Synthesis of optimal motion control of a guided aircraft on a maneuvering space object

The deployment of U.S. weapons in space reduces the flight time of weapons to important strategic ground and space objects, which in turn significantly limits the ability to counter threats and retaliate with domestic strategic nuclear and non-nuclear forces. This factor increases the importance of the task of optimal control of the guided aircraft's movement towards a maneuvering space object to improve the accuracy of guidance. This article explores the synthesis of optimal control of the guided aircraft's movement towards a maneuvering space object. The purpose of the synthesis is to ensure the acceptable conditions for capturing a space object by a television homing head by fulfilling the conditions of quasi-collinearity of the velocity vectors of the aircraft and the space object at the end of long-range homing. The experimental results of the study confirm the achievement of the goal. To determine the transition area of the guided aircraft to homing.