| Citation: | ZHANG Liang, WANG Bin, LI Yang, et al. Temperature field analysis of cryogenic propellant tanks with deep subcooling cycle[J]. Journal of Aerospace Power, 2024, 39（8）：20220588 doi: 10.13224/j.cnki.jasp.20220588
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A rocket liquid oxygen tank was taken as an example to simulate the temperature-drop characteristics of the liquid oxygen tank with subcooled cycle. Using liquid nitrogen as the simulated working medium, the principle scaling cryogenic propellant subcooled cycle experimental system was established, and the accuracy of the numerical mode was verified by the experimental data. The effects of the subcooled cycle flow rate and return form on the temperature-drop rate and thermal stratification characteristics of the tank were simulated and analyzed. Results showed that, due to the long cylinder section of the first stage liquid oxygen tank, the fluid in the tank was more fully mixed and the temperature uniformity of the liquid was better. For the secondary tank, due to its short axial length, part of the subcooled liquid oxygen was directly sucked out through the upper suction port of the tank, such that the tank temperature cannot be reduced to 70 K. The temperature in the tank was obviously stratified, and the temperature uniformity was poor. After the optimization of the tank structure, the cooling rate and temperature uniformity of the tank were significantly improved.
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