Numerical simulation of sheath structure and current-voltage characteristics of a conductor-dielectric disk in a plasma

Abstract

We present results of a calculation of current-voltage characteristic curves and voltage profiles for an idealized spacecraft charging configuration. We model a plasma interacting with a conducting disk covered by a charged dielectric, with a portion of the conductor exposed to the ambient magnetospheric plasma. We also model the electrostatics of a conducting "button" resting on the center of a dielectric disk. The calculation uses a cylindrical particle-in-cell (PIC) particle mover with variable particle number, and the potential is calculated self-consistently using successive over relaxation (SOR). Results of this electrostatic plasma simulation are presented both with and without secondary electron emission from the dielectric. FIG. 7. Potential function for a -200-Y button run, after SOOO time steps.Chaky, Nonnast, and Enoch 7095 [This article is copyrighted as indicated in the article. Reuse of AIP content is subject to the terms at: http://scitation.aip.org/termsconditions. Downloaded to ] IP: 132.174.254.155 On: Tue

Surface Charging Controlling of the Chinese Space Station with Hollow Cathode Plasma Contactor

“…The orbit is situated in F2 of ionosphere, where is filled with dense low energy plasma. The larger spacecraft using high voltage solar array can produce structural potential which was 90% of the operating voltage in LEO [5,6] . The exposed positive electrode potential on the solar array is higher than that environment plasma potential, which can attract electrons from the environment plasma.…”