The launch system experiences variable dynamic accelerations during liftoff and ballistic flight, which usually brings serious safety issues on the thermal behavior within cryogenic fuel storage tanks. 2022), are widely used as power fuel on aerospace engineering and deep space exploration (Inoue et al. The present study is significant to the safety flight of launch vehicle and may supply some technical supports for the design of cryogenic propellant system.Ĭryogenic propellants, including liquid hydrogen and liquid oxygen (Wang et al. ![]() Some valuable conclusions are obtained finally. On the basis of the numerical model, effect of the flight acceleration level on the tank pressurization and liquid outflow performance are numerically simulated and analyzed, with the gas injection rate of 0.18 kg/s and the liquid outflow rate of 36.0 kg/s. Validated against the liquid hydrogen discharge experiments, the numerical model is turned out to be proper and acceptable with the calculation errors limited within 20%. ![]() ![]() The VOF method is utilized to predict the pressurization discharge with 360 K high-temperature gaseous oxygen as the pressurant gas. In this study, a two-dimensional axisymmetric numerical model is adopted to research the outflow characteristic from a cylindrical liquid oxygen storage tank with the gas injection. Cryogenic pressurization discharge involves on complex heat exchange and fluid flow issues, and the related thermal physical performance should be comprehensively investigated.
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