Internal plasma potential profiles in a laboratory-model Hall thruster

TLDR

The study used a high‑speed axial reciprocating probe system with a floating emissive probe to map plasma potential in the P5 Hall thruster discharge chamber at 300 V for 5.4 A and 10 A currents. Measurements showed that at 5.4 A the acceleration region begins upstream of the exit and extends downstream uniformly, while at 10 A it shifts downstream on the centerline, axial electric field profiles revealed a double‑peak structure at 5.4 A indicating ion deceleration, and discharge‑current perturbations coincided with peak electric fields, implying disturbances stem from Hall current perturbations rather than probe ablation.

Abstract

The Plasmadynamics and Electric Propulsion Laboratory High-speed Axial Reciprocating Probe system is used in conjunction with a floating emissive probe to measure plasma potential in the discharge chamber of the P5 Hall thruster. Plasma potential measurements are made at a constant voltage, 300 V, at two different discharge current conditions: 5.4 and 10 A. The plasma potential contours for the 5.4 A case indicate that the acceleration region begins several millimeters upstream of the exit plane, extends several centimeters downstream, and is uniform across the width of the discharge chamber. The 10 A case is similar to the 5.4 A case with the exception that the acceleration region is shifted downstream on centerline. Axial electric field profiles, computed from the measured potential, show a double peak structure in the 5.4 A case, indicating a zone of ion deceleration. Perturbations to the discharge current are shown to correspond spatially with the location of the peak electric field indicating that thruster perturbations may result from a disturbance to the Hall current, as opposed to ablation of probe material. This conclusion is supported by the lack of any observable material ablation.