Design of Modular Power Management and Attitude Control Subsystems for a Microsatellite
The Electric Power System (EPS) and attitude control system (ACS) are the essential components of any satellite. EPS and ACS efficiency and compactness are substantial for the proper operation and performance of the satellite’s entire mission life. So, realizing the significance of EPS and ACS subsy...
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| Format: | Article |
| Language: | English |
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Wiley
2018-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2018/2515036 |
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| author | Anwar Ali Shoaib Ahmed Khan M. Usman Khan Haider Ali M. Rizwan Mughal Jaan Praks |
| author_facet | Anwar Ali Shoaib Ahmed Khan M. Usman Khan Haider Ali M. Rizwan Mughal Jaan Praks |
| author_sort | Anwar Ali |
| collection | DOAJ |
| description | The Electric Power System (EPS) and attitude control system (ACS) are the essential components of any satellite. EPS and ACS efficiency and compactness are substantial for the proper operation and performance of the satellite’s entire mission life. So, realizing the significance of EPS and ACS subsystems for any satellite, they have been assimilated and developed in modular forms focusing on efficiency and compactness. The EPS is comprised of three modules called the solar panel module (SPM), power conditioning module (PCM), and power distribution module (PDM) while the ACS has an embedded magnetorquer coil. For compactness and miniaturization purposes, the magnetorquer coil is embedded inside the SPM. The components used are commercial off-the-shelf (COTS) components emphasizing on their power efficiency, small dimensions, and weight. Latch-up protection systems have been designed and analyzed for CMOS-based COTS components, in order to make them suitable for space radioactive environment. The main design features are modularity, redundancy, power efficiency, and to avoid single component failure. The modular development of the EPS and ACS helps to reuse them for future missions, and as a result, the overall budget, development, and testing time and cost are reduced. A specific satellite mission can be achieved by reassembling the required subsystems. |
| format | Article |
| id | doaj-art-8288f69f7d69417b9bc57eb1e10e7b00 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2018-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-8288f69f7d69417b9bc57eb1e10e7b002025-02-03T07:24:54ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742018-01-01201810.1155/2018/25150362515036Design of Modular Power Management and Attitude Control Subsystems for a MicrosatelliteAnwar Ali0Shoaib Ahmed Khan1M. Usman Khan2Haider Ali3M. Rizwan Mughal4Jaan Praks5Electrical Technology Department, University of Technology (UoT), Nowshera, PakistanNational University of Computer & Emerging Sciences Peshawar Campus, PakistanNational University of Computer & Emerging Sciences Peshawar Campus, PakistanElectrical Technology Department, University of Technology (UoT), Nowshera, PakistanDepartment of Electrical Engineering, Institute of Space Technology, Islamabad, PakistanDepartment of Electronics and Nanoengineering, School of Electrical Engineering, Aalto University, FI-00076 AALTO, 02150 Espoo, FinlandThe Electric Power System (EPS) and attitude control system (ACS) are the essential components of any satellite. EPS and ACS efficiency and compactness are substantial for the proper operation and performance of the satellite’s entire mission life. So, realizing the significance of EPS and ACS subsystems for any satellite, they have been assimilated and developed in modular forms focusing on efficiency and compactness. The EPS is comprised of three modules called the solar panel module (SPM), power conditioning module (PCM), and power distribution module (PDM) while the ACS has an embedded magnetorquer coil. For compactness and miniaturization purposes, the magnetorquer coil is embedded inside the SPM. The components used are commercial off-the-shelf (COTS) components emphasizing on their power efficiency, small dimensions, and weight. Latch-up protection systems have been designed and analyzed for CMOS-based COTS components, in order to make them suitable for space radioactive environment. The main design features are modularity, redundancy, power efficiency, and to avoid single component failure. The modular development of the EPS and ACS helps to reuse them for future missions, and as a result, the overall budget, development, and testing time and cost are reduced. A specific satellite mission can be achieved by reassembling the required subsystems.http://dx.doi.org/10.1155/2018/2515036 |
| spellingShingle | Anwar Ali Shoaib Ahmed Khan M. Usman Khan Haider Ali M. Rizwan Mughal Jaan Praks Design of Modular Power Management and Attitude Control Subsystems for a Microsatellite International Journal of Aerospace Engineering |
| title | Design of Modular Power Management and Attitude Control Subsystems for a Microsatellite |
| title_full | Design of Modular Power Management and Attitude Control Subsystems for a Microsatellite |
| title_fullStr | Design of Modular Power Management and Attitude Control Subsystems for a Microsatellite |
| title_full_unstemmed | Design of Modular Power Management and Attitude Control Subsystems for a Microsatellite |
| title_short | Design of Modular Power Management and Attitude Control Subsystems for a Microsatellite |
| title_sort | design of modular power management and attitude control subsystems for a microsatellite |
| url | http://dx.doi.org/10.1155/2018/2515036 |
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