Numerical calculation of the operating parameters of the ION engine for satellite correction

The article provides a description of methods for numerical simulation of physical processes occurring in an electric jet engine. A method for estimating the ionization of the working fluid based on drift-diffusion equations is presented. The possibility of calculating the neutralization coefficient...

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Bibliographic Details
Published inActa astronautica Vol. 204; pp. 807 - 814
Main Authors Borodin, I.K., Silnikov, M.V., Kulakov, K.S.
Format Journal Article
LanguageEnglish
Published Elsevier Ltd 01.03.2023
Subjects
Ion thruster
Neutralization
Numerical simulation
Ion thruster
Numerical simulation
Neutralization
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Summary:The article provides a description of methods for numerical simulation of physical processes occurring in an electric jet engine. A method for estimating the ionization of the working fluid based on drift-diffusion equations is presented. The possibility of calculating the neutralization coefficient to prevent erosion of an engine with an original design based on a system of nested electrodes is shown. The article describes the sequence of creating a computer model of an ion engine and the main methods of numerical analysis of the dynamics of charged particles. •Space debris is one of the problems of modern astronautics.•The main reason for the appearance of space debris is the departure of satellites from orbit.•The correction can significantly increase the lifespan of the satellite.•Ion engine is a good option for correction engine.•Computer simulation of individual physical processes makes it possible to create an optimal ion engine.
ISSN:0094-5765
1879-2030
DOI:10.1016/j.actaastro.2022.11.035