An Analytical Model of the Effective Technology for Thermal Preparation of Rocket Propellant in Tanks of Filling Systems of Ground-Based Complexes

Thermal preparation of rocket propellant prior to filling the tanks of launch vehicles, upper stages and spacecraft, is among the most energy-intensive and lengthy processes taking place at launch pads and technical areas of launch sites. The thermal preparation stage requires the use of efficient technologies and modes of cooling (heating) rocket fuel. To forecast the design and performance characteristics of the thermal preparation systems, analytical models are preferred. They allow the determination of parameters of the fuel cooling (heating) processes under specific conditions and requirements defined by the equipment of ground-based systems. This paper presents an analytical model of the effective technology of rocket propellant thermal preparation in the tanks of ground-based filling systems where the propellant is cooled (heated) in a heat exchanger, with the heat exchange process taking place in the tank with antifreeze. The cooling process of the propellant is based on bubbling of the antifreeze by liquid nitrogen; and the heating mode is provided by electric heating elements placed in the tank with the antifreeze. The calculated dependencies and the results of modelling the propellant temperature in filling tanks are presented, as well as relative consumption of liquid nitrogen in the cooling process as compared with other technologies.

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