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COMPARATIVE STUDY OF THE MATHEMATICAL MODEL OF THE PROPELLANT TANK PRESSURIZATION SYSTEM ; ПОРІВНЯЛЬНЕ ДОСЛІДЖЕННЯ МАТЕМАТИЧНОЇ МОДЕЛІ СИСТЕМИ НАДДУВУ ПАЛИВНОГО БАКА
Abstract. The pressurization system of launch vehicle (LV) fuel tanks serves to maintain a specified excess pressure in the tank's gas cushion, based on calculated requirements for fuel component supply and tank design. This necessitates the coordination of all elements within the pressurization system. This paper examines a pressurization system consisting of single high-pressure cylinder, the fuel tank and the connecting line with the metering element. To maintain the required excess pressure in the gas cushion, pressurization gas is supplied with the mass flow rate dependent on the parameters within the high-pressure cylinder. This excess pressure ensures a consistent flow rate of fuel components to the pumps or combustion chamber. System elements such as the gas reducer and gas pipes are treated as a single line with an equivalent flow rate coefficient. The objective of this work was to develop a mathematical model of the system described above. The suggested model includes a system of ordinary differential equations for both the high-pressure tank and the fuel tank, which is derived from the conservation laws of mass and energy, as well as the equation of state for the pressurization gas. The model takes into account the gas reducer by allowing for changes in the area of the gas outflow section over time. The model's operation was simulated, revealing that with a constant cross-sectional area of the gas line, the deviation in the mass flow rate of the fuel component during tank emptying is up to 4% of the nominal value. Implementing a linear law of area change reduced this deviation to 1%. Overall, the results confirm the accuracy of the proposed method for calculating tank parameters, making it suitable for designing rocket pressurization systems. ; Анотація. Система наддуву паливних баків ракет-носіїв (РН) розробляється для підтримки надлишкового тиску в газовій подушці баків відповідно до розрахункової залежності, яка визначається вимогами подачі компонентів палива та конструкцією баків. Отже, необхідно ...
COMPARATIVE STUDY OF THE MATHEMATICAL MODEL OF THE PROPELLANT TANK PRESSURIZATION SYSTEM ; ПОРІВНЯЛЬНЕ ДОСЛІДЖЕННЯ МАТЕМАТИЧНОЇ МОДЕЛІ СИСТЕМИ НАДДУВУ ПАЛИВНОГО БАКА
Abstract. The pressurization system of launch vehicle (LV) fuel tanks serves to maintain a specified excess pressure in the tank's gas cushion, based on calculated requirements for fuel component supply and tank design. This necessitates the coordination of all elements within the pressurization system. This paper examines a pressurization system consisting of single high-pressure cylinder, the fuel tank and the connecting line with the metering element. To maintain the required excess pressure in the gas cushion, pressurization gas is supplied with the mass flow rate dependent on the parameters within the high-pressure cylinder. This excess pressure ensures a consistent flow rate of fuel components to the pumps or combustion chamber. System elements such as the gas reducer and gas pipes are treated as a single line with an equivalent flow rate coefficient. The objective of this work was to develop a mathematical model of the system described above. The suggested model includes a system of ordinary differential equations for both the high-pressure tank and the fuel tank, which is derived from the conservation laws of mass and energy, as well as the equation of state for the pressurization gas. The model takes into account the gas reducer by allowing for changes in the area of the gas outflow section over time. The model's operation was simulated, revealing that with a constant cross-sectional area of the gas line, the deviation in the mass flow rate of the fuel component during tank emptying is up to 4% of the nominal value. Implementing a linear law of area change reduced this deviation to 1%. Overall, the results confirm the accuracy of the proposed method for calculating tank parameters, making it suitable for designing rocket pressurization systems. ; Анотація. Система наддуву паливних баків ракет-носіїв (РН) розробляється для підтримки надлишкового тиску в газовій подушці баків відповідно до розрахункової залежності, яка визначається вимогами подачі компонентів палива та конструкцією баків. Отже, необхідно ...
COMPARATIVE STUDY OF THE MATHEMATICAL MODEL OF THE PROPELLANT TANK PRESSURIZATION SYSTEM ; ПОРІВНЯЛЬНЕ ДОСЛІДЖЕННЯ МАТЕМАТИЧНОЇ МОДЕЛІ СИСТЕМИ НАДДУВУ ПАЛИВНОГО БАКА
Alieksieienko, V. (author) / Bucharskyi, V. (author)
2024-06-13
doi:10.15421/452434
Journal of Rocket-Space Technology; Vol. 33 No. 4-28 (2024): Journal of Rocket-Space Technology; 125-132 ; Journal of Rocket-Space Technology; Том 33 № 4-28 (2024): Вісник Дніпровського університету. Серія: Ракетно-космічна техніка; 125-132 ; 2409-4056 ; 10.15421/4524330102
Article (Journal)
Electronic Resource
English
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