Abstract: The purpose of this paper is to solve the Dynamic Launch Zone (DLZ) problem for air-to-air homing missiles, by finding a numerical solution through integration of the nonlinear equations of the motion of the missile and target. To build the mathematical model of the real process we used experimental data of missile aerodynamic and thrust, mechanical measurements. The complex mathematical model includes a dynamic equation system with six degrees of freedom (DOF) and a guidance law, experimentally validated. By integrating the complex mathematical model we obtained the flight parameters for some significant cases and the DLZ for several tactical situations of aerial combat. The conclusions point to the altitude influence on DLZ configuration and the relevance of the input data on model precision.