Power Generation on a Bare Electrodynamic Tether during Debris Mitigation in Space
Power generation can be realized in space when current is induced on a bare electrodynamic tether system. The performance of power generation is discussed based on a debris mitigation mission by numerical simulation in the paper. A Li-ion battery subsystem is used to complete the energy conversion—h...
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| Format: | Article |
| Language: | English |
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Wiley
2021-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2021/8834196 |
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| _version_ | 1832547027156729856 |
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| author | Kan Xie Fuwen Liang Qimeng Xia Ningfei Wang Zun Zhang Haoxiang Yuan Xiangyang Liu Zhiwen Wu |
| author_facet | Kan Xie Fuwen Liang Qimeng Xia Ningfei Wang Zun Zhang Haoxiang Yuan Xiangyang Liu Zhiwen Wu |
| author_sort | Kan Xie |
| collection | DOAJ |
| description | Power generation can be realized in space when current is induced on a bare electrodynamic tether system. The performance of power generation is discussed based on a debris mitigation mission by numerical simulation in the paper. A Li-ion battery subsystem is used to complete the energy conversion—harvest and supply the energy. The battery can provide 10–300 W average electric power continuously during several hundred hour mission time. The energy conversion efficiency ranges from 1% to a maximum value 30%. With constant power consumption on board, the battery operation generally experiences a discharging phase, a charging phase, and a stable phase. The first two phases determine the mission risk coefficient. The heating problem in the stable phase cannot be ignored. The optimization of battery design and tether design should be considered for each debris mitigation mission. An extra control circuit or small battery voltage with large capacity for battery design is suggested to eliminate the stable phase. Wide or long tether designs are more appropriate for mission with high or low power demands on board, respectively. The power generation is affected by the system mass and the mission orbit parameters. |
| format | Article |
| id | doaj-art-99a45305f86d42ef9f4b207c04cfc94c |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2021-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-99a45305f86d42ef9f4b207c04cfc94c2025-02-03T06:46:22ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742021-01-01202110.1155/2021/88341968834196Power Generation on a Bare Electrodynamic Tether during Debris Mitigation in SpaceKan Xie0Fuwen Liang1Qimeng Xia2Ningfei Wang3Zun Zhang4Haoxiang Yuan5Xiangyang Liu6Zhiwen Wu7School of Aerospace Engineering, Beijing Institute of Technology, 100081, ChinaSchool of Aerospace Engineering, Beijing Institute of Technology, 100081, ChinaSchool of Aerospace Engineering, Beijing Institute of Technology, 100081, ChinaSchool of Aerospace Engineering, Beijing Institute of Technology, 100081, ChinaSchool of Space and Environment, Beihang University, 100191, ChinaSchool of Aerospace Engineering, Beijing Institute of Technology, 100081, ChinaSchool of Aerospace Engineering, Beijing Institute of Technology, 100081, ChinaSchool of Aerospace Engineering, Beijing Institute of Technology, 100081, ChinaPower generation can be realized in space when current is induced on a bare electrodynamic tether system. The performance of power generation is discussed based on a debris mitigation mission by numerical simulation in the paper. A Li-ion battery subsystem is used to complete the energy conversion—harvest and supply the energy. The battery can provide 10–300 W average electric power continuously during several hundred hour mission time. The energy conversion efficiency ranges from 1% to a maximum value 30%. With constant power consumption on board, the battery operation generally experiences a discharging phase, a charging phase, and a stable phase. The first two phases determine the mission risk coefficient. The heating problem in the stable phase cannot be ignored. The optimization of battery design and tether design should be considered for each debris mitigation mission. An extra control circuit or small battery voltage with large capacity for battery design is suggested to eliminate the stable phase. Wide or long tether designs are more appropriate for mission with high or low power demands on board, respectively. The power generation is affected by the system mass and the mission orbit parameters.http://dx.doi.org/10.1155/2021/8834196 |
| spellingShingle | Kan Xie Fuwen Liang Qimeng Xia Ningfei Wang Zun Zhang Haoxiang Yuan Xiangyang Liu Zhiwen Wu Power Generation on a Bare Electrodynamic Tether during Debris Mitigation in Space International Journal of Aerospace Engineering |
| title | Power Generation on a Bare Electrodynamic Tether during Debris Mitigation in Space |
| title_full | Power Generation on a Bare Electrodynamic Tether during Debris Mitigation in Space |
| title_fullStr | Power Generation on a Bare Electrodynamic Tether during Debris Mitigation in Space |
| title_full_unstemmed | Power Generation on a Bare Electrodynamic Tether during Debris Mitigation in Space |
| title_short | Power Generation on a Bare Electrodynamic Tether during Debris Mitigation in Space |
| title_sort | power generation on a bare electrodynamic tether during debris mitigation in space |
| url | http://dx.doi.org/10.1155/2021/8834196 |
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