Abstract
The analysis is represented of some works devoted to the mathematical modeling of processes in plasma-ion thrusters and Hall effect thrusters. It is shown that the common in these works is the use of approximate forms of the equations of gas dynamics, which are applicable to the description of relatively dense gases, but not to analyze the processes in the rarefied plasma of electric propulsion thrusters. As a result, the above mathematical models do not represent the processes that are significantly responsible for the values of the thruster operating parameters.Authors try to partially correct this drawback by insertion into the initial approximate forms of the equations written for a point in the plasma volume, the parameters that actually represent the boundary effects and should be written not in the equations of gas dynamics themselves, but in the boundary conditions for these equations.The most complete forms of the necessary equations are given in this paper. It is shown that it is necessary to take into account electrons thermal conductivity as well as at least one (radial-azimuth) component of viscosity tensor to describe the "wall scattering" effect.It is concluded that the most productive approach in mathematical modeling is to write the most complete forms of equations with their subsequent simplification – removing the terms responsible for the processes recognized on the basis of primary numerical estimates as such, which can be neglected.
Highlights
Plasma-ion thruster with radial magnetic field and Hall effect thruster relate to electrostatic electric propulsion thrusters with almost axial electric field for ions acceleration and almost radial magnetic field, which is used to prevent the extreme axial electrons current
The main effect of the axial flow of electrons was named the lost of their rotation moment because of non-mirror reflection from a potential barrier in a Langmuir layer near the surface, which was called "near-wall conductivity" or "wall scattering" [1]
The purpose of this study is to show that these problems are associated with the use of not the most complete forms of the equations of plasma dynamics, but approximate ones, suitable for describing relatively dense gases in contrast to the rarefied plasma of electric propulsion thrusters
Summary
(2021) Influence of Wall Scattering Effect on Electrons Gas Dynamics Parameters in Electric Propulsion Thrusters with Closed Electron Drift. Guo Zongshuai, postgraduate student of National Aerospace University "Kharkiv Aviation Institute", Kharkiv, Ukraine Huang Zhihao, postgraduate student of National Aerospace University "Kharkiv Aviation Institute", Kharkiv, Ukraine. KEYWORDS plasma-ion thruster, Hall effect thruster, wall scattering, thermal conductivity, viscosity, pressure tensor, Langmuir layer
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