An investigation has been conducted to develop techniques for obtaining quantitative data that can be used to relate solid rocket propellant composition and operating environment to the behavior of solid particulates within the grain port and exhaust nozzle. The techniques employed are high speed motion pictures of propellant strand burners and slab burners in a cross-flow environment, SEM analysis of post-fire residue (strand, slab, and motor), determination of D32 across the exhaust nozzle using measurements of scattered laser light, and holograms of burning propellant strands, slabs, and motors. In addition, techniques are being developed for automatic retrieval of particular size distributions from holograms taken of the combustion of solid propellants. Results are presented on (1) the measurement of particular size changes across an exhaust nozzle, (2) holograms obtained at the nozzle entrance, and (3) automatic data retrieval from holograms.


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    Solid-Propellant Rocket Motors

    Greatrix, David R. | Springer Verlag | 2012


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