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The strength and shape of the magnetic field are the core factors in the design of the Hall thruster. However, Hall current can affect the distribution of static magnetic field. In this paper, the Particle-In-Cell (PIC) method is used to obtain the distribution of Hall current in the discharge channel. The Hall current is separated into a direct and an alternating part to calculate the induced magnetic field using Finite Element Method Magnetics (FEMM). The results show that the direct Hall current decreases the magnetic field strength in the acceleration region and also changes the shape of the magnetic field. The maximum reduction in radial magnetic field strength in the exit plane is 10.8 G for an anode flow rate of 15 mg/s and the maximum angle change of the magnetic field line is close to 3° in the acceleration region. The alternating Hall current induces an oscillating magnetic field in the whole discharge channel. The actual magnetic deformation is shown to contain these two parts.

The radio frequency ion thruster (RIT) is an electric propulsion device that utilizes radio frequency (RF) power to ionize propellants; thus, its performance is influenced by the frequency and matching network of the RF. In this study, an L&T type wide-range matching network was employed to experimentally investigate the performance of a miniature RIT with 4 cm diameter at different frequencies. The experimental results show that changing the matching parameters of the L&T network at the same frequency leads to changes in the effective quality factor and varying performances of the thruster; under similar effective quality factors, changing the frequency does not significantly affect the performance of the thruster; however, the plasma resistance exhibits frequency dependence. As the frequency increases, the effective collision frequency increases, leading to an increase in plasma resistance, which is beneficial for improving the performance of the thruster at high frequencies. Finally, a set of methods for quickly comparing the performance of RITs was summarized based on the effective quality factor. These research results are also instructive for improving the ionization of induction-coupled discharge devices of other sizes. [ABSTRACT FROM AUTHOR]

The energy supply mode of a micro-cathodic arc thruster (μ-CAT) was adjusted based on the charge and discharge characteristics of the energy storage element, and the cathode discharge characteristics of μ-CAT were studied under different energy supply modes. We applied an electrical method to measure the discharge characteristics of μ-CAT, with an enhanced intensified charge coupled device spectrum detector to measure the plasma parameters of μ-CAT, allowing analysis of the internal logic among thruster plasma parameters, arc discharge characteristics, and thruster energy supply mode. The mechanisms of μ-CAT were analyzed and characteristics of accumulated discharge, energy distribution, and ion velocity distribution of thruster were compared under different energy supply modes to obtain the effect of the energy supply mode on the discharge characteristics of the interelectrode of μ-CAT. The results show that the energy supply mode of μ-CAT affected the ionization characteristics and ionization stability of the micro-cathodic arc thruster, causing a multistage ionization difference in the cathode metal target. This would not only affect the propulsion performance of the thruster, but also affect the change of the number of particles in the cathode region in a single discharge cycle. [ABSTRACT FROM AUTHOR]

This paper proposes increasing the width of the discharge channel to improve the specific impulse of Hall thrusters. In our study, we significantly increased the achievable channel width by optimizing the magnetic circuit topology, and the design freedom of the Hall thruster was improved. A prototype of a wide-channel high-specific-impulse Hall thruster was designed and experimentally verified. The effects of channel width on the discharge process and the characteristics of an aft-loaded magnetic field Hall thruster were investigated. The high-intensity luminous region did not diffuse radially with an increase in the channel width, and the plasma was always concentrated near the channel centerline. A wider channel is more conducive for improving the propellant utilization efficiency, thereby effectively improving the specific impulse of the Hall thruster. By optimizing the discharge channel width, the upper limit of the discharge voltage was increased, and the maximum specific impulse was increased from 3170 to 3794 s, a relative improvement of 20%. The effect of the specific impulse improvement at the same discharge voltage was analyzed and discussed. The results of this study are significant for the design of high-specific-impulse Hall thrusters. [ABSTRACT FROM AUTHOR]

A typical Hall thruster is powered by a constant-voltage power supply. In this study, to ensure the normal operation of Hall thrusters at lower power conditions, we applied pulse modulation technology to supply power to a 600-W Hall thruster. The results show that, when the input power of the thruster was within the rated power range, the thrust and efficiency of the thruster were slightly reduced under pulsating mode compared with those of direct current (DC) operation. However, the thrust-to-power ratio of the thruster under pulsating mode was superior to that under DC operation at low power (<350 W). The thrust-to-power ratio under pulsating mode was improved to 77.5 mN/kW at 210 W compared with that under DC operation (70 mN/kW). Meanwhile, we found that the stable operating boundary of the thruster under pulsating mode significantly widened at high frequencies. A 600-W Hall thruster under pulsating mode can operate at a lowest power of 66.8 W, which is an order of magnitude lower than the rated power. The thrust and anode efficiency under pulsating mode at 68.8 W were 4.3 mN and 7.8%, respectively. [ABSTRACT FROM AUTHOR]

This letter reports a new magnetic field-enhanced radio frequency (RF) ion thruster, which uses a high-frequency shielding network to isolate the direct current and RF supplies. This provides an additional magnetic field for a novel magnetized RF ion thruster (HRIT-4M) without changing the original thruster structure. The results show an improvement in the performance of an RF ion thruster in a verified magnetic field. Compared to other excitation structures, this excitation structure is simpler and more efficient. However, it is influenced by factors such as the size of the discharge chamber and pressure, which should be further investigated. [ABSTRACT FROM AUTHOR]

In this paper, the relationship between the morphology of the cathode crater and plasma ionization between thrusters is studied by adjusting the input energy of the micro-cathode arc thruster (μ CAT). We monitor the morphology of the cathode crater of the μ CAT using scanning electron microscopy and explore the relationship between the crater morphology and the internal energy loss of the cathode crater. This relationship, combined with the numerical simulation results, is used to monitor the ionization between the electrodes of the μ CAT using an enhanced intensified charge coupled device spectrum detector. The effect of cathode crater morphology on the ionization of the propellant during the operation of the μ CAT is determined. The results show that with a change in the input power processing unit voltage, the external profile and depth-to-diameter ratio of the cathode crater change, resulting in a change in the internal energy loss of the thruster cathode crater and then affecting the ionization efficiency of the cathode working fluid in the μ CAT. Under the condition of basically unchanged cathode feed energy flow density, reasonable adjustment of the depth-to-diameter ratio of the cathode crater can effectively improve the ionization efficiency of the cathode working fluid in the μ CAT. [ABSTRACT FROM AUTHOR]

Previous research has demonstrated that the decoupled method improves the performance of the electroaerodynamic (EAD) thruster and that the overall characteristics of the EAD thruster are influenced by the ionization and acceleration processes. In this study, a decoupled EAD thruster structure is proposed, and the influence of the auxiliary electrode is experimentally explored. The characteristics of electrical discharge imaging and thrust performance are studied in detail to demonstrate the performance of the decoupled EAD thruster. The experimental results demonstrate that the auxiliary electrode significantly influences the characteristics of the ionization and acceleration processes, and the condition of L1 = 5 mm is the best position of the auxiliary electrode for this experiment. There is an optimal auxiliary electrode arrangement that can improve the performance of the EAD thruster. [ABSTRACT FROM AUTHOR]