Thrust termination of solid rocket motor

Abstract Rocket motors are engines that create the necessary thrust for rocket motion. There different types of based on propellant state, such as solid motors, liquid and hybrid motors. One biggest disadvantages in comparison to is they extremely difficult extinguish, necessitating use specific devices. This paper reviews various ways termination fluid injection, rapid increase throat area, sudden opening an additional port at forward section motor, which increases depressurization rate (dp/dt) required extinguishing. The varies depending components, combustion pressure, exhaust may be investigated using experimental approaches. change critical area a motor can predicted by MATLAB code ensure complete extinguishing decreasing pressure under deflagrationlimit with high rate.