Fluid Simulation of a Cusped Field Thruster

Liu, H.; Wu, Huan; Meng, Yingchao; Yang, S.; Zhang, Jize; Yu, Daren

doi:10.1002/ctpp.201500011

Cited by 6 publications

(3 citation statements)

References 10 publications

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“…During this process, some xenon (Xe) atoms in the discharge channel are ionized with electron-neutral collisions [4,16]. Then, a cross-field electron current in the cusped magnetic field can be formed with classical or abnormal conduction mechanisms [17,18]. Meanwhile, the ions generated in the discharge channel are accelerated by the electric field near the channel exit, and a reaction thrust is formed [4,12].…”

Section: Introductionmentioning

confidence: 99%

Magnet stage optimization of 5 kW multi-cusped field thruster

Hu¹,

Yu²,

Shen³

2020

Plasma Sci. Technol.

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The multi-cusped field thruster is a unique electric thruster device, which has many advantages such as long lifetime, large-range thrust throttling ability, high thrust density, and low mass. The thruster employs several alternating polarity permanent magnets to create a periodic magnetic field with several cusps. Previous studies have indicated that the basic ionization and acceleration processes are directly related to the electron motion behavior, which mainly depends on the magnetic field characteristics. The magnet number and magnet stage length are two key magnetic field parameters that have important effects on the thruster performances. In this paper, both the magnet number and magnet stage length parameters are studied for the optimization of a 5 kW multi-cusped field thruster. The results indicate that the three-stage thruster has a better electron confinement than the two-stage thruster. It has lower ion energy loss at the wall, and shows a higher ionization rate. Therefore, the three-stage magnetic field is a superior magnetic field configuration. Besides, the three-stage magnetic field simulation results indicate that an optimal accelerating electric field distribution and ionization region distribution could be obtained when the magnet length ratio is 78:25:20.

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Section: Introductionmentioning

confidence: 99%

Magnet stage optimization of 5 kW multi-cusped field thruster

Hu¹,

Yu²,

Shen³

2020

Plasma Sci. Technol.

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“…Especially, Hall and ion thrusters of using xenon propellant have been used on many satellites [6,7]. There are investigations on EP devices by fluid and particlein-cell simulations [8][9][10][11] and diagnostic (probe, optical, and laser) methods [12][13][14][15][16][17] and studies on new structures and materials for these devices [18,19]. Xe collisional-radiative (CR) models for EP devices are also required to describe the kinetic behaviors of the excited species in numerical simulations as well as to predict the plasma emission spectra for diagnostic technique, e.g.…”

Section: Introductionmentioning

confidence: 99%

A xenon collisional-radiative model applicable to electric propulsion devices: II. Kinetics of the 6s, 6p, and 5d states of atoms and ions in Hall thrusters

Zhu

Wang

et al. 2019

Plasma Sources Sci. Technol.

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Electric propulsion devices of using xenon propellant are nowadays widely adopted for the space missions. A collisional-radiative (CR) model of xenon needs to be developed to understand the kinetic mechanisms of the excited and energetic species in these devices and also to support their optical diagnostics. Previously, due to limitations in the fundamental cross section data, Xe CR models focused on the atomic species; the ionic species, which also play important roles for the thrusters, were not studied in detail. In our previous paper, a fully relativistic Dirac B-spline R-matrix method was applied to calculate the relevant cross sections for electron collisions with the Xe+ ion. Based on these data, a comprehensive CR model—with the kinetics of metastable and excited levels of both Xe and Xe+ included—could be built. The calculated density distributions of atomic and ionic levels are examined by optical measurements in Hall thrusters in all of the four typical regions (near-anode-, ionization-, acceleration-, and plume-region). The special kinetic behaviors of the excited species are analyzed, and a set of rate coefficient data used for the Xe CR model is also provided.

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“…In reference [22], a diverging cusped field thruster was simulated with a one-dimensional fluid model, but the radial difference of the magnetic field and the magnetic mirror effect were not considered. In reference [23], a cusped field thruster was simulated with a one-dimensional fluid model but without considering electron temperature terms.…”

Section: Introductionmentioning

confidence: 99%

Simulation study of the influence of leak electrons on the discharge characteristics of a cusped field thruster

Liu

Niu

et al. 2019

Plasma Sci. Technol.

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Previous studies have shown that leak electrons in cusped field thrusters can move along the channel axis to the anode after crossing the magnetic cusp on the exit. In this paper, a onedimensional fluid model is built along two typical electron paths to study the influence of leak electrons on the discharge characteristics of a cusped field thruster, considering the electron temperature equation. It is found that the frequencies of low-frequency oscillations increase with a decrease in the proportion of leak electrons, which is related to an increase in the ion speed in the channel. Simulation results show that the position of the peak electron temperature is near the magnetic cusp on the exit and the position of the peak electron density is located downstream from the middle magnetic tip. With a decrease in the proportion of the leak electrons, the peak electron temperature and peak electron density decrease and the position of the peak electron density moves away from the exit, which is related to a decrease in the potential fall on the exit and an increase in confinement of electrons to the middle magnetic cusp.

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Fluid Simulation of a Cusped Field Thruster

Cited by 6 publications

References 10 publications

Magnet stage optimization of 5 kW multi-cusped field thruster

Magnet stage optimization of 5 kW multi-cusped field thruster

A xenon collisional-radiative model applicable to electric propulsion devices: II. Kinetics of the 6s, 6p, and 5d states of atoms and ions in Hall thrusters

Simulation study of the influence of leak electrons on the discharge characteristics of a cusped field thruster

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