Simulation of Flowing Plasma Discharges With Applications to Lasers, Fuel Cells, and Microthrusters

Small satellites (few kg) require muN - mNs thrust for station keeping with nominal power requirements (few Watts). MDs deposit power to flowing Ar (at 10s Torr), and the incremental velocity, gas temperature, and thrust are studied. Due to the large surface-to-volume ratio and low Reynolds number, heat conduction to the walls and viscous losses play a significant role in determining thrust. Geometrical parameters like nozzle length and angle, and flow parameters such as power, pressure, and flow rate can be used to optimize the thrust.

Name thesis:degree_name

Ph.D.

Level thesis:degree_level

Dissertation

Discipline thesis:degree_discipline

Aerospace Engineering

Grantor

University of Illinois at Urbana-Champaign

Year dc:date

2015

Author dc:creator

• Arakoni, Ramesh A.

Contributors dc:contributor

• Kushner, Mark J.

• Physics, Fluid and Plasma

Language dc:language

eng

Identifier

(MiAaPQ)AAI3290166

OAI identifier oai:identifier

oai:www.ideals.illinois.edu:2142/85102