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Information × Registration Number 0220U104790, 0119U102577 , R & D reports Title Development of structural chart and research of auxiliary control system of launch vehicle stage with the use of detonation engine popup.stage_title Head Ternova Kateryna V., Кандидат технічних наук Registration Date 27-12-2020 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 an auxiliary control system for the space stage of the rocket in normal and freelance conditions on the active part of the rocket flight. The purpose of the work is to develop a constructive scheme of the auxiliary control system of the space stage of the launch vehicle on the active part of the trajectory using a detonation engine for injecting gas into the supercritical part of the nozzle. Research methods include numerical and experimental studies of thermogas-dynamic processes with control of gas flows in rocket engines. The actual scientific and practical problem has been solved - to increase the energy and mass characteristics of existing engines for the space stage of the launch vehicle and to improve the control system of the space stage of the launch vehicle in the case of parrying of disturbing moments in emergency situations. A model for a priori estimation computer modeling has been developed to optimize the location of detonation products in the supersonic part of the nozzle, which allowed to determine that the injection of detonation products into the supersonic part of the nozzle and it allows to achieve significant lateral forces with the main chamber. Computer simulations of the injection of detonation products into the supersonic part of the nozzle revealed two force factors that occur when the detonation products are injected perpendicular to the axis of the chamber. It has been found that the injection of detonation products can reduce or increase the thrust of the chamber, depending on the depth of penetration of the shock wave and the interaction with the main flow of the nozzle. The optimal location for further research has been selected. A flat model with a profile used for a priori computer modeling has been produced for experimental research. The developed method to calculate parameters and the created bench equipment is planned to be used in the following researches of gas-dynamic processes in detonation engines. Product Description popup.authors Yevseienko Maksym V. Vasyliv Stepan S. popup.nrat_date 2020-12-27 Close