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An evaluation of marine propulsion engines for several Navy shipsStanko, Mark Thomas January 1992 (has links)
Thesis (Nav. E.)--Massachusetts Institute of Technology, Dept. of Ocean Engineering, 1992 and Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 1992. / Thesis Advisors: Wilson, D. G. ; Carmichael, A. Douglas. "May 1992." Description based on title screen as viewed on March 30, 2009 Includes bibliographical references (p. 57-58). Also available in print.
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The development And Testing Of Pulsed Detonation Engine Ground Demonstrators /Panicker, Philip Koshy. January 2008 (has links)
Thesis (Ph.D.) -- University of Texas at Arlington, 2008.
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Simulation of direct current microdischarges for microthruster applicationsKothnur, Prashanth Srinivasa 28 August 2008 (has links)
Not available / text
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A technique for rapid prediction of aftbody nozzle performance for hypersonic launch vehicle designBradford, John Edward 08 1900 (has links)
No description available.
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Analysis of simulation tools for the study of advanced marine power systemsBrochard, Paul Eugene. January 1992 (has links)
Thesis (M.S. in Electrical Engineering)--Naval Postgraduate School, September 1992. / Thesis Advisor: Williams, Stephen M. "September 1992." Description based on title screen as viewed on March 10, 2009. Includes bibliographical references (p. 103-105). Also available in print.
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Investigation of transient plasma ignition for a Pulse Detonation Engine /Rodriguez, Joel. January 2005 (has links) (PDF)
Thesis (M.S. in Astronautical Engineering)--Naval Postgraduate School, March 2005. / Thesis Advisor(s): Jose O. Sinibaldi. Includes bibliographical references (p. 39-41). Also available online.
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Design of a coaxial split flow pulse detonation engineHall, Philip D. 06 1900 (has links)
Future Navy Capabilities indicate the need for a supersonic cruise missile. Thus the need exists for a low cost, light-weight, and efficient means of supersonic propulsion. NPS has been developing the Pulse Detonation Engine, which in theory has a thermodynamic efficiency greater than 50% as compared to 35% for state of the art constant-pressure cycles currently in use in gas turbines/ramjets/scramjets. Nonetheless, there are two major problems in the development of this engine. These are the increase of the propulsive efficiency by removing the oxygen-assisted initiator currently in use, and the reduction of internal total pressure losses caused by the highly constrictive internal flow-path geometry currently required to promote the deflagration to detonation transition (DDT). The aforementioned problems have been addressed and a viable design proposed through the implementation of a novel Transient Plasma Ignition system and a split-flow path engine geometry as described in this work. Future work will concentrate on the development of a performance measurement test rig to experimentally assess the designs presented herein. / US Navy (USN) author.
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Modelling of the propulsion mechanism for a miniaturized corona ionization thrusterKrommenhoek, Marinus Frans 30 October 2015 (has links)
A dissertation submitted to the Faculty of Science, University of Witwatersrand, Johannesburg, in fulfilment of the requirements for the degree of Master of Science. / In this dissertation a recipe has been outlined on how thrust can be calculated
using the conservation of momentum in continuum form. With the aim
of modelling a CORION (corona ionization) like thruster in mind it was then
argued using a much simpler system and stochastic calculus why a statistical
description of the system is necessary. From this the one-particle distribution
emerged as a natural tool for the description of a system su cient for the determination
of the system's thrust.This was followed by a short investigation
into the background of non-equilibrium statistical mechanics, both classical and
quantum, necessary to understand how one-particle distributions could be derived
formally and in a physically consistent way. Mass
ow and current-voltage experiments of the CORION like thrust system, necessary for characterization of part of the system, were conducted. This led to a proposal for a modelling strategy, consisting of merging di erent modelling approaches and descriptions
considered throughout the dissertation.
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Experimental investigation of the mini-magnetospheric plasma propulsion prototype /Ziemba, Timothy Martin. January 2003 (has links)
Thesis (Ph. D.)--University of Washington, 2003. / Vita. Includes bibliographical references (p. 165-170).
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The ferroelectric plasma thrusterKemp, Mark A., January 2008 (has links)
Thesis (Ph. D.)--University of Missouri-Columbia, 2008. / The entire dissertation/thesis text is included in the research.pdf file; the official abstract appears in the short.pdf file (which also appears in the research.pdf); a non-technical general description, or public abstract, appears in the public.pdf file. Title from title screen of research.pdf file (viewed on June 9, 2009) Vita. Includes bibliographical references.
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