Abstract
A new procedure is created for the calculation of heat and mass transfer processes in a cryogenic rocket tank. This simplified method is based on the assumption about homogeneity of temperature in liquid and vapor phase of a fuel component. This assumption made this model useful for such regime as refueling, self-pressurization, pressurization during engine working and other. As the example of method applicability, some calculation is made for refueling of KVTK upper stage to estimate component losses. For the self-pressurization regime, the results of the calculation is compared with experimental data for one cylindrical and one spherical hydrogen tanks. This comparison is shown that pressure rise rate in a full tank several times upper than in the calculations. But for the low level of liquid hydrogen the accuracy of this method is significantly increased. As the result, this procedure is recommended as a lover score of pressure rise during self-pressurization. Key words: cryogenic propellant tank, cryogenic fuel storage, cryogenic tank processes, mathematical modelling, calculation method, refueling, mass-average temperature.
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