Experimental Study of a Low-Voltage Pulsed Plasma Thruster for Nanosatellites

TL;DR

This study demonstrates a low-voltage coaxial pulsed plasma thruster suitable for nanosatellites, operating efficiently at reduced voltages with detailed imaging and erosion analysis to understand plasma and cathode behavior.

Contribution

Introduces a novel low-voltage pulsed plasma thruster design with experimental validation and cathode imaging, advancing nanosatellite propulsion technology.

Findings

Successful operation at 100-200 V discharge voltage

Diffuse arc attachment observed at higher pressures

Cathode erosion rates quantified at different pressures

Abstract

In this paper, a coaxial pulsed plasma thruster was designed, built, and tested. This design confirmed PPT operation at substantially reduced discharge voltages of 100 to 200 V across the discharge plasma at a discharge current level of 10.4 kA similar to magnetoplasmadynamic arcs. The PPT cathode was imaged with an ICCD camera over a wide range of pressures, and the photos indicated "spotless" diffuse arc attachment to the cathode at higher pressures, and the appearance of conventional cathode spots at lower pressures. Cathode erosion rate measurements support the conclusion of "spotless" operation at higher pressures and the presence of cathode spots at lower pressures (the erosion rates of 16.194 ug/C and 40.785 ug/C were measured at 4 Torr and 3.5e-5 Torr, respectively).