SIMULATION STUDY OF A MISSILE COLD LAUNCH SYSTEM

摘要

In this paper the missile flight dynamics during the launch phase is studied. The main concept behind this work was to use a vertical cold launch system and the rapid pitch maneuver to achieve longer missile range and better firing coverage. A set of a small pulse rocket engines was used to obtain the desired missile attitude. The physical and mathematical models of the missile are described. The pulse jets control algorithm is presented. The computer program of the missile model has been developed in the Simulink environment. The missile behavior in the low-speed flight envelope has been examined. The results of numerical simulations in the form of the graphs are presented. It has been obtained that there exist several benefits of the cold launch method as increased range and higher target kill probability.