Synthesis optimal guidance law for missile in cruise phases with terminal additional requires

The article analyzes and proposes the synthesis of an optimal guidance method for missiles during the cruise phase in a combined remoteautonomous control system The objective of the problem to be solved is to guide the missile to a nonfixed point in space according to a predefined rule meeting specific requirements and criteria In combined remote control systems at the moment of switching to guidance the missile must satisfy several stringent requirements such as ensuring the target is within the seekers field of view determining the distance to the target meeting the initial slip value h at the moment of autonomous guidance and considering the missiles maneuverability among others The article focuses on researching a synthesized optimal guidance law for the missile during the remote control phase while taking into account these requirements at the transition point to autonomous control at the end of the remote control phase