Research on the modeling of the missile's disturbance motion and the initial control point optimization

The initial trajectory design of the missile is an important part of the overall design, but often a tedious calculation and analysis process due to the large dimension nonlinear differential equations and the traditional statistical analysis methods. To improve the traditional design methods, a robust optimization concept and method are introduced in this paper to deal with the determination of the initial control point. First, the Gaussian Radial Basis Network is adopted to establish the approximate model of the missile's disturbance motion based on the disturbance motion and disturbance factors analysis. Then, a direct analytical relationship between the disturbance input and statistical results is deduced on the basis of Gaussian Radial Basis Network model. Subsequently, a robust optimization model is established aiming at the initial control point design problem and the niche Pareto genetic algorithm for multi-objective optimization is adopted to solve this optimization model. An integral design example is give at last and the simulation results have verified the validity of this method.