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Information × Registration Number 0222U005145, 0121U111995 , R & D reports Title Development of a new method for the thrust vector control of a rocket engine with the detonation shock wave effect on the gas flow in the nozzle popup.stage_title Head Ternova Kateryna V., Кандидат технічних наук Registration Date 20-12-2022 Organization Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine popup.description2 The object of study is gas-dynamic controls of the thrust vector direction of the rocket stage on the active part of the flight. The purpose of work is to develop a new method to control the thrust vector of a rocket engine by the effect of a detonation shock wave on the gas flow in the nozzle. Research methods include calculation and experimental methods of analysis of control forces creation by the disturbance of the gas flow in the nozzle by a detonation wave. An urgent scientific and practical task has been solved - increasing the speed of the thrust vector control bodies of the upper stage engines and the need to maneuver space rockets to avoid collisions with elements of space debris. With the help of computer modeling of the detonation product injection into the supersonic part of the nozzle at different angles to its axis, it has been possible to reveal the dependence of the relative lateral force on time for each case. It has been discovered that when detonation products are blown in at angles less than 90⁰, it is possible to obtain a relative side force of short duration with the order of thrust of the main chamber. A system with discrete control pulses can be used to maneuver the upper stage of the rocket, to avoid its collision with elements of space debris. To conduct experimental studies, a flat model with a profile used for a priori computer modeling has been made. The developed method of calculating parameters and the created bench equipment are planned to be used in the next studies of gas-dynamic processes in detonation engines. The developed design scheme, the procedure for conducting theoretical and experimental studies is intended to be used to improve the existing control systems of the space stage of the rocket. Product Description popup.authors Vasyliv Stepan S. popup.nrat_date 2022-12-20 Close