This study experimentally investigates the burn rate characteristics of solid rocket propellants with varying compositions, utilizing sucrose as the fuel and potassium nitrate as the oxidizer. Solid propellants are significant in aerospace applications due to their reliability, simplicity, and efficiency in various propulsion systems, making them ideal for launch vehicles and missile technology. Data on burn rate from strand burning tests and performance evaluations from static fire testing are obtained after the propellants have been carefully dried and cast. The main goal is to comprehend how compositional changes affect the propellant’s overall performance and combustion characteristics. Following the initial testing, aluminum powder with a changed burn rate is added, and its effects on combustion are examined. The findings indicate that changes in the fuel-to-oxidizer ratio significantly impact the burn rate. Adding aluminum powder improves performance for a short while, but ultimately reduces combustion efficiency. In order to optimize solid propellant formulations for use in rocket propulsion, this effort intends to thoroughly investigate compositional alterations and burn rate modifiers. The results offer important new information for creating robust, efficient propulsion systems, which will eventually improve the performance and dependability of rocket technologies utilized in the aerospace industry.