DTIC ADA164217: Holographic Investigation of Solid Propellant pdf

DTIC ADA164217: Holographic Investigation of Solid Propellant

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An investigation was conducted to determine the feasibility of obtaining holographic recordings of particulate behavior during the combustion process of solid propellant in a three-dimensional, windowed rocket motor. Transmittance measurements through the combustion chamber were made in order to select the appropriate neutral density filters which would yield the proper scene beam to reference beam intensity ratio. Holographic recordings were successfully made at combustion chamber pressures up to 185 psia using an HTPB-AP propellant containing 2.0 percent aluminum and 0.25 percent Fe203. The laser had to be fired manually because of the unreliability of the current igniter/grain design. For high combustion pressures, it is recommended that the laser beam power density be increased to penetrate the more opaque combustion products. Also, it is strongly recommended that a remote controlled laser firing device be used to improve the timing sequence for the hologram

• Creator/s: Defense Technical Information Center
• Date: 12/1/1985
• Year: 1985
• Book Topics/Themes: DTIC Archive, Yoon, Sang Chu, NAVAL POSTGRADUATE SCHOOL MONTEREY CA, *COMBUSTION, *HOLOGRAPHY, *SOLID PROPELLANT ROCKET ENGINES, *SOLID ROCKET PROPELLANTS, DENSITY, MEASUREMENT, RATIOS, NEUTRAL, INTENSITY, THESES, HIGH PRESSURE, LASERS, LASER BEAMS, SEQUENCES, TIME, TRANSMITTANCE, THREE DIMENSIONAL, ALUMINUM, PRESSURE, COMBUSTION CHAMBERS, PARTICULATES, RECORDING SYSTEMS, POWER, FILTERS, POLYBUTADIENE, ROCKET ENGINES, OPACITY, SOLID PROPELLANTS, COMBUSTION PRODUCTS, ALUMINIZED PROPELLANTS

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