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Information × Registration Number 0222U000611, 0121U107999 , R & D reports Title Determination of the thrust spreading of the multi-engine propulsion system during start-up for the first stage of the "Cyclone-4M" launch vehicle popup.stage_title Head Pylypenko Oleh V., Registration Date 14-01-2022 Organization Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine popup.description2 MULTIENGINE LIQUID ROCKET PROPULSION SYSTEM, POGO SUPPRESSOR, START-UP, EXTERNAL AND INTERNAL FACTORS, CAVITATION IN PUMPS, MATHEMATICAL MODELING, THRUST SPREADING. The object of research is the process of start-up liquid-propellant rocket propulsion system of the first stage of a launch vehicle "Cyclone-4M", containing four liquid-propellant rocket engines, taking into account the action of external and internal factors. The purpose of the scientific and technical work is the calculated determination of the thrust spread during the start-up of the multi-engine propulsion, due to the influence of internal and external factors, on transient processes in the systems of individual engines and their dynamic interaction. A nonlinear mathematical model has been developed for the launch of a multi-engine propulsion system of the launch vehicle, which takes into account the effect of external and internal factors. An effective method for determining the scatter of engine thrust caused by the action of internal and external factors, based on the use of LP -sequences, has been developed. Based on the results of the calculations, transient processes in the propulsion system were determined for various combinations of scatter of external and internal factors. It is shown that the spread in the values of the 90% thrust gain and thrust gain for the RD-874 as a whole is significantly (approximately 2 times) less than for each individual RD-870 engine as part of this propulsion system The values of these characteristics for individual RD-870 engines are, respectively, in the ranges from 0.1028 s to +0.0841 s and from 7.1% to +7.0% of the nominal engine thrust, and for the RD-874 multiengine propulsion system as a whole - respectively in the ranges from 0.0490 s to +0.0408 s and from 3.4 to +3.4% of the nominal engine thrust. Product Description popup.authors Bashliy Inna Dmitrivna Dolgopolov Sergiy Ivanovych Kvasha Yuri Oleksandrovych Nikolayev Olexiy D Khoryak Natalia V. popup.nrat_date 2022-03-09 Close