Numerical Simulation on the effect of flow pattern in solid rocket motor

Abstract

Pressure Oscillations are known problem of large solid rocket motors (SRMs), which lead to thrust oscillations and to significant dynamic loads that often cause the need for dampers on the payload, reducing the payload mass capacity and launcher usability. The relationship of aerodynamics and acoustics in the SRM combustion chamber, which is at the heart of self - sustained pressure oscillations, is essentially a feedback loop. When the vortex shedding frequency is close to the natural frequency of the chamber, pressure oscillations grow and reach a maximum. The numerical simulation of such complicated processes is difficult because each step in the feedback loop must be correctly accounted for.