Low-temperature propellant rapid pre-cooling transmission pipeline structure

Abstract

The invention relates to a low-temperature propellant rapid pre-cooling transmission pipeline structure. The low-temperature propellant rapid pre-cooling transmission pipeline structure includes a ground storage tank, a low-temperature liquid outlet of the ground storage tank is connected with an inlet of a low-temperature transmission pipeline, an outlet of the low-temperature transmission pipeline is connected with a propellant filling opening of an on-rocket storage tank, and the low-temperature transmission pipeline includes an inner micro-ribbed vacuum tube and a vacuum straight tube; thevacuum straight tube forms an annular cavity through an inner straight tube and an outer tube, the annular cavity is vacuumized, and the outer side of the inner straight tube is wrapped with a plurality of heat insulation layers; and the inner micro-ribbed vacuum tube forms an annular cavity through a micro-ribbed inner tube and an outer tube, the annular cavity is vacuumized, the outer side of the micro-ribbed inner tube is wrapped with a plurality of heat insulation layers, and micro-ribbed protrusions of the micro-ribbed inner tube are formed by machining. The low-temperature propellant rapid pre-cooling transmission pipeline structure adopts the layout form combining the inner micro-ribbed vacuum tube and the vacuum straight tube, the advantage of conversion from strengthened membranestate boiling to transition boiling of the inner micro-ribbed vacuum tube are used for achieving rapid pre-cooling, the advantage of the small resistance of the vacuum straight tube is used, the flowresistance of the overall low temperature transmission pipeline is reduced, and the pre-cooling process is accelerated.

Description

technical field [0001] The invention relates to the technical field of aerospace low-temperature propellant ground filling, in particular to a low-temperature propellant rapid precooling transmission pipeline structure. Background technique [0002] Cryogenic propellant has become the preferred propellant for spaceflight, but the low boiling point and easy evaporation of low temperature propellant will cause it to experience complex two-phase flow problems in ground filling. For example: before large-scale transfer of cryogenic liquid, the transfer pipe must be cooled to the cryogenic liquid temperature zone. The process of the pipeline system from room temperature to low temperature is called "precooling", and the duration of precooling will affect the propellant transfer process. [0003] Future space missions require rapid launch of the launch vehicle, so the precooling process must be accelerated. At present, it takes about 1 hour to pre-cool the low-temperature pipeli...

AI Technical Summary

Problems solved by technology

This special phenomenon can be explained as follows: in the film boiling region, the substructure of the bellows causes an obvious radial velocity component in the gas film layer, which can disturb the gas film layer and promote earlier contact between the liquid and the wall; but the inner fin of the bellows The structure also causes the thickness of the gas film layer in the entire boiling zone to increase, which affects the overall heat transfer effect

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