Design of a Miniaturized Hall Thruster for Microsatellites

Microsatellite technology has become increasingly popular in recent years as it can offer significant cost savings, higher reliability, and is generally more affordable for a large variety of commercial applications. Since many microsatellite missions require considerable propulsion capabilities, miniaturization of the propulsion subsystem is critical in the design of most miniature spacecraft. A Hall thruster has been analyzed, designed, and manufactured for operation at considerably lower than standard power levels. This particular engine was chosen as one of the most mature electric propulsion devices. In an effort to miniaturize the thruster, a number of complications have been encountered. Of the most troublesome were higher magnetic field requirements, larger internal heat fluxes and temperatures, and complexities associated with manufacturing of the various miniaturized components. These and other related issues were addressed and analyzed in this work. The results of our findings are reflected as major changes to the conventional Hall thruster design. The thruster has been manufactured and tested for operation in a vacuum chamber. Preliminary assessment indicates excellent performance matching with the existing devices, hence opening new opportunities for the use of microthrusters in a variety of spacecraft applications. Thesis Supervisor: Manuel Martinez-Sanchez Title: Professor