Plume Characterization of a Novel Electrically Ignited Solid Propellant
Department
Mechanical and Aerospace Engineering
Major
Aerospace and Mechanical Engineering
Research Advisor
Rovey, Joshua L.
Advisor's Department
Mechanical and Aerospace Engineering
Funding Source
Opportunities for Undergraduate Research Experience (OURE)
Abstract
Electric propulsion is a current mainstay within the aerospace engineering field used for satellites and deep-space spacecraft. For a newly developed propellant, it is extremely important to understand and quantify the plasma plume behavior exhibited during thruster firing. This work researches and develops significant plasma diagnostics to characterize the plume of an innovative electrically ignited solid propellant. Diagnostics developed include a Triple Langmuir Probe, Faraday Cup, and Single Langmuir Probe Rake. These tools allow the quantification of chief plasma parameters such as electron number density and the electron-fluid temperature. Results from the application of these diagnostics will be presented to show successful plasma characterization.
Biography
Johnathan Sumpter is currently an undergraduate student double majoring in Aerospace and Mechanical Engineering at the Missouri University of Science and Technology. His research interests include: plasma applications within spacecraft, astrodynamics, and spacecraft/launch vehicle propulsion. Extra-curricular activities have included the Advanced Aero-Vehicle Group, M-SAT, and Sigma Gamma Tau. Past internship experience was gained at Space Exploration Technologies in Hawthorne, CA. Upon graduation in December 2015, John expects to attend graduate school internationally for spacecraft propulsion.
Research Category
Engineering
Presentation Type
Poster Presentation
Document Type
Poster
Location
Upper Atrium/Hall
Presentation Date
15 Apr 2015, 1:00 pm - 3:00 pm
Plume Characterization of a Novel Electrically Ignited Solid Propellant
Upper Atrium/Hall
Electric propulsion is a current mainstay within the aerospace engineering field used for satellites and deep-space spacecraft. For a newly developed propellant, it is extremely important to understand and quantify the plasma plume behavior exhibited during thruster firing. This work researches and develops significant plasma diagnostics to characterize the plume of an innovative electrically ignited solid propellant. Diagnostics developed include a Triple Langmuir Probe, Faraday Cup, and Single Langmuir Probe Rake. These tools allow the quantification of chief plasma parameters such as electron number density and the electron-fluid temperature. Results from the application of these diagnostics will be presented to show successful plasma characterization.
