Design and Analysis of Optimized Solid Propellant Grain

In rocket motors, propellants are utilized to undergo combustion and generate thrust. In the case of solid rocket motors, this is accomplished with solid propellant grain, which is the mixture of solid fuel and/or oxidizer cast and cured inside the combustion chamber to a semi-solid state. For the purpose of achieving various types of combustion, numerous designs have been created. There are four distinct types of combustion: progressive, neutral, regressive, and multi-stage thrust. Although these geometries have been designed since the earliest days of rocket manufacturing, they perform as intended despite not being optimized. This research investigates and analyzes the creation of new and optimized designs with differential calculus method and finite element analysis in order to increase surface area and propellant volume within the combustion chamber. Two models are theorized, designed, and analyzed in software for their various parameters, including internal surface area, volume, and pressure versus time curves.