A Detailed Thermal and Effective Induced Residual Spin Rate Analysis for LEO Small Satellites
In space thermal environment, satellites are exposed to multiple heat sources which can deteriorate structural and equipment integrity over long periods of time. Normally radiators are used to release heat, but due to space and weight constraints, it is impossible to mount radiators on small satelli...
| Main Authors: | , , , , |
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| Format: | Article |
| Language: | English |
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IEEE
2020-01-01
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| Series: | IEEE Access |
| Subjects: | |
| Online Access: | https://ieeexplore.ieee.org/document/9160911/ |
| _version_ | 1818930562873688064 |
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| author | Anwar Ali Jijun Tong Haider Ali Muhammad Rizwan Mughal Leonardo M. Reyneri |
| author_facet | Anwar Ali Jijun Tong Haider Ali Muhammad Rizwan Mughal Leonardo M. Reyneri |
| author_sort | Anwar Ali |
| collection | DOAJ |
| description | In space thermal environment, satellites are exposed to multiple heat sources which can deteriorate structural and equipment integrity over long periods of time. Normally radiators are used to release heat, but due to space and weight constraints, it is impossible to mount radiators on small satellites. This problem signifies the importance of thermal analysis of a satellite in every development stage, such as design, manufacturing and testing. The ultimate goal of this work is to analyze a small spacecraft in space thermal environment by considering the effect of various heat sources. Thermal equilibrium equation is achieved which is applied to spacecraft with different shapes and dimensions and temperature is measured for a range of absorption co-efficient values (i.e. 0.5 ~ 0.9). Through an experimental setup a method is devised to measure the absorption co-efficient of small satellites that can be used for exact temperature measurement. Secondly, the paper presents a preliminary analysis of induced spin produced by small satellites due to asymmetrical colors (different absorptance) of satellite outer surface. The substantial contributors for induced spin are considered and the estimated spin is measured. |
| first_indexed | 2024-12-20T04:02:41Z |
| format | Article |
| id | doaj.art-a2af17f6f398479988f048a823580d10 |
| institution | Directory Open Access Journal |
| issn | 2169-3536 |
| language | English |
| last_indexed | 2024-12-20T04:02:41Z |
| publishDate | 2020-01-01 |
| publisher | IEEE |
| record_format | Article |
| series | IEEE Access |
| spelling | doaj.art-a2af17f6f398479988f048a823580d102022-12-21T19:54:08ZengIEEEIEEE Access2169-35362020-01-01814619614620710.1109/ACCESS.2020.30146439160911A Detailed Thermal and Effective Induced Residual Spin Rate Analysis for LEO Small SatellitesAnwar Ali0https://orcid.org/0000-0001-7366-9002Jijun Tong1https://orcid.org/0000-0002-6209-6605Haider Ali2https://orcid.org/0000-0002-2261-4105Muhammad Rizwan Mughal3https://orcid.org/0000-0002-0660-2761Leonardo M. Reyneri4School of Information Science and Technology, Zhejiang Sci-Tech University, Hangzhou, ChinaSchool of Information Science and Technology, Zhejiang Sci-Tech University, Hangzhou, ChinaDepartment of Electrical Engineering Technology, University of Technology (UoT), Nowshera, PakistanDepartment of Electronics and Nanoengineering, School of Electrical Engineering, Aalto University, Espoo, FinlandDepartment of Electronics and Telecommunication (DET), Politecnico di Torino, Turin, ItalyIn space thermal environment, satellites are exposed to multiple heat sources which can deteriorate structural and equipment integrity over long periods of time. Normally radiators are used to release heat, but due to space and weight constraints, it is impossible to mount radiators on small satellites. This problem signifies the importance of thermal analysis of a satellite in every development stage, such as design, manufacturing and testing. The ultimate goal of this work is to analyze a small spacecraft in space thermal environment by considering the effect of various heat sources. Thermal equilibrium equation is achieved which is applied to spacecraft with different shapes and dimensions and temperature is measured for a range of absorption co-efficient values (i.e. 0.5 ~ 0.9). Through an experimental setup a method is devised to measure the absorption co-efficient of small satellites that can be used for exact temperature measurement. Secondly, the paper presents a preliminary analysis of induced spin produced by small satellites due to asymmetrical colors (different absorptance) of satellite outer surface. The substantial contributors for induced spin are considered and the estimated spin is measured.https://ieeexplore.ieee.org/document/9160911/Satellitesthermal analysistemperatureabsorption |
| spellingShingle | Anwar Ali Jijun Tong Haider Ali Muhammad Rizwan Mughal Leonardo M. Reyneri A Detailed Thermal and Effective Induced Residual Spin Rate Analysis for LEO Small Satellites IEEE Access Satellites thermal analysis temperature absorption |
| title | A Detailed Thermal and Effective Induced Residual Spin Rate Analysis for LEO Small Satellites |
| title_full | A Detailed Thermal and Effective Induced Residual Spin Rate Analysis for LEO Small Satellites |
| title_fullStr | A Detailed Thermal and Effective Induced Residual Spin Rate Analysis for LEO Small Satellites |
| title_full_unstemmed | A Detailed Thermal and Effective Induced Residual Spin Rate Analysis for LEO Small Satellites |
| title_short | A Detailed Thermal and Effective Induced Residual Spin Rate Analysis for LEO Small Satellites |
| title_sort | detailed thermal and effective induced residual spin rate analysis for leo small satellites |
| topic | Satellites thermal analysis temperature absorption |
| url | https://ieeexplore.ieee.org/document/9160911/ |
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