A study of 3-D analysis of solid propellant combustion configuration

초록

The performance and configuration of the solid rocket is associated with the solid propellant. The propellant configuration is changed when the propellant combustion proceeds. The change in the propellant configuration determines combustion performance variables such as burning surface and port volume. So the change in the propellant configuration should be analyzed for calculating the solid rocket performance. The solid rocket motor has been given the various propellant configurations according to its mission. The initial propellant configuration determines the change in combustion process. The effect of the change in the propellant configuration has the complicated impact on performance such as combustion chamber pressure, thrust and burning time. It is difficult to use the geometry equation or the empirical method for the performance prediction of the change in the propellant configuration. In this study, the analysis technique of the 3-Dimensional combustion configuration has been developed using the level set method. The developed method has been connected the internal ballistics analysis technique and used for developing the performance analysis program for the solid rocket motor. The complicated propellant configurations have been analyzed for the change in the propellant configuration and performance. Through this study, the developed method has been proven to be efficient for the various configurations of solid rocket motors.