Abstract
Factors, which contribute to the dissipation of acoustic energy in the chamber of solid rocket motors during combustion, include nozzle performance, particulate matter, propellant structural response, rotational flow, vortex shedding, etc. The most significant effect appears to be the response of the propellant combustion zone to acoustic pressure and acoustic velocity oscillations. In this paper, a significant improvement over the current practice of combustion stability calculations is achieved. A three-dimensional formulation of stability integral for the coupled acoustic-vortex fluctuations leads to new integral terms accounting for the various phenomena previously neglected.