고체 로켓 모터 설계를 위한 추진제 형상 최적화 연구

초록

A study for solid rocket optimal design considering propellant configuration optimization has been conducted. A thrust-time profile is one of the main design considerations of solid rocket and it has been given in various forms according to the mission. So solid rocket is needed for satisfying the object thrust-time profile. In this study, components of solid rocket motor have been studied. And the propellant optimal design program has been developed using the Burn-back Analysis module, 0-D unsteady Internal Ballistics Solver and the Optimization Technique. The Burn-back Analysis module that calculates change of tube, slot and star grain configuration has been developed using the analytical method. The 0-D unsteady Internal Ballistics Solver has been developed for calculating thrust-time profile. After calculating the thrust-time profile, the accuracy between the calculation result and requirement is determined by object function. If the accuracy doesn’t satisfy the requirement, the program performs optimization module for the redesign process. Through this process, optimal design of the solid rocket has been performed.