COLLECTING DATA ON ALUMINUM COMBUSTION AND ITS OXIDES IN SOLID ROCKET MOTORS

Abstract

A programmatic and unified framework of techniques, targeting the particles size evolution in solid rocket motors (SRMs) from the combustion chamber to the nozzle exit, is delivered. On one hand, quench bomb tests enable to obtain the statistical distribution of particles diameter at the release from the propellant burning surface. On the other, an innovative intrusive technique leads to the experimental definition of the final state of the particles, by collecting them downstream of the nozzle. Numerical investigation of the rocket plume collector enabled to gain information concerning the reliability of the technique and of the collection methodology. Hence, this set of facilities may enable an end-toend description of the SRM multiphase flow, providing a consistent database for the validation of solid rocket motors simulations.