Document Type
Article
Publication Date
5-2025
Abstract
Gridded Ion Thrusters are a satellite propulsion system that generate a Low- Temperature Plasma and electrostatically accelerates the ions to produce thrust at a high specific impulse. This work presents the design, testing, and initial characterization of a 3- cm diameter DC-discharge ring-cusp Gridded Ion Thruster that utilizes Argon as a propellant. The test infrastructure including vacuum chamber, propellant feed system, and power supplies are detailed, and operation of the ion thruster described. The material selections and design details have been presented, along with characterization based on steady-state propellant and power inputs described. In addition, a Heaterless Hollow Cathode design and test procedure has also been presented. The work presented here can be summarized as the preliminary investigation into various technologies and configurations for a low-thrust spacecraft propulsion system.
Recommended Citation
Mishra, Ishaan, "Design, Testing, and Characterization of a DC-Discharge Miniature Gridded Ion Thruster" (2025). Senior Project - Physics and Optical Engineering. 1.
https://scholar.rose-hulman.edu/physics_optics_seniorproject/1