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Micro-cathode arc thrusters have been widely used in micro-nanosatellites owing to their high specific impact, long lifetime, repeatable startup, low thrust and high control precision. Micro-cathode arc thrusters and their derivatives are currently being developed and optimized. The micro-cathode arc thruster can generate plasma stably and efficiently, and form a thrust force under a magnetic field with very low power in pulsed operation mode. This paper reviews the last 20 years of literature on micro-cathode arc thrusters, with a focus on papers published in this field in the last 5 years. In light of the development of the micro-cathode arc thruster and the latest research, the direction of future development and the application of key technologies are reviewed. Future micro-cathode arc propulsion systems are expected to exhibit higher reliability, longer lifetimes, higher specific impact, greater integration and higher thrust and to be operated in various modes. [ABSTRACT FROM AUTHOR]

The backpressure in the ground vacuum chamber significantly influences the discharge characteristics and performance of Hall effect thrusters (HETs). In this study, the propellant supplied from the anode and the propellant ingested from the background are treated as two separate components. Their ionization and acceleration processes are then studied numerically with a Particle-in-cell discharge model. It is found that the background propellant is mainly ionized near the outlet of the channel, thus affecting the local electron mobility and potential distribution inside and outside the channel. This results in an improvement in the ionization and acceleration of the anode propellant, an enhancement in the utilization of the propellant, and a reduction in the divergence of the ion beam. Consequently, the performance of the HETs is augmented. In particular, the increment in the thrust caused by the introduction of backpressure is not only due to the ionization and acceleration of the background propellant but also due to the improvement in the anode propellant discharge. [ABSTRACT FROM AUTHOR]

The effect of the magnetic-field intensity near an intermediate electrode in the discharge channel of a Hall thruster with a double-peaked configuration, on the thruster discharge and performance is investigated by applying the particle-in-cell Monte Carlo collision model. The result shows that by increasing the magnetic-field intensity near the intermediate electrode while keeping the magnetic-field peak intensity and position unchanged, the current received by the intermediate electrode is gradually reduced, whereas the propellant utilization and thrust are increased. Thus, the specific impulse and efficiency are improved. The efficiency can be increased by more than 10%. Increasing the magnetic-field strength near the intermediate electrode is conducive to improving the performance of the thruster, which provides a reference for the design of a Hall thruster with a double-peaked magnetic field. [ABSTRACT FROM AUTHOR]