Modelling of the formulated solid rocket propellant characteristics

This study is a mathematical model to obtain the characteristics performance of magnesium metal (powder) and carbon on potassium nitrate-sucrose (KNSU) solid propellant formulation. Characterization is, as general rule, important determine its before it can be suitable for use rocket flight or any mission. Method ballistic load cell evaluation was used validate results using combustion exhaust products solved parameters propellant. The constituent which acts an opacifier coolant kept constant at 2% in order arrest some heat during process helped lower temperature, because high temperature could lead chamber rupture failure. effect addition optimized 3% formulation contributed significantly improving overall utilization KNSU provided higher values better compared when not included. confirmed with equations. equation parameters. gave specific impulse (122.9s), (1821K), ratio (1.1592), molecular weight (36.89g/mole), density (1912.5kg/m3) velocity (1000m/s) result while maintaining same pressure.