Experimental techniques for characterization of particles in plumes of sub-scale solid rocket motors

An innovative collection methodology based on a recently developed supersonic probe enabled the of alumina particulate from exhaust plume sub-scale solid propellant rocket motor and comparison with quench bomb analysis incipient agglomeration. Laser diffraction, scanning electron microscopy, X-ray spectroscopic methods were used to determine particle size, morphology, crystalline nature, elemental composition. A significant reduction size occurred across nozzle. The distribution resulting expansion was monomodal centered around 2 μ m 3 m. Propellants containing lower aluminum mass fraction led number-based in sub-micrometric region while, for higher metal loading, distributions sensibly shifted towards larger same operative conditions. Similarly, identified be weakly dependent chamber pressure, an increase former as latter decreased. Hermsen correlation supported verified experimental analysis. majority particles composed by γ -alumina phase, had typical than m, characterized smooth surfaces. Occurrences spitting collision-to-coalescence phenomena analyzed. • Alumina are collected proximity nozzle exit motor. PSD morphology determined laser diffraction SEM Crystal phase composition studied through methods. influence relevant parameters is studied.