Accession Number : ADA587288


Title :   Combustion and Magnetohydrodynamic Processes in Advanced Pulse Detonation Rocket Engines


Descriptive Note : Doctoral thesis


Corporate Author : CALIFORNIA UNIV LOS ANGELES


Personal Author(s) : Cole, Lord K


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a587288.pdf


Report Date : Oct 2012


Pagination or Media Count : 251


Abstract : A number of promising alternative rocket propulsion concepts have been developed over the past two decades that take advantage of unsteady combustion waves in order to produce thrust. These concepts include the Pulse Detonation Rocket Engine (PDRE), in which repetitive ignition, propagation, and reflection of detonations and shocks can create a high pressure chamber from which gases may be exhausted in a controlled manner. The Pulse Detonation Rocket Induced Magnetohydrodynamic Ejector (PDRIME) is a modification of the basic PDRE concept, developed by Cambier (1998), which has the potential for performance improvements based on magnetohydrodynamic (MHD) thrust augmentation. The PDRIME has the advantage of both low combustion chamber seeding pressure, per the PDRE concept,and efficient energy distribution in the system, per the rocket-induced MHD ejector (RIME) concept of Cole, et al. (1995).


Descriptors :   *ROCKET ENGINES , *ROCKET PROPULSION , COMBUSTION , COMBUSTION CHAMBERS , DETONATIONS , EFFICIENCY , HIGH PRESSURE , MAGNETOHYDRODYNAMICS , PROPAGATION , THESES , THRUST , UNSTEADY FLOW


Subject Categories : Rocket Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE