This paper studied the dynamic characteristics of electrodynamic tethered satellite with consideration of coupled multiphysics field for orbital boostmaneuver by a fully insulated electrodynamic tether(EDT).We propose...This paper studied the dynamic characteristics of electrodynamic tethered satellite with consideration of coupled multiphysics field for orbital boostmaneuver 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.展开更多
基金supported by the Chinese Scholarship Council Scholarship No.201806230154.
文摘This paper studied the dynamic characteristics of electrodynamic tethered satellite with consideration of coupled multiphysics field for orbital boostmaneuver 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.
