STREAMLINING THE DESIGN OF NEUTRAL BURNING SOLID ROCKET MOTORS: A GUI-DRIVEN COMPUTATIONAL APPROACH

Abstract

This paper presents a computational tool for optimizing SRM internal ballistics, focusing on neutral burning star grain geometries. Users input mission-specific parameters such as thrust, burn time, and grain caliber, along with chamber pressure ranges, select propellants, and predefine geometric constraints on the star. The tool employs two 0D flow models for efficient simulations, enabling rapid iteration and optimization. Validation of the analytical burn-back model showed strong agreement with the Level Set Method (LSM), with an average deviation of 0.35% in web thickness and 0.959% in burning area predictions. A case study demonstrated its capability by evaluating 103,289 unique star grain designs, selecting optimal configurations with thrust variations under 0.02% and burn time deviations within 0.04%.The tool is integrated into a graphical user interface (GUI), streamlining design with minimal programming knowledge. This approach enhances accuracy, reduces trial-and-error, and ensures robust SRM designs for mission-specific applications.