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oai:www.ideals.illinois.edu:2142/85102 2023-07-11 col_2142_5131 col_2142_14800 com_2142_5130 com_2142_14799 com_2142_234

Kushner, Mark J. Arakoni, Ramesh A. 2015-09-25T22:34:25Z 2015-09-25T22:34:25Z 10000-01-01 2007 2007 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). 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. http://hdl.handle.net/2142/85102 (MiAaPQ)AAI3290166 eng Physics, Fluid and Plasma Simulation of Flowing Plasma Discharges With Applications to Lasers, Fuel Cells, and Microthrusters text Aerospace Engineering Aerospace Engineering University of Illinois at Urbana-Champaign Dissertation Ph.D.