Investigation on solid propellant test and time calibration for complete combustion

Abstract

A solid propellant is simple and reliable rocket fuel. Once ignited, the propellant cannot be stopped since they burn until they run out. Solid fuel rockets are widely used in military applications such as missiles, model rockets, boosters for satellite launchers and so on because they can be stored for long periods of time without degrading the propellant. The primary objective of this research is to study the burnout mass of solid propellants using various propellants and catalysts. Potassium Nitrate (KNO3) was chosen as an oxidant in the experiment because of its compatibility with other ingredients and low-cost affordability. KNO3 was used as an oxidizer in a 65% ratio with 34% of the fuel and 1% of the catalyst. KNO3, fuel ingredients like Fructose, Glucose and Lactose with catalysts Copper and Aluminum were taken in powdered form. Cylindrical stainless steel with one closed end was taken to fill the cavity, and a concentric hole was made for constant burning. This propellant-filled chamber is fixed strongly in a position so that it does not propel during fuel combustion when thrust is formed. The obtained result shows that the longest burnout mass was secured by burning Glucose with Copper powder and KNO3 for 136 s when compared to the shortest burnout mass was secured by burning Lactose with Aluminum powder and KNO3 mixture to 57 s. The highest temperature of the mixture was Lactose with Copper powder and KNO3 resulted in 518 °C when compared to the lowest temperature of the mixture was Glucose with Copper powder and KNO3 was 211.75 °C.