{"id":{"repo_id":"uiuc","oai_identifier":"oai:www.ideals.illinois.edu:2142/85102"},"canonical_url":"https://search.dev.ndltd.org/etd/uiuc/oai:www.ideals.illinois.edu:2142/85102","repository":{"repo_id":"uiuc","name":"University of Illinois - Urbana-Champaign","base_url":"https://www.ideals.illinois.edu/oai-pmh"},"display":{"title":"Simulation of Flowing Plasma Discharges With Applications to Lasers, Fuel Cells, and Microthrusters","abstract":"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.","abstract_html":"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.","abstract_has_math":false,"creators":["Arakoni, Ramesh A."],"institution":"University of Illinois at Urbana-Champaign","degree_name":"Ph.D.","degree_level":"Dissertation","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":["Kushner, Mark J."],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2015,"date_issued":"2015-09-25T22:34:25Z","date_published":"2015-09-25T22:34:25Z","updated_at":"2026-07-22T22:26:24Z","subjects":["Physics, Fluid and Plasma"],"languages":["eng"],"rights":[],"rights_urls":[],"identifier_entries":[{"key":"dc:identifier","label":"Identifier","values":["(MiAaPQ)AAI3290166"],"render_values":[{"text":"(MiAaPQ)AAI3290166","href":null,"code":true}]}]},"links":{"outbound_url":"http://hdl.handle.net/2142/85102","outbound_label":"Handle","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Kushner, Mark J."]},{"key":"dc:creator","label":"Author","values":["Arakoni, Ramesh A."]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2015-09-25T22:34:25Z","10000-01-01","2007"]},{"key":"dc:type","label":"Dc Type","values":["text"]},{"key":"thesis:degree_discipline","label":"Discipline","values":["Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Dissertation"]},{"key":"thesis:degree_name","label":"Degree Name","values":["Ph.D."]},{"key":"thesis:institution_name","label":"Thesis Institution Name","values":["University of Illinois at Urbana-Champaign"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["Physics, Fluid and Plasma"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language","label":"Dc Language","values":["eng"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["http://hdl.handle.net/2142/85102","(MiAaPQ)AAI3290166"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["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.","Made available in DSpace on 2015-09-25T22:34:25Z (GMT). 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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.","Made available in DSpace on 2015-09-25T22:34:25Z (GMT). No. of bitstreams: 2 license.txt: 4848 bytes, checksum: 96035ab3f5e1c23cc7138a224ce498bd (MD5) 3290166.pdf: 6091448 bytes, checksum: b8122bd7bfebed58e84a70a4414bb4bf (MD5) Previous issue date: 2007","Embargo set by: Seth Robbins for item 86383 Lift date: Forever Reason: Restricted to the U of I community idenfinitely during batch ingest of legacy ETDs","Restricted to the U of I community idenfinitely during batch ingest of legacy ETDs","U of I Only","231 p.","Thesis (Ph.D.)--University of Illinois at Urbana-Champaign, 2007."],"dc:identifier":["http://hdl.handle.net/2142/85102","(MiAaPQ)AAI3290166"],"dc:language":["eng"],"dc:subject":["Physics, Fluid and Plasma"],"dc:title":["Simulation of Flowing Plasma Discharges With Applications to Lasers, Fuel Cells, and Microthrusters"],"dc:type":["text"],"thesis:degree_discipline":["Aerospace Engineering"],"thesis:degree_level":["Dissertation"],"thesis:degree_name":["Ph.D."],"thesis:institution_name":["University of Illinois at Urbana-Champaign"]},"updated_at":"2026-07-22T22:26:24Z"}