Estimation of the Static-charge Accumulation of a Spacecraft in the Orbit

The paper estimation the effect of electrification on the spacecraft in low Earth orbit (hereinafter referred to as the LEO). For this purpose, the effects of differential charging and total charging of spacecraft per orbit are calculated. Recently, when developing spacecraft for low-Earth orbit, the parameters of the electrification process that ensure the stable operation of the satellite have become required. The purpose of this work is to draw a conclusion about the influence of the electrification of the spacecraft on its functioning. For this purpose, the plasma-spacecraft interaction was calculated using the Space Plasma Interaction Software (SPIS) program. The object of the study was a model of a spacecraft operating in a sun-synchronous orbit. The role of many spacecraft in this orbit is to obtain images of the earth's surface, including meteorological satellites and earth remote sensing satellites. As a result, the values of information about the absolute and differential charge of the spacecraft were obtained. Based on the results of the calculation, it was concluded that an electrostatic discharge (hereinafter ESD) may occur when the spacecraft is charged on LEO, which can lead to damage to onboard electronics. Possible measures to protect the consequences of satellite electrification were also given. The work is done on 42 pages and is divided into 9 chapters using 18 sources, contains 1 table and 20 figures.