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Simulation of flowing plasma dischar...

Arakoni, Ramesh A.

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Simulation of flowing plasma discharges with applications to lasers, fuel cells, and microthrusters.

Record Type:	Language materials, printed : Monograph/item
Title/Author:	Simulation of flowing plasma discharges with applications to lasers, fuel cells, and microthrusters./
Author:	Arakoni, Ramesh A.
Description:	231 p.
Notes:	Adviser: Mark J. Kushner.
Contained By:	Dissertation Abstracts International68-11B.
Subject:	Engineering, Aerospace. -
Online resource:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=3290166
ISBN:	9780549339717

Simulation of flowing plasma discharges with applications to lasers, fuel cells, and microthrusters.
Arakoni, Ramesh A.

Simulation of flowing plasma discharges with applications to lasers, fuel cells, and microthrusters. - 231 p.

Adviser: Mark J. Kushner.

Thesis (Ph.D.)--University of Illinois at Urbana-Champaign, 2007.

Plasmas are gases composed of electrons, ions, and neutral species. Typically, the electrons and heavy species are in thermal non-equilibrium, and impact by energetic electrons breaks the feedstock gases into desired products. The plasma hydrodynamics is studied by solving Maxwell's and transport equations in 2-d unstructured meshes. A plug-flow model is used for large reaction chemistries. In this thesis we look at the following problems:

ISBN: 9780549339717Subjects--Topical Terms:

1018395
Engineering, Aerospace.

Simulation of flowing plasma discharges with applications to lasers, fuel cells, and microthrusters.
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020 $a 9780549339717
035 $a (UMI)AAI3290166
035 $a AAI3290166
040 $a UMI $c UMI
100 1 $a Arakoni, Ramesh A. $3 1269378
245 1 0 $a Simulation of flowing plasma discharges with applications to lasers, fuel cells, and microthrusters.
300 $a 231 p.
500 $a Adviser: Mark J. Kushner.
500 $a Source: Dissertation Abstracts International, Volume: 68-11, Section: B, page: 7462.
502 $a Thesis (Ph.D.)--University of Illinois at Urbana-Champaign, 2007.
520 $a Plasmas are gases composed of electrons, ions, and neutral species. Typically, the electrons and heavy species are in thermal non-equilibrium, and impact by energetic electrons breaks the feedstock gases into desired products. The plasma hydrodynamics is studied by solving Maxwell's and transport equations in 2-d unstructured meshes. A plug-flow model is used for large reaction chemistries. In this thesis we look at the following problems:
520 $a Oxygen-iodine lasers are used in defense applications, and in metal cutting. Collisions between O2(1Delta) and I produces the I* (1.315 mum), and the fraction of O2 in the 1Delta state (yield) determines the efficiency. The yield is a function of discharge efficiency (He/O2 mixture), although it scales sub-linearly with power due to dissociation. O2(1Delta) production is efficient at electron temperatures (Te) of 1-1.5 eV, and uniform power deposition, addition of NO improves this efficiency. O atoms are detrimental to the laser, and they are managed by adding small amounts of NO/NO2 which recoup O atoms. The optical gain in the laser cavity is optimized using parameters like flow rates of NO/NO2, I2 for a given power.
520 $a An in-situ creation of H2 using NH3 microdischarges is explored for use in portable fuel cells. Electron-impact reactions and neutral chemistry in the afterglow are important sources of H and H2 . Te significantly affects the dissociation of NH3 especially at low NH3 concentrations. Conversion of NH3 is efficient at lower flow speeds, and higher energy deposition per NH3. A tradeoff exists between the energy required to create a H2 molecule and number of H2 molecules produced per NH3.
520 $a 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.
590 $a School code: 0090.
650 4 $a Engineering, Aerospace. $3 1018395
650 4 $a Physics, Fluid and Plasma. $3 1018402
690 $a 0538
690 $a 0759
710 2 $a University of Illinois at Urbana-Champaign. $3 626646
773 0 $t Dissertation Abstracts International $g 68-11B.
790 $a 0090
790 1 0 $a Kushner, Mark J., $e advisor
791 $a Ph.D.
792 $a 2007
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=3290166