Coupling plasma plume of a low-power magnetically shielded Hall thruster with a hollow cathode

Zhang, Guangchuan; Ren, Junxue; Liang, Wenzhong; Ouyang, Ning; Lü, Chao; Tang, Haibin

doi:10.1016/j.cja.2020.03.023

Cited by 21 publications

(2 citation statements)

References 24 publications

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“…Based on the operating principle, electric thrusters can be classified as electrostatic, electromagnetic and electrothermal. Various specific micro plasma thrusters, such as low-power Hall thruster, radio-frequency or microwave ion thrusters, field emission electric propulsion (FEEP), micro cathode arc thruster (μCAT), pulsed plasma thruster (PPT) and other technologies either working in steady state or pulse mode [4][5][6][7][8][9][10][11] are under continuous research. In general, the propellant of a thruster can be gaseous, liquid or solid.…”

Section: Introductionmentioning

confidence: 99%

Design and fabrication of a full elastic sub-micron-Newton scale thrust measurement system for plasma micro thrusters

Zhang

Hang²,

et al. 2021

Plasma Sci. Technol.

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In this work, a force measurement system is proposed to measure the thrust of plasma microthruster with thrust magnitude ranging from sub-micro-Newtons to hundreds micro-Newtons. The thrust measurement system uses an elastic torsional pendulum structure with a capacitance sensor to measure the displacement, which can reflect the position change caused by the applied force perpendicular to the pendulum axis. In the open-loop mode, the steady-state thrust or the impulse of the plasma micro-thruster can be obtained from the swing of the pendulum, and in the closed-loop mode the steady-state thrust can be obtained from the feedback force that keeps the pendulum at a specific position. The thrust respond of the system was calibrated using an electrostatic weak force generation device. Experimental results show that the system can measure a thrust range from 0 to 200 μN in both open-loop mode and closed-loop mode with a thrust resolution of 0.1 μN, and the system can response to a pulse bit at the magnitude of 0.1 mN s generated by a micro cathode arc thruster. The background noise of the closed-loop mode is lower than that of the open-loop mode, both less than 0.1 / mN Hz in the range of 10 mHz to 5 Hz.

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Section: Introductionmentioning

confidence: 99%

Design and fabrication of a full elastic sub-micron-Newton scale thrust measurement system for plasma micro thrusters

Zhang

Hang²,

et al. 2021

Plasma Sci. Technol.

Self Cite

View full text Add to dashboard Cite

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“…Because high-energy ions are produced outside the channel owing to the outward shift of the acceleration zone, wall erosion caused by high-energy ions can be avoided. It has been found that in a magnetically shielded Hall thruster, a wall profile that is parallel to the magnetic field lines can protect the wall from ion bombardment [21,22]. A chamfered wall in a 50 kW high-power magnetically shielded Hall thruster reduced the interaction intensity between the plasma and wall [23,24], and the wall was protected from ion bombardment.…”

Section: Introductionmentioning

confidence: 99%

Matching characteristics of magnetic field configuration and chamfered channel wall in a magnetically shielded Hall thruster

Wang

Zhong

et al. 2021

Plasma Sci. Technol.

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To date, the selection of the magnetic field line used to match the chamfered inner and outer channel walls in a magnetically shielded Hall thruster has not been quantitatively studied. Hence, an experimental study was conducted on a 1.35 kW magnetically shielded Hall thruster with a xenon propellant. Different magnetic field lines were chosen, and corresponding tangentially matched channel walls were manufactured and utilized. The results demonstrate that high performance and a qualified anti-sputtering effect cannot be achieved simultaneously. When the magnetic field lines that match the chamfered wall have a strength at the channel centerline of less than 12% of the maximum field strength, the channel wall can be adequately protected from ion sputtering. When the magnetic field lines have a strength ratio of 12%-20%, the thruster performance is high. These findings provide the first significant quantitative design reference for the match between the magnetic field line and chamfered channel wall in magnetically shielded Hall thrusters.

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Roll torque measurement and interpretation of low power Hall-effect thrusters

Zhang

et al. 2023

Acta Astronautica

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Coupling plasma plume of a low-power magnetically shielded Hall thruster with a hollow cathode

Cited by 21 publications

References 24 publications

Design and fabrication of a full elastic sub-micron-Newton scale thrust measurement system for plasma micro thrusters

Design and fabrication of a full elastic sub-micron-Newton scale thrust measurement system for plasma micro thrusters

Matching characteristics of magnetic field configuration and chamfered channel wall in a magnetically shielded Hall thruster

Roll torque measurement and interpretation of low power Hall-effect thrusters

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