Thermal Design and Experimental Validation of a Lightweight Microsatellite
The multiple working modes, complex working conditions, frequent changes in external heat flux, and high-power consumption of satellites all pose great difficulties to their thermal design. In this paper, the material MB15 magnesium alloy was used, which has not been performed for the main structure...
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MDPI AG
2025-01-01
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| Series: | Aerospace |
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| Online Access: | https://www.mdpi.com/2226-4310/12/1/52 |
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| author | Hongzhou Huang Changgen Bu |
| author_facet | Hongzhou Huang Changgen Bu |
| author_sort | Hongzhou Huang |
| collection | DOAJ |
| description | The multiple working modes, complex working conditions, frequent changes in external heat flux, and high-power consumption of satellites all pose great difficulties to their thermal design. In this paper, the material MB15 magnesium alloy was used, which has not been performed for the main structure of satellites. This material not only reduces the weight of the structure and the launch cost, but also its good thermal conductivity is very helpful for the thermal control design of the satellite. This paper mainly describes the design of a thermal control system for lightweight microsatellites. Firstly, the satellite structure, thermal control indices of the main equipment, and the power consumption of the equipment in different working modes are introduced. Then, the external heat fluxes are analyzed, the position of the heat dissipation surface and extreme conditions are confirmed, and detailed thermal designs of each part of the satellite are determined via the combination of active and passive thermal control. Finally, the thermal balance test is carried out for the whole satellite. It is found that the deviation between the temperature of the thermistor and thermocouple at the same moment in the thermal analysis simulation data and thermal balance test is generally within 0.5 °C, and the maximum difference is not more than 1.7 °C, which indicates that the simulation model is well established and that the thermal analysis is reliable. |
| format | Article |
| id | doaj-art-fbb14853b6fa4f6eba65f19ff2b24f9f |
| institution | Kabale University |
| issn | 2226-4310 |
| language | English |
| publishDate | 2025-01-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj-art-fbb14853b6fa4f6eba65f19ff2b24f9f2025-01-24T13:15:38ZengMDPI AGAerospace2226-43102025-01-011215210.3390/aerospace12010052Thermal Design and Experimental Validation of a Lightweight MicrosatelliteHongzhou Huang0Changgen Bu1School of Engineering and Technology, China University of Geosciences, Beijing 100084, ChinaSchool of Engineering and Technology, China University of Geosciences, Beijing 100084, ChinaThe multiple working modes, complex working conditions, frequent changes in external heat flux, and high-power consumption of satellites all pose great difficulties to their thermal design. In this paper, the material MB15 magnesium alloy was used, which has not been performed for the main structure of satellites. This material not only reduces the weight of the structure and the launch cost, but also its good thermal conductivity is very helpful for the thermal control design of the satellite. This paper mainly describes the design of a thermal control system for lightweight microsatellites. Firstly, the satellite structure, thermal control indices of the main equipment, and the power consumption of the equipment in different working modes are introduced. Then, the external heat fluxes are analyzed, the position of the heat dissipation surface and extreme conditions are confirmed, and detailed thermal designs of each part of the satellite are determined via the combination of active and passive thermal control. Finally, the thermal balance test is carried out for the whole satellite. It is found that the deviation between the temperature of the thermistor and thermocouple at the same moment in the thermal analysis simulation data and thermal balance test is generally within 0.5 °C, and the maximum difference is not more than 1.7 °C, which indicates that the simulation model is well established and that the thermal analysis is reliable.https://www.mdpi.com/2226-4310/12/1/52microsatellitemagnesium alloyexternal heat fluxthermal balance test |
| spellingShingle | Hongzhou Huang Changgen Bu Thermal Design and Experimental Validation of a Lightweight Microsatellite Aerospace microsatellite magnesium alloy external heat flux thermal balance test |
| title | Thermal Design and Experimental Validation of a Lightweight Microsatellite |
| title_full | Thermal Design and Experimental Validation of a Lightweight Microsatellite |
| title_fullStr | Thermal Design and Experimental Validation of a Lightweight Microsatellite |
| title_full_unstemmed | Thermal Design and Experimental Validation of a Lightweight Microsatellite |
| title_short | Thermal Design and Experimental Validation of a Lightweight Microsatellite |
| title_sort | thermal design and experimental validation of a lightweight microsatellite |
| topic | microsatellite magnesium alloy external heat flux thermal balance test |
| url | https://www.mdpi.com/2226-4310/12/1/52 |
| work_keys_str_mv | AT hongzhouhuang thermaldesignandexperimentalvalidationofalightweightmicrosatellite AT changgenbu thermaldesignandexperimentalvalidationofalightweightmicrosatellite |