Control of the thrust vector of the rocket engine by the injection of an inert gas into the expanding part of the nozzle

In this article, the authors presented the results of the research on the design layout scheme for controlling the thrust vector by injecting an inert gas into the expanding part of the nozzle of a rocket engine. The analysis was carried out by modeling the processes of gas dynamics on computational models of the engine differing in the angle of injection (45° and 90°) and having the injection unit located in the nozzle block at a distance from the critical section of 50 mm. This particular site was chosen for the study in view of the maximum possible effect on the incoming flow in the supersonic part of the nozzle block. According to the results of the research, it was found that the most rational position of the nozzle is 45° in relation to the incoming flow in the supersonic part of the nozzle block. Such injection angle gives the highest values of the control torque, which provides the most effective way to control the rocket with small weight and size characteristics of the injection mechanism. The data obtained during the research can be used in the design of rocket engines of high-altitude stages.