôme Van Grootel, Valérie |
Language : | English |
Number of pages : | 137 |
Keywords : | [en] CubeSat [en] Satellite [en] Thermal [en] Esatan |
Discipline(s) : | Engineering, computing & technology > Aerospace & aeronautics engineering |
Institution(s) : | Université de Liège, Liège, Belgique |
Degree: | Master en ingénieur civil en aérospatiale, à finalité spécialisée en "aerospace engineering" |
Faculty: | Master thesis of the Faculté des Sciences appliquées |
Abstract
[en] This thesis will carry out the first thermal analysis of the NAOS CubeSat. The objective of this study is to verify that the temperatures of satellite components remain in their respective allowed ranges.
After a brief description of the satellite mission and configuration, its modeling will begin. First the complex shape of the satellite will be simplified in the Esatan geometric model. This model will be used by Esatan to define the thermal nodes and compute the radiative exchanges between the components. The modeling will continue with the definition of the thermal properties of the materials and surface finishes. The model will be corrected with the definition of capacitances and finished with the definition of conductive links between the shells.
After the definition of the worst cases, the first results will be obtained. It will be observed that the initial design will lead to excessive temperatures (for example 101.8 °C for the batteries). The design will have to be optimized. These optimizations will include the modification of the initial external surface finish replaced by white paint. The internal conductances will be improved by using five layers of copper inside the PCB and using a filler material for the spacers. Finally a realistic model of the detector assembly will be built. Its improvement will include the modification of the insulation and the increase of the radiator area.
With the final design determined, the worst cases, as well as intermediate cases, will be ran. The predicted temperatures of these cases will show that the batteries, ADCS and the detector will still present issues. Several recommendations for these components will then be suggested for future thermal designs of the satellite.
File(s)
Document(s)
Description: Report of the master thesis
Size: 9.49 MB
Format: Adobe PDF
Description: Summary of the master thesis
Size: 86.01 kB
Format: Adobe PDF
Annexe(s)
Description: Temperature field of the satellite during the hot case
Size: 123.54 kB
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Description: Temperature field of the platform during hot case
Size: 77.29 kB
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Description: Temperature field of the platform during cold case
Size: 27.19 kB
Format: image/png
Description: Temperature field of the satellite during cold case
Size: 96.32 kB
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Description: Evolution temperatures payload during hot case
Size: 31.82 kB
Format: image/png
Description: Evolution temperatures platform during hot case
Size: 45.92 kB
Format: image/png
Description: Evolution temperatures payload during cold case
Size: 34.5 kB
Format: image/png
Description: Evolution temperatures platform during cold case
Size: 47.53 kB
Format: image/png
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