Numerical Studies of Hybrid Rocket Propellant

Future space missions are expected to be significantly impacted by developments in hybrid rocket propellant technology. Propellants that are more effective, sustainable, and good for the environment are needed to travel to more places in space and are cost-effective. In the current scenario, it is necessary to use high-performance propellant with the least amount of fuel so that space missions can reach their orbit and accomplished their mission. Sounding rockets, experimental airplanes, and space launch vehicles are just a few of the current uses for hybrid rocket engines. Due to a better combination of fuel/oxidizer and their benefits, such as a high specific impulse, improved safety, and simpler handling compared to conventional liquid or solid fuel rockets, hybrid rockets have the potential to be used in military weapons. The effectiveness of blend metal additions in enhancing the performance of hybrid rocket propellants has been the subject of much investigation. Metal additives can improve mechanical and combustion properties. This paper evaluates fuels such as paraffin and paraffin with additives aluminum and boron and oxidizer as liquid oxygen and discusses their combustion characteristics.