Two types of high frequency electromagnetic resistive instabilities are found to occur in a Hall thruster plasma in the presence of collisions and ionization, out of which one of lower growth rate (called lower magnitude high frequency instability (LMHFI)) is sensitive to the axial component of the wave vector. The effects of ionization, collisions, and electron drift velocity on the growth rates of these instabilities are studied in greater details. The LMHFI grows faster in the presence of ionization but shows weaker dependence on the electrons' E→×B→ drift, contrary to the case of other instability (called higher magnitude high frequency instability) which is sensitive to the azimuthal wave number and collisions.

High frequency electromagnetic resistive instability in a Hall thruster under the effect of ionization

In this paper, we summarize the research development of low-frequency oscillations in the last few decades. The findings of physical mechanism, characteristics and stabilizing methods of low-frequency oscillations are discussed. It shows that it is unreasonable and incomplete to model an ionization region separately to analyze the physical mechanism of low-frequency oscillations. Electro-dynamics as well as the formation conditions of ionization distribution play an important role in characteristics and stabilizing of low-frequency oscillations. Understanding the physical mechanism and characteristics of low- frequency oscillations thoroughly and developing a feasible method stabilizing this instability are still important research subjects.

http://iopscience.iop.org/article/10.1088/1674-1056/24/5/055201/pdf

Low-frequency oscillations in Hall thrusters

Effect of the hollow cathode heat power on the performance of a Hall-effect thruster is investigated. The variations in the Hall-effect thruster's performance (thrust, specific impulse and anode efficiency) with the hollow cathode heat power was obtained from the analysis of the experimental data. Through an analysis on the coupling relationship between the electrons emitted from the hollow cathode and the environmental plasma, it was found that the heat power would affect the electron emission of the emitter and the space potential of the coupling zone, which would lead to a change in the effective discharge voltage. The experimental data agree well with the results of calculation which can be used to explain the experimental phenomena.

https://iopscience.iop.org/article/10.1088/1009-0630/11/2/12/pdf

Effect of the Hollow Cathode Heat Power on the Performance of an Hall-Effect Thruster

Hall thruster is an attractive type of electric propulsion that is being developed to replace the chemical propulsion deployed in many tasks on satellites. The research on Hall thrusters in China has gradually progressed from basic theory to engineering applications, especially with the experience of on-orbit flight tests in low earth and geostationary equatorial orbits. This paper discusses the progress of research on Hall thrusters in China in recent years. This includes the beam focusing, scaling, high specific impulse, long lifetime, and effective magnetic field excitation techniques, as well as the stabilization technique of low-frequency oscillation, along with other types of Hall thrusters, such as cylindrical Hall, double-stage Hall, cusped field, nested-channel Hall, and anode layer Hall thrusters. In conclusion, this paper discusses the programs intended for the future focusing on the development of thrusters, their application prospects, and their use in space applications.

Overview of Hall Electric Propulsion in China

The two major problems with Hall thrusters are the sputtering erosion of the discharge channel wall and the low-frequency oscillation. A new design for a Hall thruster with an innovative buffer chamber, in which part of the propellant is ionized, shows effective ability to restrain the low-frequency oscillation. However, how the preionization affects the erosion of the channel wall has not been well studied. In this paper, a 2-D axisymmetric fully kinetic particle-in-cell and Monte Carlo collision model is developed to investigate the effect of preionization on erosion of the channel wall of a Hall thruster. The geometry of this simulation model corresponds to the typical SPT-70 thruster, and the computational domain includes the whole discharge chamber of the thruster and the near-field plume region. Some scaling laws are introduced to accelerate this simulation. A preionization model and an erosion model are imported into the simulation to investigate the effect of different preionization ratios on the erosion of the channel wall. The results indicate that the effect of preionization on the change in the electric field is not obvious, in that it does not change the energy of the sputter ions significantly. When the preionization ratio increases, the ion incidence angle decreases slightly, but the number of sputter ions increases markedly. Overall, the erosion of the channel wall increases with the increasing preionization ratio. It needs further consideration for the application of the buffer chamber that preionizes the discharge plasma.

Effect of Preionization on the Erosion of the Discharge Channel Wall in a Hall Thruster Using a Kinetic Simulation

It was found through the experiments made with an Aton-type Hall thruster that some of the propellant was ionized in the buffer chamber by “quick electrons” This ionization is called “preionization” to discriminate it from the ionization in the discharge channel The effect of preionization on low frequency oscillation was experimentally studied by changing the electric field intensity in the buffer chamber The relationship between low frequency oscillation and preionization ratio was investigated through numerical simulation using a one-dimensional quasineutrality hydrodynamic model The results obtained indicate that the amplitude of low frequency oscillation decreases as the preionization ratio increases It was found through the analysis and numerical simulation of the physical process of low frequency oscillation that the positive feedback of electron density was the main cause of low frequency oscillation The increase of preionization ratio decreases the amplitude of the feedback variation thereby reducing the amplitude of low frequency oscillation

Effect of preionization in Aton-type Hall thruster on low frequency oscillation

The invention provides a method for on-line temperature monitoring of an exciting winding of a plasma Hall effect thruster, relates to the technical field of Hall effect thrusters and aims at solving the problem that the on-line temperature monitoring of the exciting winding of an existing plasma Hall effect thruster needs an additional measurement galvanic couple. The method comprises the specific steps of 1 acquiring voltage U1 and current II of the exciting winding of the plasma Hall effect thruster on line; 2 substituting the voltage U1 and the current II of the exciting winding of the plasma Hall effect thruster into a formula and finally obtaining the current temperature of the exciting winding of the plasma Hall effect thruster; achieving the on-line temperature monitoring of the exciting winding of the plasma Hall effect thruster. The method is specifically applied to the field of temperature measurement of the exciting winding of the plasma Hall effect thruster.

Method for on-line temperature monitoring of exciting winding of plasma Hall effect thruster

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Effect of preionization in Aton-type Hall thruster on low frequency oscillation

Method for on-line temperature monitoring of exciting winding of plasma Hall effect thruster