Mitikov Y. Methodological foundations for the development and modernization of pressurization systems for fuel tanks of rocket propulsion systems

Object - processes in fuel tanks at the start and in flight, high-pressure cylinders, heat exchangers, liquid and solid fuel gas generators. The purpose of the work is to create methodological bases (complex and sequence) of scientific researches in order to solve the current scientific and technical problem of modernization of existing pressurization systems (PS) of cylindrical tanks of modern rocket propulsion systems on LOX and RP-1 components and development of perspective PS tanks of new generation propulsion plants. PS is one of the most knowledge-intensive parts of launch vehicle (LV). Modern gel pneumatic systems are the most expensive parts of LV after liquid propellant rocket engine. In the USSR, there was not a single LV that was designed from the very beginning as launch vehicle. New, highly grounded, new high-efficiency PS tanks of propulsion units of the new generation have been found theoretically grounded. The problems of determination of the level of boiling oxygen during self-inflating, safe chemical inflating, PS with oxygen vapors without impurities, high-temperature helium and renewable generator gas were solved. Effective ways to modernize the fuel tanks of the existing propulsion plants are proposed, and recommendations for their implementation are developed. Methodical bases for efficient design of fuel tank fuel tank design of common multi-unit LVs and multi-unit LREs have been developed to ensure their operability in the event of failure of one LRE, taking into account the pulse time after the action of the emergency LRE traction. The idea of the leading role of gas pipelines when using a high-temperature pressurization working fluid has been expanded. A method of determining the compression ratio of a tank design for a non-isothermal jet is proposed. New effective ways of introducing a non-isothermal pressurization working fluid into the free tank volumes have been found, theoretically reflected, and investigated. The introduction of high-temperature gas in the form of turbulent vortex rings was studied. For the first time, the rate of oxygen evaporation in a cylindrical tank with wafer reinforcement in the flight of LV was determined. In flight conditions, a complex of experimental data was obtained that fully characterizes the parameters of the new supercooled helium PS (fuel temperature, gas in the tank, upper bottoms).The materials of the dissertation were used at the enterprises: Yuzhnoye State Design Office - methods of mathematical and physical modeling of helium supercharging systems, identified and clarified the basic design parameters of the supercharging tank with liquid oxygen of the first degree after the first launch vehicle "Zenith", introduced into production three patents, and in the educational process of the Oles Honchar Dnipro National University. The areas of use are aviation and space technology.