The use of models with improved characteristics in the missile control system

Abstract

A fundamental diagram of a control system for missiles of various classes is investigated. A functional diagram of a control system with an intelligent component for long-range aerodynamic rockets returning to the atmosphere is developed. It is proposed to use in the control loop an ensemble of a priori missile models and models of external influences. It is proposed to improve the accuracy of control systems with an intelligent component by increasing the degree of controllability of the state variables for a priori models. The most convenient numerical criterion of controllability degree for of the state variables of the models is presented. The results of mathematical modeling showed a slight increase in the efficiency of missile control with an increase in the degree of controllability of the pitch angle by changing the coefficients of the control matrix. Keywords rocket; control system; intelligent component; an action acceptor; a priori model; controllability; degree of controllability; management efficiency