고체 추진제 형상 최적 설계를 위한 하이브리드 최적화 기법 보완 연구

This performance of solid rocket motor is associated with the propellant grain configuration. The grain configuration should be designed to satisfy the objective condition. Therefore, the grain configuration has been modified according to change in the objective condition. Since the grain configuration is required, the application of the optimization technique is required to redesign of save design time and cost. In this study, the grain configuration optimal design program has been developed using grain burn-back analysis, internal analysis and optimization. And the hybrid optimization technique of grain configuration has been analyzed and modified. As a results, more fast and stable optimization performance has been provided.