Abstract
The paper deals with the development of a motion correction system for an unguided rocket of a certain class. The existing method for calculating the rocket flight range based on the dependence of flight path on the initial rocket pitch angle and average parameters of disturbing effects does not provide the required accuracy of the specified flight range. This is mainly due to uncontrolled range wind deviations in the flight area. At the same time, conducting test rocket launches to identify dispersion characteristics and improve the target accuracy leads to significant material costs. Therefore, computer simulation is the most promising approach for studying rocket dispersion laws and developing a motion correction system for the unguided rocket on this basis. When developing the correction system, classical differential equations were used describing the aerodynamics of a variable-mass rocket, as well as adaptive control methods with a reference model. As a result of the study, a method for recording a program that implements the reference model on the Arduino Due platform was developed. A general Simulink model that simulates the process of rocket flight path correction was built. A half-scale rocket flight model with a correction block was developed. Based on this model, a series of experiments were carried out, which showed a high degree of rocket target accuracy due to rocket path correction. The results make it possible to take the developed system as a basis for developing a practical path correction system for Grad rockets