Theoretical study of propellant behavior during thrust chamber depressurization

Abstract

A mathematical model that permits computation of burning rates of solid-propellant rocket motors during pressure transients is presented. The conservation equations in the solid and the gas phases are coupled with the chamber over-all mass balance equation. The method is used to compute the burning rate behavior during rapid depressurizations. The results of the computations are used to obtain dP/dt—extinguishment limits of solid propellants in terms of appropriate parameters. The agreement with the experimental quenching limit data is good.