Study of Combustion and Flow Behaviour in Solid-Propellant Rocket Motors

摘要

A comprehensive study of several important aspects of the internal ballistics of solid-propellant rocket motors (SRMs) was undertaken. Numerical models were developed for the solution of the quasi-steady and unsteady, one-dimensional, hydrodynamic equations of motion governing the two-phase core flow behavior within the motor chamber and nozzle. A phenomenological model of erosive burning was develped and incorporated into an overall solid-propellant combustion model, which in turn is solved in conjunction with the equations of motion for the SRM. The quasi-steady internal ballistics predictions based on the phenomenological model was also developed for the description of normal acceleration effects on the combustion process, for the parametric study of spinning, composite-propellant SRM. The internal ballistics of an SRM within various longitudinal acceleration environments was studied numerically with the use of a comprehensive unsteady flow model. A numerical model for the description of ignition transient flow behavior of pellet-dispersion igniter systems was developed. The model was specifically created for the study of conventional bag and cartridge igniters employed for small-diameter, composite-propellant SRMs, but the model in its general form may be adapted for the study of a multitude of ignition transient problems. Good agreement is obtained between experimental firing data and the model prediction for the head-end pressure-time profile.