Prediction of Internal Ballistic Parameters of Solid Propellant Rocket Motors

A modular computer program for prediction of internal ballistic performances of solid propellant rocket motors SPPMEF has been developed. The program consists of following modules: TCPSP (Calculation of thermo-chemical properties of solid propellants), NOZZLE (Dimensioning of nozzle and estimation of losses in rocket motor), GEOM (This module consists of two parts: a part for dimensioning the propellant grain and a part for regression of burning surface) and ROCKET (This module provides prediction of an average delivered performance, as well as mass flow, pressure, thrust, and impulse as functions of burning time). Program is verified with experimental results obtained from standard ballistic rocket test motors and experimental rocket motors. Analysis of results has shown that established model enables has high accuracy in prediction of solid propellant rocket motors features in cases where influence of combustion gases flow on burning rate is not significant.