Study of Burning Rate Characteristics of Composite Propellant Based on Nitrated Hydroxyl Terminated Polybutadiene (NHTPB) Binder

One of the parameters that can be utilized to determine the performance and internal ballistic properties of rocket propellants is the burning rate value. Based on previous research, it’s known that the binder based on NHTPB (Nitrated Hydroxyl Terminated Polybutadiene) has the potential to increase the energetic properties of composite propellants. This study aims to analyze the characteristics of the internal ballistic properties of the burning rate of rocket composite propellants produced by using a binder based on NHTPB as an effort to support the development of rocket propellants technology in Indonesia. Literature studies was conducted by reviewing previous research journals. Based on several research, it shows that the NHTPB Binder can increase the burning rate of composite propellants by about 10-30%. The burning rate value of composite propellants produced is 10-13 mm/s. This burning rate value exceeds the standard propellant burning rate and propellant currently available in ORPA-BRIN (Rocket Technology Research Center) is >0.7 mm/s. The addition of an energetic plasticizer component also plays a role in influencing the increase in the burning rate. The NHTPB energetic binder can be an alternative in developing solid composite propellant manufacturing technology in the future as an effort to rocket propellants technology in Indonesia.