유도비행체의 부스터 분리 동특성 해석

In this paper a static and dynamic analysis technique for the design of a missile booster separation device is presented. The missile of particular interest recently underwent a flight test, and the related test results are shown to compare with the predicted results using the current technique. The presented static analysis is fairly simple but proves to be very useful for initial design requirements setup. The 3-DoF dynamic simulation provides a good tool for prediction of separation mechanism, as long as a proper models of thrust and drag components are available.