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dc.contributor.advisorBrophy, Christopher
dc.contributor.advisorSinibaldi, Jose
dc.contributor.advisorGopinath, Ashok
dc.contributor.authorKutrieb, Joshua M.
dc.date.accessioned2012-03-14T17:47:19Z
dc.date.available2012-03-14T17:47:19Z
dc.date.issued2001-12
dc.identifier.urihttp://hdl.handle.net/10945/5955
dc.description.abstractInterest in accurate detection and targeting of aggressor missiles has received considerable interest with the national priority of developing a missile defense system. Understanding the thermal signatures of the exhaust plumes of such missiles is key to accomplishing that mission. Before signature models can be precisely developed for specific rockets, the radiation of the molecular or combustion species within those plumes must be accurately predicted. A combination translation / rotation scanning diagnostic technique has been developed to map the combustion species of a rocket plume and characterize its radiation properties. Using new infrared spectrometer and fiber optic cable technology to transmit the signal spectrum of interest, the custom designed mechanism can sweep through two dimensions of a steady-state rocket exhaust. A glow bar, or blackbody simulator, is shuttered on the opposite side of the plume, allowing the spectrometer to measure both the emission and absorption spectra. This thesis demonstrated the first time use of fiber optic cable to transmit infrared emission / absorption (E/A) spectra from a rocket plume to an infrared detector. This new fiber optic configuration allows for rapid translation and rotation around the rocket plume, establishing the capability for rapid spatial characterization of the combustion species present. Experimental results may then be compared to DoD rocket plume model predictions to highlight areas for improvement.en_US
dc.description.urihttp://archive.org/details/rocketplumetomog109455955
dc.format.extentxiv, 76 p. ;en_US
dc.publisherMonterey, California. Naval Postgraduate Schoolen_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.en_US
dc.subject.lcshRocket enginesen_US
dc.subject.lcshExhaust emissionsen_US
dc.subject.lcshPlumes (Fluid dynamics)en_US
dc.titleRocket plume tomography of combustion speciesen_US
dc.typeThesisen_US
dc.contributor.corporateNaval Postgraduate School (U.S.)
dc.description.serviceUS Air Force (USAF) authoren_US
dc.identifier.oclc640961386
etd.verifiednoen_US


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