Dynamics of orbital boost maneuver of low Earth orbit satellites by electrodynamic tethers
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ORIGINAL PAPER
Dynamics of orbital boost maneuver of low Earth orbit satellites by electrodynamic tethers Jinyu Liu1
· Xingqun Zhan1 · Gangqiang Li2 · Qingtao Wang3 · Shizhuang Wang1
Received: 12 August 2019 / Revised: 17 March 2020 / Accepted: 13 May 2020 © Shanghai Jiao Tong University 2020
Abstract 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. Keywords Coupled multiphysics model · Electrodynamic tether · Libration dynamics · Parker–Murphy model
1 Introduction Electrodynamic tethered satellite system (ETSS) consists of main-satellite, one or more sub-satellites, and conductive tethers that connect main-satellite with sub-satellite [1, 2]. Several ETSS missions have been operated for different
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Jinyu Liu [email protected] Xingqun Zhan [email protected] Gangqiang Li [email protected] Qingtao Wang [email protected] Shizhuang Wang [email protected]
1
School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai 200240, China
2
Department of Mechanical Engineering, York University, Toronto M3J1P3, Canada
3
School of Science, Nanjing University of Science and Technology, Nanjing 210094, China
applications, such as the orbital transfer system [3, 4], tether formation system [5, 6], and space elevators [7]. There are three types of EDT, i.e., fully bare, partially bare or insulated, and fully insulated EDT. The fully insulated EDT is proposed for orbital transfer [8]. Interested readers can find the detailed literature reviews about EDT dynamics and its application in orbital transfer in [9]. Initially, Sanmartin [3, 10] compared different types of EDT system based on the evaluation of its performance of current generation. Then, William [11] studies the orbital transfer of a ful
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