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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Main Authors: Kan Xie, Fuwen Liang, Qimeng Xia, Ningfei Wang, Zun Zhang, Haoxiang Yuan, Xiangyang Liu, Zhiwen Wu
Format: Article
Language:English
Published: Wiley 2021-01-01
Series:International Journal of Aerospace Engineering
Online Access:http://dx.doi.org/10.1155/2021/8834196
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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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