Numerical Modeling of a 17.8-GHz Microwave Electrothermal Thruster
Open Access
Author:
Sinha, Swarna
Area of Honors:
Aerospace Engineering
Degree:
Bachelor of Science
Document Type:
Thesis
Thesis Supervisors:
Michael Matthew Micci, Thesis Supervisor Dr. Sven G Bilén, Thesis Supervisor Dennis K Mclaughlin, Thesis Honors Advisor Robert Graham Melton, Faculty Reader
Keywords:
propulsion microwave electrothermal electric aerospace engineering
Abstract:
This research is focused on the development of a CubeSat-scale Microwave Electrothermal Thruster (MET). The MET is an in-space propulsion device that utilizes high electric field intensity generated by a microwave antenna to ignite and sustain free-floating plasma within a cylindrical, electromagnetic resonant cavity. The propellant gas is heated and then expanded through a nozzle. Previous iterations of MET frequencies of 2.45 GHz, 7.5 GHz, 8 GHz, 14.5 GHz, and 30 GHz have all examined the performance of this technology. Higher frequency leads to smaller thruster size, lower power requirements, and a lighter overall propulsion system, albeit at lower thrust levels. This thesis discusses the design of a 17.8-GHz thruster cavity based on numerical simulations of electric field intensity within the thruster’s resonant cavity using COMSOL Multiphysics.
