An Investigation of Experimental Techniques for Obtaining Particulate Behavior in Metallized Solid Propellant Combustion
Abstract
The goal of this initial investigation was to develop and compare experimental techniques that could be used for obtaining quantitative data on the effects of propellant properties, operating pressure and nozzle geometry on the behavior of metallized particulates within the grain port and nozzle of solid propellant rocket motors. The techniques employed were high speed motion pictures of strand burners and slab burners in a cross-flow environment, SEM analysis of post-fire residue (strand, slab, and motor), determination of D32 at the exit of an exhaust nozzle using measurements of scattered laser power spectra, and holograms of burning propellant strands and slabs in a cross-flow environment. All techniques were successfully developed and employed to obtain particulate size data from a series of specially formulated propellants. The motion picture and holographic techniques were successfully demonstrated for operating pressures of 34 and 68 atm. and with up to 15% aluminum. Fourteen micrometer resolution was obtained in the high speed motion pictures with a 1. 12X magnification (and very small depth of field) and eleven micrometer resolution was obtained in the holograms. Measurements of D32 at the nozzle exit plane of a small end-burning motor were in close agreement with size analysis of collected exhaust particulates.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1982
- Accession Number
- ADA119422
Entities
People
- E. Dubrov
- P. J. Hickey
- S. G. Karagounis
- T. R. Gillespie Ii
- V. D. Diloreto
Organizations
- Naval Postgraduate School