Cathode erosion site distributions in an applied-field magnetoplasmadynamic thruster

Wu, Po-Liang; Wang, Yibai; Li, Yong; Wang, Baojun; Kaiyu, Zhang; Tang, Haibin; Cao, Jinbin

doi:10.1088/2058-6272/ab9172

Cited by 9 publications

(7 citation statements)

References 39 publications

(50 reference statements)

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“…Other recent works have focused on erosion. Erosion on MPDs varies with the relative position of the accelerating magnetic field and typically is found on the divergent part, a reduced anode mass flow rate leading to enlarged erosion on the cathode [113]. Erosion could be reduced by an applied axial converging/diverging magnetic field at the cathode.…”

Section: Magneto-plasma-dynamicmentioning

confidence: 99%

Electric Propulsion Methods for Small Satellites: A Review

2021

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Over 2500 active satellites are in orbit as of October 2020, with an increase of ~1000 smallsats in the past two years. Since 2012, over 1700 smallsats have been launched into orbit. It is projected that by 2025, there will be 1000 smallsats launched per year. Currently, these satellites do not have sufficient delta v capabilities for missions beyond Earth orbit. They are confined to their pre-selected orbit and in most cases, they cannot avoid collisions. Propulsion systems on smallsats provide orbital manoeuvring, station keeping, collision avoidance and safer de-orbit strategies. In return, this enables longer duration, higher functionality missions beyond Earth orbit. This article has reviewed electrostatic, electrothermal and electromagnetic propulsion methods based on state of the art research and the current knowledge base. Performance metrics by which these space propulsion systems can be evaluated are presented. The article outlines some of the existing limitations and shortcomings of current electric propulsion thruster systems and technologies. Moreover, the discussion contributes to the discourse by identifying potential research avenues to improve and advance electric propulsion systems for smallsats. The article has placed emphasis on space propulsion systems that are electric and enable interplanetary missions, while alternative approaches to propulsion have also received attention in the text, including light sails and nuclear electric propulsion amongst others.

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Section: Magneto-plasma-dynamicmentioning

confidence: 99%

Electric Propulsion Methods for Small Satellites: A Review

2021

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“…4,5 As such, the AF-MPDT has long been considered a promising choice for various mission scenarios, particularly those demanding high power. Nevertheless, it has significant drawbacks, such as cathode erosion, 6,7 low efficiency, 8 and demanding ground testing requirements, 9 which rendered these thrusters cost-ineffective until the past decade.…”

Section: Introductionmentioning

confidence: 99%

Investigating the impact of applied magnetic field and current on anode power deposition in AF-MPDT

Tang,

Zheng,

Liu

et al. 2024

AIP Advances

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The high temperature superconductors enhanced magnetoplasmadynamic thruster is a promising device for various space mission scenarios. However, a critical issue hindering the enhancement of the thruster’s performance is the problem of anode power deposition. Previous studies have identified the anode fall voltage as a major contributor to this power deposition. This paper introduces an approximate analytical formula for calculating anode power deposition resulting from anode fall voltage. The paper further analyzes and calculates the variation of anode fall voltage with an applied magnetic field and discharge current. The findings reveal a direct correlation between applied magnetic field and both anode fall voltage and power, indicating an increase with higher magnetic field values. In contrast, while the anode fall voltage experiences a slight decline with increased discharge current, the anode power deposition remains elevated due to the transition from field ionization to thermal ionization. To gain a comprehensive understanding of anode power deposition, an experiment was conducted to obtain measurements under different operating conditions, involving varying levels of applied magnetic field and discharge current. The experimental results align with the theoretical predictions. These insights have the potential to serve as a valuable reference for enhancing the efficiency of magnetoplasmadynamic thrusters, bringing us closer to unlocking the full potential of these remarkable propulsion systems in the realm of space exploration.

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“…In arcjets, these long-hour operations result in higher electrode thermal and electrical stress. Stress causes severe erosion of the insulators, seal joints, and electrodes, particularly at the cathode tip [12][13][14]. The phenomenon of electrode erosion has drawn the attention of researchers, for optimizing the performance and subsequently enhancing the durability of the thruster [15,16].…”

Section: Introductionmentioning

confidence: 99%

A three-dimensional numerical study on the effect of geometric asymmetry on arcjet thruster performance

Nandyala

Kumar

Jayachandran

2023

Plasma Sci. Technol.

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In an arcjet thruster, the cathode and constrictor degrade with time, and the electrical arc discharge may become unsymmetrical. In this work, a three-dimensional numerical model of hydrogen plasma arcjet is developed and validated to study the effect of unsymmetrical electric arc discharge on thruster performance. The unsymmetrical arc discharge is realized by introducing a radial shift of the cathode so that the cathode tip offset is 80 μm (25 % of the constrictor radius). Simulations are conducted for both axially centered cathode (coaxial) and off-centered cathode (non-coaxial) configurations with identical propellant flow rates and input current. Simulations show asymmetrical arc discharge in non-coaxial cathode configuration, resulting in azimuthally asymmetric Joule heating, species concentrations, and velocity field. This asymmetry continues as the plasma expands in the divergent section of the nozzle. Temperature, species concentrations, and axial velocity exhibit asymmetric radial distribution at the nozzle exit. The computed Joule heating was found to reduce with cathode shift, and consequently, the thrust and specific impulse of the thruster was decreased by about 6.6 %. In the case of the non-coaxial cathode, geometric asymmetry also induces a small side thrust.

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Cathode erosion site distributions in an applied-field magnetoplasmadynamic thruster

Cited by 9 publications

References 39 publications

Electric Propulsion Methods for Small Satellites: A Review

Electric Propulsion Methods for Small Satellites: A Review

Investigating the impact of applied magnetic field and current on anode power deposition in AF-MPDT

A three-dimensional numerical study on the effect of geometric asymmetry on arcjet thruster performance

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