Derivation of Optimal Design Parameters for Grain Configuration of Solid Rocket Motor

초록

The grain design has been a vital part of the solid rocket motor (SRM). In the design of a SRM, the thrust profile is one of main design considerations and it has been given in various forms according to the mission. The main task of the grain design is to choose the suitable grain configuration depending on the variety of conditions, including the thrust profiles and the constraints. Based on the design objective set, the SRM has many options available for selection of the grain configuration. In previous study, Several grain design methodologies have been developed to fulfill the required parameters of volumetric loading fraction, web fraction and length to diameter ratios etc. However, these grain configurations are results of the optimal design with limited constraint conditions. It means that grain configurations should be redesigned when mission profiles are changed. The SRM is quite dependent on the various limitations. So, constraint conditions are frequently changed according to the mission profiles. Therefore, the SRM design process must be included in the system design process of the SRM for the reduction of time and effort. In this study, design parameters of the grain configuration have been investigated through the internal ballistics analysis according to the various grain configurations. The grain design module has been developed for system design of the SRM using the numerical code. Grain configurations such as star, wagon wheel and slotted tube have been modularized using the form function for the convenience of the code expansion.