Low-temperature propellant storage tank with pressure control device

Abstract

The invention discloses a low-temperature propellant storage tank with a pressure control device. The low-temperature propellant storage tank comprises a low-temperature propellant storage tank body,a low-temperature circulation pump, a throttling valve, an expansion machine, a double-pipe heat exchanger, an exhaust cooling coil and an exhaust valve. In order to improve the heat exchange efficiency of the heat exchanger, the reverse-flow double-pipe heat exchanger is adopted, and more cooling capacity can be generated. Meanwhile, fluid passing through the throttling valve absorbs heat and becomes saturated gas or superheated gas which is expanded and cooled through the expansion machine after being discharged out of the tank body, the low-temperature gas forms a cold shield through the cooling coil wound in an insulation layer outside the tank body, external leakage is reduced to the greatest extent, and the exhaust cooling capacity is fully used. The low-temperature propellant storage tank is simple in structure and high in heat exchange efficiency, the cooling capacity is fully used, the tank body pressure is effectively controlled, and effective guarantee is provided for long-term storage of a low-temperature propellant and the tank body pressure.

Description

technical field [0001] The invention relates to the field of low-temperature propellant storage and fluid management, in particular to a low-temperature propellant storage tank body pressure control device. Background technique [0002] Cryogenic propellants have received more and more attention and applications in the field of aerospace due to their excellent performance. In particular, cryogenic liquid hydrogen and liquid oxygen have been considered by NASA as the preferred propellant combination for future deep space exploration. However, due to the low storage temperature of cryogenic propellants, heat can easily heat up and cause thermal stratification of the fluid. Thermal stratification will promote the evaporation phase change of cryogenic fluid, which will cause the pressure of the tank to rise, which is extremely dangerous for the low-temperature propellant storage tanks running on space orbits and deep space probes. Once the tank pressure exceeds Therefore, it i...

AI Technical Summary

Problems solved by technology

The core heat exchange component in the thermodynamic exhaust system researched by NASA in the United States is a downstream concentric sleeve heat exchanger, and its heat exchange efficiency is relatively low; although the relevant patent CN105444591A applied for in China has improved the heat Three-tube heat exchanger, at the same time, the interlayer between the inner tube and the middle tube is provided with a helically wound disturbance wire, but the flow direction of the two heat exchange fluids is not changed, and it is still limited by the heat exchange efficiency of the downstream heat exchanger.

In addition, the above two sets of system devices do not consider the cold energy utilization of exhaust gas

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