Response of a burning solid propellant to pressure waves of finite amplitude

Abstract

Abstract : A measure of the effect of solid propellant combustion upon pressure perturbations arising in a rocket chamber is provided by the response function of the burning surface. Conventional methods of measuring this quantity are based upon a number of assumptions which are doubtful; further, they require a large number of tests for characterization of propellant response with frequency. A shock-tube method, free from some of these objections, was utilized to determine the response of a burning solid propellant surface to pressure perturbations of small but finite amplitude. The theory, experimental details, and treatment of the data are described briefly. Results are reported for several propellant formulations, including different aluminum loadings. These results are compared with empirical instability data and with theory. A critique of the shock-tube and other methods of measuring propellant response is presented in terms of effects found to be important during the course of the program. (Author)