Accession Number : ADA260900


Title :   Particle Behavior in Solid Propellant Rocket Motors and Plumes


Descriptive Note : Master's thesis


Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA


Personal Author(s) : McCrorie, John D , II


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a260900.pdf


Report Date : Dec 1992


Pagination or Media Count : 57


Abstract : The particle size distribution inside the combustion chamber and the changes that occurred across the exhaust nozzle were measured in a subscale solid propellant rocket motor with a 2% aluminized end-burning propellant grain and a highly underexpanded nozzle. A combination of diagnostic techniques were used. Size distributions in the exhaust plume were determined by a Single Particle Counter, a Malvern 2600 ensemble particle sizer, and by Scanning Electron Microscope (SEM) examinations of particles collected on a timed exposure impact probe. Size distributions inside the combustion chamber were determined by Malvern 2600 measurements through windows at the nozzle entrance, SEM examinations of particles collected from the nozzle entrance wall, and exhaust plume measurements of a helium quenched motor. It was determined that agglomeration processes dominated in the flow from the center of the combustion chamber up to the nozzle entrance. Particle breakup processes dominated particle behavior from the nozzle entrance, through the nozzle, and into the exhaust. Solid-Propellant; Rocket Motor; Particle Sizing.


Descriptors :   *PARTICLE SIZE , *PARTICLES , *BEHAVIOR , *SOLID PROPELLANT ROCKET ENGINES , *EXHAUST PLUMES , MEASUREMENT , PROBES , SCANNING ELECTRON MICROSCOPES , IMPACT , SIZES(DIMENSIONS) , WINDOWS , NOZZLES , ROCKETS , CHAMBERS , ROCKET ENGINES , MOTORS , OPTICAL PROCESSING , MICROSCOPES , FLOW , HELIUM , WALLS , COUNTERS , ALUMINIZED PROPELLANTS , PARTICLE COUNTERS , PROPELLANT GRAINS , EXHAUST NOZZLES , COMBUSTION CHAMBERS , ALUMINUM OXIDES , DISTRIBUTION , THESES , QUENCHING , PROPELLANTS , ELECTRONS


Subject Categories : Inorganic Chemistry
      Combustion and Ignition
      Nuclear Propulsion
      Solid Propellant Rocket Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE