## 4 Conclusions  
Through SPIS simulations of the spacecraft in the most challenging GEO environment, considering Hall thrusters in various states and different thruster positions influencing surface charging, the following conclusions can be obtained:  
1. With the Hall thruster closed, the glass and other areas are in the vicinity of the existence of a great potential difference, about 3740 V. This region is highly susceptible to electrostatic discharge phenomena, necessitating a certain level of protection to prevent discharges that could impact the performance of nearby payloads. 2. The Hall thruster plume has a major effect on the spacecraft surface charging potential, while the influence of the space environment has less of an effect on the surface potential, which is mainly affected by the charge exchange ions in the plume. 3. The position of the thrusters has almost no effect on the overall surface charging of the satellite, and the surface charging potential of Position 2, where the thrusters are located closer to the main body of the spacecraft, is only 1.3 V higher than the surface charging potential of Position 1. However, when the thruster is in Position 2, more CEX_Xe+ is attracted to the spacecraft surface, which results in a greater deposition contamination of the spacecraft surface. 4. The spacecraft surface potential appears to be the maximum value of the glass surface; by their own shade, not light and poor conductivity of the material, the emission of photoelectrons is inhibited so that the surface potential of the charge moves to a higher position. The results of this study not only help to deepen the understanding of the possible environmental impacts of Hall thrusters in practical applications, but also provide guidance for the design and selection of spacecraft suitable for specific missions. Through the detailed study of Hall thruster plumes, we can better understand the complex interaction between Hall thrusters and spacecraft, and thus provide a more reliable foundation for the successful execution of future space exploration missions. However, it is important to note that certain factors, such as the intensity of the plume, have not been thoroughly analyzed and investigated, so these conclusions still require further consideration and validation. Conceptualization, X.Z. and W.W.; methodology, X.Z. and W.W.; software, C.B. ; validation, Z.Y., S.J., Q.C., L.Z. ([PERSON]) and L.Z. ([PERSON]); formal analysis, X.Z. and W.W.; investigation, Z.Y., S.J., Q.C., L.Z. ([PERSON]) and L.Z. ([PERSON]); resources, C.B. ; data curation, W.W.; writing--original draft preparation, X.Z. and W.W.; writing--review and editing, Z.Z. ; visualization, Z.W., S.J. and S.Z. ; supervision, Y.S. ; project administration, X.Z. and Y.S. ; funding acquisition, C.B. All authors have read and agreed to the published version of the manuscript. \begin{table}
\begin{tabular}{c c c c} \hline \hline  & **Location of the** & **Collection of Photoelectron** & **Collection of Xe+** \\  & **Thruster** & **Current (A)** & **Current (A)** \\ \hline Node 4 & 1 & 1.8 \(\times\) 10\({}^{-6}\) & 3.75 \(\times\) 10\({}^{-5}\) \\  & 2 & 0 & 2.75 \(\times\) 10\({}^{-5}\) \\  & 1 & 0 & 2 \(\times\) 10\({}^{-6}\) \\  & 2 & 5 \(\times\) 10\({}^{-6}\) & 2.25 \(\times\) 10\({}^{-5}\) \\ \hline \hline  
**Funding:** This research was funded by Convolutional Neural Network-based Algorithmic Recognition Algorithm for Particle Waveform Signals on Starboard FPGA Platforms, grant number 42204180. **Institutional Review Board Statement:** Not applicable. **Informed Consent Statement:** Not applicable. **Data Availability Statement:** The original contributions presented in the study are included in the article, further inquiries can be directed to the corresponding author.