A combined optical and collection probe for solid propellant exhaust particle analysis.

Abstract

A combined optical and collection probe for solid propellant rocket motor exhaust particle analysis was designed and utilized in initial experiments with a sub-scale rocket motor. Shock swallowing capabilities of the probe were verified under restricted motor operations using a schlieren system. Window purge and ejector design were shown to be capable of keeping the probe windows clean when the probe was placed approximately 14 nozzle diameters downstream of the exhaust nozzle. The exhaust plume deflection device allowed sampling to occur during the minimum time required to reach steady flow within the probe. A MALVERN Mastersizer was used for in situ measurements of the particles, and a collection filter at the aft end of the probe was partially successful in capturing the probe flow. Suggestions are made for probe improvements and future investigations.