Comparison of the trajectory optimization methods for multi-stage solid boost launcher

다단 고체연료 우주발사체의 비행궤적 최적화기법 비교

Two methods are applied to the problem of trajectory optimization for launch vehicles which burn solid propellant. One is 'Optimal Control' theory, the other is 'NonLinear Programming' method. Trajectory optimization for solid rocket motors has a special problem. The special problem is that the payload of launch vehicle is not the function of control variable. This paper deals with this special problem.