Accession Number : ADA140168

Title :   Holographic Investigation of Solid Propellant Combustion Particles.

Descriptive Note : Master's thesis,

Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s) : Mellin,P J

PDF Url : ADA140168

Report Date : Dec 1983

Pagination or Media Count : 43

Abstract : This investigation continued the development of a method for obtaining high quality holograms of the combustion products from aluminized solid rocket motor propellants burned in a two-dimensional motor to provide a cross-flow environment. The use of glass side plates as a motor casing provided both a convenient construction technique and allowed good quality holograms to be obtained. At combustion pressures above 500 psia and propellant slab thicknesses greater than 0.080 inches, the timing of the laser pulse during the burn was found to be critical, since an extremely short time interval existed between the establishment of steady state slab burning and the generation of too much smoke/combustion products to permit laser penetration. As desired operating pressures increase and aluminum powder particle sizes decrease, it will probably be necessary to use thinner propellant slabs. (Author)

Descriptors :   *Solid propellants, *Combustion, *Particulates, *Holography, Glass, Metals, Holograms, Combustion products, Two dimensional, Solid propellant rocket engines, Cross flow, Composite propellants, Smokeless propellants, Powders, Aluminum, Particle size, Firing tests(Ordnance), Burning rate, Steady state, Naval research, Theses

Subject Categories : Physical Chemistry
      Optics
      Combustion and Ignition
      Solid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE