Abstract This paper investigates spacecraft orbital boost maneuver by a fully insulated electrodynamic tether using a coupled multiphysics dynamic model that considers electric-magnetic-dynamic energy coupling. The current-potential characteristics of the electrodynamic tether is described by a simplified analytical model, where revised Parker-Murphy model is employed to evaluate electric current generation at plasma contactors together with libration dynamics of tether. The 13th-order Earth's magnetic field model is used to account influence of inhomogeneity of Earth's magnetic field on orbital parameters of electrodynamic tether system, especially in inclined orbits. Parametric analysis has been conducted for orbital boost maneuver from 400 km to 1,200 km at four different orbital inclinations. The results show that (i) the orbit of electrodynamic tether system will change from circular to elliptical orbits, especially in inclined orbits, (ii) the voltage of onboard power supply at the anode affect electric current generation, (iii) the coupled multiphysics model is necessary to characterize the interaction of electrodynamic tether with the surrounding space environment and the controllability of electric current in electrodynamic tether, (iv) the motion of orbital boost maneuver by electrodynamic tether is stable, which is different from the deorbit by electrodynamic tether.

中文翻译：

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考虑电-磁-动力能量耦合的电动系绳助推航天器特性

摘要 本文使用考虑电磁-动态能量耦合的耦合多物理场动力学模型研究了通过完全绝缘的电动系绳进行的航天器轨道助推机动。电动系绳的电流-电位特性由简化的分析模型描述，其中采用修正的 Parker-Murphy 模型来评估等离子体接触器处的电流产生以及系绳的振动动力学。13阶地球磁场模型用于考虑地球磁场不均匀性对电动系绳系统轨道参数的影响，特别是在倾斜轨道上。对从 400 公里到 1,200 公里的四种不同轨道倾角的轨道助推机动进行了参数分析。