Study of the flow structure during the injection of detonation products into the supersonic nozzle
DOI:
https://doi.org/10.34185/1562-9945-2-145-2023-02Keywords:
injection, detonation engine, closing part, vector control thrust, nozzleAbstract
The gradual unloading of the space stage by undocking objects from it or an emer-gency situation due to the undocking of one of the spacecraft leads to mass asymmetry. In outer space there is also the problem of the collision of a space object with elements of space debris. Therefore, the relevance of the topic of this work is determined by the need to develop a system for avoiding the collision of a rocket with elements of space de-bris and controlling the flight, observing the programmed trajectory of movement. The gas-dynamic aircraft system is characterized by the highest speed control. Injection of detonation products into the supercritical part of the nozzle was used as a gas-dynamic system. Modeling was carried out in the SolidWorks application software package. The purpose of the work is to develop alternative methods of the thrust vector control of the upper stage rocket engine. The scheme of the system for the thrust vector control of a rocket engine by the effect of a detonation wave on the gas flow in its nozzle has been developed. The simulation was carried out in a non-stationary flat model at angles to the axis of the combustion chamber of 90°, 60°, 45°, 30° and parallel to the axis, - 0°. The location of the detonation gas generator was near the nozzle section. Numerical simulation revealed that the impact of the detonation wave on the main gas flow in the nozzle causes two power factors. The first force factor is due to the reactive force when detonation products are thrown into the nozzle and on the wall of the high pressure zone where the detonation gas generator is located. The second force factor is due to the change in pressure distribution on the nozzle surface, where high pressure zone creates reflecting on it. The dependence of the relative lateral force on the injection angle of detonation products into the combustion chamber over time has been obtained. The structure of the flow according to the patterns of the velocity distribution in the nozzle during the injection of detonation products is also considered. In cases when the injec-tion is blown at 900 and 450, the release of detonation products initiates a shock wave of high intensity, which moves against the supersonic flow, retarding it. The developed scheme can be used for maneuvering the upper stage of a prospective launch vehicle to avoid its collision with elements of space debris.
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