The article discusses the optimization of the process transition missile from its own trajectory to the kinematic trajectory during the flight anti-aircraft guided missiles. In addition, the requirements for the control contour of the guided anti-aircraft missile, the stability missile during its flight, the transfer function in the missile when taking into account feedback, and the structural guidance scheme of the guided anti-aircraft missile are considered. The purpose of the research work is to implement the control of the flight of anti-aircraft guided missiles, the optimization control contour. The tasks set to achieve the goal are the following: The relationship equation between the missile displacement rudder and normal acceleration; the equation for changing the missile rudder and pitch control according to control signals; the equation of the command transmitter of the computing-solving device, which creates a relationship between the control and changed parameters; the equation for matching the parameters that link the target and missile motion; the kinematic equation of the missile motion. To solve the problems, theoretical analysis, mathematical modeling, and mathematical statistical research methods are used. As a result of the research work: it was determined that the “freezing of coefficients” method is the most suitable method to use to determine the effect various parameters on the accuracy characteristics control systems.
