Ryan Pahl
Missouri University of Science & Technology
Advisor: Dr. Hank Pernicka

Abstract
In order to optimize pulsed plasma thrusters performance, the amount surface scorching that results from repetitive firing of the pulsed plasma thruster needs to be reduced, and a model generated for the thrust produced by each pulse. By use of a threaded annular-electrode pulsed plasma thruster and vacuum chamber, data will be collected and combined with established findings to construct a model for the thrust generated by a given configuration. Additionally, the rate of scorching of the threaded thruster as compared to the standard configuration will be determined. By predicting the characteristics of a given pulsed plasma thruster, the system can be optimized to generate only the thrust required. This will allow for better component selection, which will reduce overall weight while increasing overall efficiency and delivering a more beneficial satellite propulsion system.
NOTE: This work was sponsored in part by the Exploration Systems Mission Directorate.