특이섭동법을 이용한 미사일 비행궤적 최적화

Abstract

This study examines the singular perturbation technique(SPT) for the trajectory optimization problem. and applies it to the range maximization problem of a typical missile. Firstly. the zeroth order solutions for the three boundary layers are derived by the SPT and a midcourse feedback guidance law is obtained. Secondly. the comparison of the SPT solution with the exact solution obtained by the first-order gradient method confirms the validity of the SPT solution. Lastly. the SPT solution is compared with proportional navigation guidance(PNG) in midcourse guidance performance. The results of this study show that the SPT solution accounts for the aerodynamic characteristics of the vehicle so that it does not exceed the aerodynamic limit of the vehicle. This is not true for the PNG law. The efficiency of the SPT for the range maximization problem is also demonstrated in this study.