Abstract
By performing full Particle-In-Cell simulations, we examined the transient response of electrons released for the charge neutralization of a local ion beam emitted from an ion engine which is one of the electric propulsion systems. In the vicinity of the engine, the mixing process of electrons in the ion beam region is not so obvious because of large difference of dynamics between electrons and ions. A heavy ion beam emitted from a spacecraft propagates away from the engine and forms a positive potential region with respect to the background. Meanwhile electrons emitted for a neutralizer located near the ion engine are electrically attracted or accelerated to the core of the ion beam. Some electrons with the energy lower than the ion beam potential are trapped in the beam region and move along with the ion beam propagation with a multi-streaming structure in the beam potential region. Since the locations of the neutralizer and the ion beam exit are different, the above-mentioned bouncing motion of electrons is also observed in the direction of the beam diameter.
Highlights
As an interplanetary flight system, electric propulsion has been used for many spacecraft
The previous works handled uniform ion beam which has an infinite cross section [2,3], we consider a situation in which an ion beam is emitted with a finite radius from a spacecraft [4,5,6,7,8] and simultaneously thermal electrons for the charge neutralization are released from a different position from the ion emitter [4]
To understand the complex dynamics of the electrons shown in the previous figures, we examined the relation of the electrons to the electrostatic potential
Summary
As an interplanetary flight system, electric propulsion has been used for many spacecraft. Ion beam emission and its neutralization by thermal electrons in electric propulsion is one of the most fundamental problems in spacecraft-plasma interactions. By emitting the same amount of electrons as the beam ions, the charge neutralization can be basically achieved in the spacecraft environment. The previous works handled uniform ion beam which has an infinite cross section [2,3], we consider a situation in which an ion beam is emitted with a finite radius from a spacecraft [4,5,6,7,8] and simultaneously thermal electrons for the charge neutralization are released from a different position from the ion emitter [4].
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
