Parameter optimization of multistage missile for terminal velocity maximization

Abstract

This paper deals with an optimal control and parameter optimization problem of three-stage missile system. The objective function of this problem is to find a control input history for maximum terminal velocity. This missile is designed to intercept an aerial target at long distance and low altitude. The missile should be delivered to a target position with maximum terminal velocity for high killing ability. The missile has two boosting stages and warhead part, and is modelled as simplified 3-DOF in the pitch plane. The missile is accelerated by a thrust force and controlled by pitch angle which is aligned to thrust direction. Pitch angle history is optimal control input in this problem. Additional optimized parameter is coast time between first and second stage as well as pitch history for maximum terminal velocity. Two optimization methods are used: one is Pseudo Spectral method for optimal control problem and the other is Co-evolutionary Augmented Lagrangian Method for parameter optimization.