Development of an intrusive technique for particles collection in rockets plume

Abstract

An intrusive technique for particles capturing in supersonic-high temperature flows to be used in solid rocket motors plume characterization is proposed. A supersonic probe for the collection of the condensed combustion products in the proximity of the rocket nozzle has been designed to handle a progressive deceleration and cooling down of the exhaust gas, aiming at preserving liquid particles from break-up. A quasy-1D gas dynamics software (POLIRocket-V2) based on the Shapiro method and normal shock wave theory, supported by a CFD investigation using the DLR TAU code, was employed for the feasibility and the design study. Preliminary cold flow tests have been performed in the VMK supersonic vertical wind tunnel at DLR in relevant flow conditions. A proofs of concept of the probe working principle and the collection methodology were studied.