Design, characterization, and performance of a valveless pulse detonation engine
By: Robert G. Johnson
Contributors: Naval Postgraduate School (U.S.)
Publisher: Naval Postgraduate School; Available from National Technical Information Service
Published: 2000
Place of publication: Monterey, Calif; Springfield, Va
Language: eng
Number of pages: 106
Description: Current interest in developing a low cost, less complex tactical missile propulsion system that operates on readily available liquid fuels and can operate from low subsonic to a flight Mach number of 5 is driving research on pulse detonation engines. This research program involved the design, construction, and testing of a valveless Pulse Detonation Engine using a JP-10/ air mixture as the primary combustible reactants. A small JP-10/oxygen pre- detonation tube was used to initiate the detonation in the JP-10/air mixture in the engine. The engine was tested at various inlet conditions and equivalence ratios in order to determine the detonable regime of the fuel/air mixture. The original area transition from the pre-detonation tube to the main combustion tube appeared to be too extreme, so a tube was added to extend the pre- detonation tube into the throat of a shock focusing device inserted flush with the head end of the main combustion tube to promote more favorable transition conditions.
Notes: Thesis advisor(s):  Brophy, Christopher.

"June 2000."

Thesis (M.S. in Astronautical Engineering)--Naval Postgraduate School, June 2000.

Includes bibliographical references (p. 103)

Approved for public release, distribution unlimited--Cver.

Also available online.

Mode of access: World Wide Web.

System requirements: Adobe Acrobat reader.

US Navy (USN) author.

updated dlb 11/2/06