Synthesis of a Control System for Planning a Rocket Projectile on a Passive Flight Section along a Program-Defined Trajectory

Abstract

The article solves a problem aimed at creating a control system for the planning of a rocket projectile. The existing method of calculating the missile range does not provide the necessary accuracy. The use of computer simulation methods is the most promising approach for the development of a rocket planning control system based on laws. The proposed control system is based on the use of a reference trajectory of the rocket flight calculated for the predicted average values of the velocity of the longitudinal component of the wind. An algorithm for controlling the planning of a rocket by changing the angle of rotation of a horizontal support is proposed, based on the dependence of vertical and horizontal coordinates and on the pitch angle. The computer system of visual programming Simulink was used as a platform for the development of the algorithm. As a result, a block diagram of the rocket planning control was obtained, including a model of the rocket flight path as a control object and an on-board control system organized on the basis of a dual-core ESP-32 microcontroller. The technique of wireless recording of the control program into the memory of the microcontroller in the field is proposed. Based on the Simulink Desktop software package, a half-scale rocket flight model was developed in real time, including an ESP-32 microcontroller, a PCI-1710HG board and a Simulink rocket flight trajectory model with a variable mass in the vertical plane. A series of experiments were conducted that showed a high degree of accuracy of the missile hitting the target because of the projectile planning control system.