Ballistic Performance of Solid Rocket Motor with Various Propellant Grain Configurations

Abstract

The initial phase of the development of the solid propellant rocket motor is characterized by a series of parametric studies that are carried out to fulfill the rocket's mission. Throughout the process of evaluating feasible solutions for propellant shape, engine configuration and type of propellant, production issues, specific engine performance requirements, and operating conditions are considered. After several preliminary project studies, and practical assessments of possible solutions, an optimal construction is selected. It is then sent for detailed analysis. During this analysis, the motor has to satisfy the necessary parameters for a stable solid propellant rocket motor design for which the propellant type, geometry of the propellant grain, and motor structure are critically tested. The main objective of this project is to define and produce a propellant grain that will fulfill the required thrust - time profile, impulse and needed for a successful rocket mission considering the other limitations (envelope, mass, etc.). In this article, different grain configurations of solid rocket and their burning rates are studied. A direct modelling is involved in the design process of the grain geometry in CAD software using various features. The numerical results from the CAD are used to derive the performance of the propellant grain using MATLAB Programming. The procedure we have followed here can be applied to any complex geometry in a simpler way for preliminary designing of grain configuration.