Dynamics of orbital boost maneuver of low Earth orbit satellites by electrodynamic tethers

被引：0

作者：

Liu J. ^{[1
]}

Zhan X. ^{[1
]}

Li G. ^{[2
]}

Wang Q. ^{[3
]}

Wang S. ^{[1
]}

机构：

[1] School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai

[2] Department of Mechanical Engineering, York University, Toronto

[3] School of Science, Nanjing University of Science and Technology, Nanjing

来源：

Aerospace Systems | 2020年 / 3卷 / 3期

关键词：

Coupled multiphysics model; Electrodynamic tether; Libration dynamics; Parker–Murphy model;

D O I：

10.1007/s42401-020-00053-y

中图分类号：

学科分类号：

摘要：

This paper studied the dynamic characteristics of electrodynamic tethered satellite with consideration of coupled multiphysics field for orbital boost maneuver by a fully insulated electrodynamic tether (EDT). We proposed a simplified analytical nonlinear current–voltage circuit method based on the Parker–Murphy model to evaluate the real-time electric current-carrying tether. Furthermore, the performances of orbital boost maneuver by a fully insulated electrodynamic tether is investigated. This current–voltage model is influenced by the electron density, the intensity of Earth’s magnetic field and the space plasma temperature. The hollow plasma contactor located on the sub-satellite to attract the electrons from the ambient plasma. An on-board power supply is adopted to change the direction of electric current for boosting the system. The direction of electric current in tether is from main-satellite to sub-satellite. The efficiency of orbital boost maneuver is compared with different sizes of anodic contactors and the given voltage of power supply. The simulation results showed that electric current is easily affected by the fluctuation of electron density, the Earth’s magnetic field and plasma temperature. The electrodynamic tether system can stable boost its orbit altitude from 400 to 1200 km in four cases by a fully insulated electrodynamic tether. © 2020, Shanghai Jiao Tong University.

引用

页码：189 / 196

页数：7

共 50 条

[1] Micro Satellite Orbital Boost by Electrodynamic Tethers
Yao, Peter
Sands, Timothy
MICROMACHINES, 2021, 12 (08)
[2] Automatic orbital maneuver for mega-constellations maintenance with electrodynamic tethers
Liu, Jinyu
Li, Gangqiang
Zhu, Zheng H.
Liu, Ming
Zhan, Xingqun
AEROSPACE SCIENCE AND TECHNOLOGY, 2020, 105
[3] Dynamics of Nanosatellite Deorbit by Bare Electrodynamic Tether in Low Earth Orbit
Zhong, R.
Zhu, Z. H.
JOURNAL OF SPACECRAFT AND ROCKETS, 2013, 50 (03) : 691 - 700
[4] Effect of electrodynamic forces on the orbital dynamics of tethered satellites
Lanoix, ELM
Misra, AK
Modi, VJ
Tyc, G
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 2005, 28 (06) : 1309 - 1315
[5] RELATIVE ORBITAL EVOLUTION OF A CLUSTER OF FEMTO-SATELLITES IN LOW EARTH ORBIT
Sundaramoorthy, P. P.
Gill, E.
Verhoeven, C. J. M.
SPACEFLIGHT MECHANICS 2010, PTS I-III, 2010, 136 : 899 - +
[6] THE FLUX OF METEOROIDS AND ORBITAL SPACE DEBRIS STRIKING SATELLITES IN LOW EARTH ORBIT
LAURANCE, MR
BROWNLEE, DE
NATURE, 1986, 323 (6084) : 136 - 138
[7] Orbital maneuver technology of temporary networked satellites for earth exploration
Zhao J.
Li W.
Gao R.
Zhang G.
Zhu X.
Zhan Y.
Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University, 2022, 40 (04): : 875 - 882
[8] Navigation Satellites Orbit Determination with the Enhancement of Low Earth Orbit Satellites
Yang Y.
Yang Y.
Xu J.
Xu Y.
Zhao A.
Wuhan Daxue Xuebao (Xinxi Kexue Ban)/Geomatics and Information Science of Wuhan University, 2020, 45 (01): : 46 - 52
[9] Two-Line-Elements-Based Maneuver Detection Methods for Satellites in Low Earth Orbit
Lemmens, Stijn
Krag, Holger
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 2014, 37 (03) : 860 - 868
[10] Fuzzy-based continuous current control of electrodynamic tethers for stable and efficient orbital boost
Liu, Jinyu
Zhu, Zheng H.
Li, Gangqiang
Zhan, Xingqun
AEROSPACE SCIENCE AND TECHNOLOGY, 2021, 118

← 1 2 3 4 5 →