Global ETD Search

41	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).
42	The effects of acceleration upon the linear burning rate of solid-rocket propellants Towson, Earl Raymond, 1938- January 1965 (has links) No description available. Rockets (Aeronautics) -- Fuel. Solid propellants.
43	Nonlinear combustion instability in liquid propellant rocket engines Powell, Eugene Alexander 12 1900 (has links) No description available. Liquid propellant rockets Combustion Research
44	An experimental investigation of the leading edge of diffusion flames Chiang, Hau-Jei 12 1900 (has links) No description available. Diffusion Solid propellant rockets Flame
45	Driving of axial acoustic fields by sidewall stabilized diffusion flames Chen, Tzengyuan 08 1900 (has links) No description available. Combustion Solid propellant rockets Flame
46	The role of surface layer processes in solid propellant combustion Chakravarthy, Satyanarayanan R. 12 1900 (has links) No description available. Rockets (Aeronautics) Fuel Combustion Flame
47	High pressure LOx/H₂ rocket engine combustion. Smith, Joshua J. January 2007 (has links) Title page, abstract and table of contents only. The complete thesis in print form is available from the University of Adelaide Library. / This thesis describes a study based on propellant injection conditions which was performed with a single shear coaxially injected liquid rocket engine combuster. Steady state operation was closely examined with the thrust chamber operating at sub critical, near critical and supercritical pressure levels with respect to the thermodynamic critical pressure of oxygen. It was found that unstable combustion could not be triggered whatsoever with LOx/H₂ propellants at near or supercritical pressure, irrespective of operating conditions. Such findings illustrate that operating near or above the critical pressure of propellants (oxygen) results in inherently stable combustion process over a broad range of operating conditions. / http://proxy.library.adelaide.edu.au/login?url= http://library.adelaide.edu.au/cgi-bin/Pwebrecon.cgi?BBID=1283711 / Thesis (Ph.D.) -- University of Adelaide, School of Mechanical Engineering, 2007
48	High pressure LOx/H₂ rocket engine combustion. Smith, Joshua J. January 2007 (has links) Title page, abstract and table of contents only. The complete thesis in print form is available from the University of Adelaide Library. / This thesis describes a study based on propellant injection conditions which was performed with a single shear coaxially injected liquid rocket engine combuster. Steady state operation was closely examined with the thrust chamber operating at sub critical, near critical and supercritical pressure levels with respect to the thermodynamic critical pressure of oxygen. It was found that unstable combustion could not be triggered whatsoever with LOx/H₂ propellants at near or supercritical pressure, irrespective of operating conditions. Such findings illustrate that operating near or above the critical pressure of propellants (oxygen) results in inherently stable combustion process over a broad range of operating conditions. / http://proxy.library.adelaide.edu.au/login?url= http://library.adelaide.edu.au/cgi-bin/Pwebrecon.cgi?BBID=1283711 / Thesis (Ph.D.) -- University of Adelaide, School of Mechanical Engineering, 2007
49	Design hazard analysis, and system level testing of a university propulsion system for spacecraft application Siebert, Joseph R., January 2009 (has links) (PDF) Thesis (M.S.)--Missouri University of Science and Technology, 2009. / Vita. The entire thesis text is included in file. Title from title screen of thesis/dissertation PDF file (viewed April 14, 2009) Includes bibliographical references (p. 201-203).
50	Feasibility of SCRAMJET technology for an intermediate propulsive stage of an expendable launch vehicle / Schafer, Michael D. January 2002 (has links) (PDF) Thesis (M.S. in Space Systems Operations)--Naval Postgraduate School, September 2002. / Thesis advisor(s): Stephen A. Whitmore, Charles M. Racoosin. Includes bibliographical references (p. 93). Also available online.

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