Characteristics of ring-cusp discharge chambers

Matossian, J. N.; Beattie, J. R.

doi:10.2514/3.23415

Cited by 20 publications

(4 citation statements)

References 8 publications

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“…For micro DC ion thrusters, SmCo permanent magnet is used to generate strong and shortrange magnetic field, for example, ring-cusp magnet field, to raise the ionization rate by increasing the path length of primary electrons in the discharge chamber [9]. Indeed, ringcusp magnetic fields are widely used in ion thrusters of various sizes [10]. Placed in alternative polarity, magnets produce strong cusp boundaries near the wall.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of plasma behavior in a micro DC ion thruster using the particle-in-cell/Monte Carlo collision (PIC/MCC) method

Liu¹,

Cai²,

Zhang³

et al. 2021

J. Phys. D: Appl. Phys.

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Micro direct current (DC) ion thruster has advantages of small volume, light weight and significantly improved specific impulse performance compared to conventional chemical propulsion systems, thus having a wide application prospect in the tasks of cube-satellites and micro satellite networking systems. In this paper, a two-dimensional axisymmetric particle-in-cell/Monte Carlo collision model for the discharge chamber is developed for a micro DC ion thruster, which adopt the real configuration of original MiXI thruster with ring-cusp magnetic field. This model takes the thermal electron emission including the Schottky effect, various collision processes and the uneven background gas density distribution in the cathode-anode gap into account. The transient discharge process and the influence of operating conditions on the discharge process in the ionization chamber are presented for the first time so as to provide a detailed understanding of transport characteristics of plasma associated with the DC discharge process. Our calculated properties are compared with literature experimental data under similar conditions and qualitative and quantitative agreements are reached. The leak widths for charged species are obtained and closely related to charge separation. The simulations indicate that low neutral flow rate may lead to a discharge instability accompanied with oscillation of plasma quantities. These results lay a foundation for further optimization of thruster discharge chamber design in the future.

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Section: Introductionmentioning

confidence: 99%

Numerical investigation of plasma behavior in a micro DC ion thruster using the particle-in-cell/Monte Carlo collision (PIC/MCC) method

Liu¹,

Cai²,

Zhang³

et al. 2021

J. Phys. D: Appl. Phys.

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show abstract

“…In later tests it was found that ring-cusp discharges provide superior performance to Kaufmann discharges (and other configurations), avoid the concerns related to cathode pole piece wear for Kaufmann discharges and operate at lower discharge voltages (thus reducing erosion concerns for the screen grid) [2,3]. The most popular method for designing the magnetic field of ring-cusp ion thrusters is to ensure a sufficient 'maximum closed contour' (herein called B cc ) inside the discharge chamber [4].…”

Section: Background and Motivationmentioning

confidence: 99%

“…beam flatness (per equation ( 5)) J B total beam current J + B , j + B beam current and current density due to singly charged ions 1 Senior Engineer, Advanced Propulsion Technology Group. 2 Senior Research Scientist, Advanced Propulsion Technologies Group.…”

mentioning

confidence: 99%

Effects of magnetic field topography on ion thruster discharge performance

Wirz¹,

Goebel²

2008

Plasma Sources Sci. Technol.

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Traditional magnetic field design techniques for dc ion thrusters typically focus on closing a sufficiently high maximum closed magnetic contour, B cc , inside the discharge chamber. In this study, detailed computational analysis of several modified NSTAR thruster 3-ring and 4-ring magnetic field geometries reveals that the magnetic field line shape as well as B cc determines important aspects of dc ion thruster performance (i.e. propellant efficiency, beam flatness and double ion content). The DC-ION ion thruster model results show that the baseline NSTAR configuration traps the primary electrons on-axis, which leads to the high on-axis plasma density peak and high double ion content observed in experimental measurements. These

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“…[4][5][6][7] This may be overcome by employing wave induced plasma sources. Radiofrequency (RF) and microwave (MW) based plasma sources for propulsion has been developed by various researchers and space agencies around the world.…”

Section: Introductionmentioning

confidence: 99%

Development of a Low Power Multipole Confined Microwave Plasma Ion Thruster

Dey

Toyoda

Hirano

et al. 2014

AEROSPACE TECHNOLOGY JAPAN

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A modified magnetic multipolar plasma source is developed and tested for application as an ion thruster for space propulsion. The configuration consists of eight samarium-cobalt bar-magnets, symmetrically surrounding a cylindrical discharge volume of 21 mm diameter, with their magnetization in the radial direction. A donut magnet is placed at one axial end of the discharge volume with its magnetization along the cylindrical axis. A short monopole antenna, coaxial with the donut magnet is used for launching microwaves in the discharge volume. The resulting magnetic configuration due to the radial and axial magnetic fields, help in generation and sustenance of microwave induced electron cyclotron resonance plasma. Ions are extracted from the plasma by high voltage grids, attached to the end, opposite to the donut magnet. Two different magnetic configurations obtained by reversing the magnetization direction of the donut magnet are compared. Three dimensional magnetic field simulations and ion saturation current measurements at various microwave frequencies are used to determine the optimum magnetic configuration. Ion beam current extraction measurements, using the grids is carried out. Typical ion beam current of 9.9 mA is obtained, with calculated thrust of 0.63 mN at 8 W for 1600 MHz, with a Xenon mass flow rate of 20 g/s.

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Characteristics of ring-cusp discharge chambers

Cited by 20 publications

References 8 publications

Numerical investigation of plasma behavior in a micro DC ion thruster using the particle-in-cell/Monte Carlo collision (PIC/MCC) method

Numerical investigation of plasma behavior in a micro DC ion thruster using the particle-in-cell/Monte Carlo collision (PIC/MCC) method

Effects of magnetic field topography on ion thruster discharge performance

Development of a Low Power Multipole Confined Microwave Plasma Ion Thruster

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