Expanding the functionality of an adjustable liquid rocket engine

Abstract

To reliably ensure the mission of the rocket flight, it is important to increase the accuracy, efficiency and reliability of the system to ensure the necessary navigational characteristics of rocket movement. Ensuring high rocket characteristics and expanding their functional capabilities are the most important tasks for the further improvement of rocket and space technology. The task of the thrust vector control of a rocket engine through all channels of rocket stabilization is achieved by using separate control bodies: in modulus, direction and roll.
The purpose of the work is to justify a new solution of expanding the functionality of an adjustable liquid propellant rocket engine, namely, additional control of the thrust vector direction and the creation of torque about the engine axis.
Main researches. In order to expand the functionality of a rocket engine, it is proposed to create control forces on flowing surfaces in the nozzle. This is achieved by installing a central body on the hinge assembly and a solid obstacle in the critical nozzle section with the injection of liquid through it into the flow of chamber gas running on the obstacle. At the same time, separate processes and subsystems of thrust vector control are distinguished with their subsequent integration. The flow perturbations in the rocket engine nozzle with obstacles of various natures make it possible to control the thrust vector of the engine in all planes of rocket stabilization. For a rocket engine with a disk nozzle, this is achieved by installing a central body on the hinge assembly and a solid obstacle (interceptor) with liquid injection through it in the region of the nozzle critical section.
It was found that additional control of the direction of the thrust vector and the creation of torque around the engine axis simplify the thrust vector control system of a fast maneuverable rocket; increase its energy-mass characteristics and the reliability of the flight control system as a whole. Research on the development of controlled liquid rocket engines has shown the advantages of using annular nozzles with axial movement of the central body. Annular nozzles with internal expansion of the gas stream have great potential for providing regulation of the module and the thrust vector direction of the rocket engine. The proposed solution can be used in promising projects for creation fast-maneuverable liquid rockets.