Abstract.
The paper analyzes the current state and capabilities of existing systems for the development and testing of design and technological solutions in electric propulsion engines (EPEs). The study highlights the principles of modern approaches to computer modeling, material selection, and experimental validation. The analysis demonstrates that while significant progress has been achieved, the integration of these systems into a unified framework remains an open challenge. The research identifies gaps in predictive modeling, experimental techniques, and quality assurance methods, and suggests directions for further development of integrated systems for ensuring reliability and efficiency in EPEs.
Keywords: electric propulsion engines, design solutions, technological processes, system analysis, reliability, digital modeling.
Introduction
Electric propulsion engines (EPEs) are increasingly used in modern spacecraft due to their high efficiency and the ability to provide long-duration thrust for orbital maneuvers [1, p. 15]. However, the process of developing and validating design and technological solutions for EPEs remains complex and resource-intensive. Existing systems of working out design and technological decisions include a combination of theoretical modeling, material testing, and full-scale experimental validation [2, p. 8].
The purpose of this paper is to analyze existing approaches to the development of design and technological solutions for EPEs, to identify their limitations, and to outline possible pathways for their integration into comprehensive systems.
1. Theoretical foundations of design and technological solutions in EPEs
The development of EPEs is based on a complex interplay of physics, materials science, and advanced manufacturing methods. Core challenges include:
- Plasma-material interaction leading to erosion of critical components [3, p. 27].
- Optimization of geometry for plasma confinement and acceleration.
- Material selection for electrodes, dielectric channels, and magnetic systems [4, p. 112].
- Manufacturing tolerances which critically influence the performance and lifetime of EPEs.
Existing systems of theoretical validation focus on mathematical modeling of plasma flows and erosion, often using computational fluid dynamics (CFD) and particle-in-cell (PIC) methods [5, p. 43]. However, such models still lack sufficient predictive accuracy without experimental calibration.
2. Existing systems for working out design and technological solutions
Currently, the validation of design and technological solutions in EPEs involves several interconnected systems:
2.1. Computer-aided design and simulation systems.
Widely used software allows modeling of plasma dynamics, thermal loads, and electromagnetic fields. Nevertheless, current tools have limited ability to fully reproduce the complexity of plasma-wall interactions [6, p. 75].
2.2 Material testing systems.
Laboratory-based facilities evaluate resistance to erosion, high-temperature stability, and compatibility with plasma flows [7, p. 52]. Such experiments provide essential data but are costly and time-consuming.
2.3. Experimental and test-bench facilities.
Ground-based test chambers simulate near-space conditions, enabling verification of thrust parameters, efficiency, and lifetime. However, discrepancies between laboratory and in-orbit conditions remain significant [8, p. 31].
2.4. Quality control and production assurance systems.
Methods of additive manufacturing and high-precision machining are increasingly integrated into EPE production. Control systems ensure compliance with design specifications, but integration with predictive modeling is still insufficient [9, p. 17].
3. Analysis of capabilities and limitations
The analysis shows that existing systems provide valuable insights but remain fragmented. Key limitations include:
- Lack of integration between digital models and physical experiments.
- Insufficient accuracy in long-term lifetime prediction [10, p. 204].
- High costs and limited availability of large-scale experimental facilities.
- Weak connection between production quality assurance and early-stage design validation.
As a result, the efficiency of EPE development cycles is reduced, and the reliability of design solutions depends heavily on costly full-scale tests.
4. Prospects for development
To overcome current limitations, research should focus on:
- Development of digital twins for EPEs, integrating plasma modeling, material testing data, and operational feedback [11, p. 6].
- Expansion of accelerated testing methods that simulate erosion and thermal loads in reduced timeframes.
- Application of machine learning and AI to optimize design and predict performance based on big experimental datasets [12, p. 94].
- Establishing unified standards for system-level validation to ensure interoperability between design, manufacturing, and testing facilities.
Conclusions
The conducted analysis confirms that existing systems for working out design and technological solutions of electric propulsion engines are essential but fragmented. Their current capabilities are not sufficient to guarantee rapid and cost-effective development of reliable EPEs. A promising direction is the creation of integrated systems that combine theoretical modeling, material science data, and experimental results into a unified framework. Such systems will significantly improve the accuracy of predictions, reduce development costs, and enhance the competitiveness of EPE technologies in the global space industry.
Bibliographic References
1. Hofer R. R. Electric propulsion for spacecraft: a review of current technologies // Journal of Propulsion and Power. – 2018. – Vol. 34, No. 6. – P. 14–29.
2. Goebel D., Katz I. Fundamentals of Electric Propulsion: Ion and Hall Thrusters. – Hoboken: Wiley, 2008. – 456 p.
3. Morozov A. I. The conceptual development of Hall thrusters // Plasma Physics Reports. – 2017. – Vol. 43. – P. 26–40.
4. Manzella D. M., Oleson S. R. Materials issues for ion and Hall thrusters // NASA Technical Reports. – 2015. – P. 110–125.
5. Boyd I. D. Modeling of plasma flow in electric propulsion devices // Physics of Plasmas. – 2016. – Vol. 23. – P. 42–56.
6. Boeuf J. P. Tutorial: Physics and modeling of Hall thrusters // Journal of Applied Physics. – 2017. – Vol. 121. – P. 75–91.
7. Komurasaki K. Plasma erosion testing of dielectric materials for Hall thrusters // Vacuum. – 2019. – Vol. 165. – P. 51–59.
8. Kim V. Hall thruster lifetime studies // IEEE Transactions on Plasma Science. – 2018. – Vol. 46. – P. 30–39.
9. Lev D., Shagam Y. Advanced manufacturing methods in electric propulsion development // Acta Astronautica. – 2020. – Vol. 177. – P. 15–21.
10. Crofton M. W. Lifetime assessment of electric propulsion engines // Progress in Aerospace Sciences. – 2016. – Vol. 83. – P. 200–215.
11. Hernández L., Sanz J. Digital twin applications in aerospace propulsion systems // Aerospace Science and Technology. – 2021. – Vol. 118. – P. 1–12.
12. Cai W., Li J. Artificial intelligence in aerospace propulsion research // Engineering Applications of Artificial Intelligence. – 2022. – Vol. 110. – P. 92–104.
|
Голосування 
Ця робота ліцензується відповідно до Creative Commons Attribution 4.0 International License
Знайшли помилку? Виділіть помилковий текст мишкою і натисніть Ctrl + Enter