No description available.

Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1988. / Abstract. Includes bibliographical references (leaves 59-61). Also available via the Internet.

Thesis--University of Wisconsin--Madison. / Typescript. Vita. eContent provider-neutral record in process. Description based on print version record. Includes bibliographies.

Thesis (M.S. in Astronautical Engineering)--Naval Postgraduate School, December 2006. / Thesis Advisor(s): Oscar Biblarz, Jose Sinibaldi. "December 2006." Includes bibliographical references (p. 63). Also available in print.

A pressurized hydrogen plasma jet is developed for pressure broadening experiments at pressures of from 4 to -20 atmospheres. Operation at low flow rates produced a plasma which was homogeneous in cross section with respect to electron density and temperature, with axial gradients, well suited for broadening experiments. The broadening of two Sil lines, X3905 Å and A2881 Å was studied. Widths and shifts due to broadening by electrons (Stark effect) and also by neutral hydrogen atoms were measured. The experimental results were compared with the theory of Griem in the case of the Stark broadening and with the Unsold theory of Van der Waals broadening for the case of the hydrogen perturbers. Comparison is also made between the experimental results and other experimental results for broadening by argon atoms. Significant disagreement was found, especially in the case of the broadening by hydrogen atoms. / Science, Faculty of / Physics and Astronomy, Department of / Graduate

No description available.

Thesis (M.Sc.Eng.)-University of KwaZulu-Natal, Durban, 2009. / Full text also available online. Scroll down for electronic link.

Thesis (Ph.D.)--Université Laval, 2001. / "A doctoral thesis submitted to Laval University." "November 2001." Includes bibliographical references. Also available via the World Wide Web.

Thesis (Ph. D.)--Ohio State University, 2007. / Title from first page of PDF file. Includes bibliographical references (p. 232-236).

Electric propulsion thrusters are considered to be candidates for microsatellites; ion engines are among the most scalable. Miniaturizing the ion engine will require novel concepts for the ionizer. MEMS, nanotechnology and other new technologies are expected to impact here. This thesis explores the use of these technologies to enable a new design for ion-thruster propellant ionization. An ideal approach, using expensive fabrication processes, is first described. This approach could prove to be a good method for testing and for the collection of precise data. A cost effective approach, on which our testing is based, is then discussed in detailed. After assembling a facility which uses existing vacuum systems and available instrumentation, we manufactured and tested miniature discharge geometries consisting of commercial 2â x2â copper-clad wafers. Three nominal insulator thicknessâ were used, 0.005,â 0.010â and 0.115.â The wafers were each drilled with 9 equal wholes of diameters 300, 400, and 500 m. A total of 12 wafers were tested (including 3 widths without wholes for a baseline) for the breakdown voltage as a function of argon pressure in the range of 10 to 1000 mTorr. Results indicate that argon breakdown may occur in the holes consistent with the classical Paschen curves.