ВДОСКОНАЛЕННЯ СИСТЕМИ КЕРУВАННЯ ВЕКТОРОМ ТЯГИ МАРШОВОГО РАКЕТНОГО ДВИГУНА НА БАЗІ ДОСЛІДЖЕННЯ ДИНАМІКИ КОСМІЧНОГО СТУПЕНЯ РАКЕТИ НА АКТИВНІЙ ДІЛЯНЦІ ПОЛЬОТУ

Abstract

The variant of the combined thrust vector control system of the propulsion rocket engine for the space rocket stage, which consists of the large-scale interceptor gas-dynamic thrust vector control system and the control jet nozzle system, is substantiated. Functional scheme of the control channel and a structural scheme of a gas-dynamic control system with an interceptor injection node have been developed. The complex transfer function, the transition function and the amplitude-phase characteristics of the gas-dynamic control system are defined. The relations between the values of dynamic parameters and the quality of the transition process are presented