A screen-type liquid acquisition device for cryogenic propellant on-orbit management

Abstract

A mesh-type liquid acquisition device for low-temperature propellant on-orbit management, including a hollow channel surrounded by metal walls on three sides and a metal mesh curtain on one side, and both ends of the channel are blocked by blind ends, forming In a closed cavity, a channel outlet is provided at the center of the metal wall facing the metal mesh screen; or the cavity is divided into several sub-cavities that are not connected to each other through one or more partition plates, and each sub-cavity A channel outlet is provided at the center of the metal wall facing the metal mesh screen; or a coarse mesh screen is provided in the section near the blind end and the partition plate of each sub-cavity, and a fine mesh screen is provided in the section near the exit; or The channel is only provided with a blind end at one end, and an outlet at the other end. A coarse-mesh screen is provided upstream, and a fine-mesh screen is provided downstream. The transition between the coarse-mesh screen and the fine-mesh screen is through welding or bonding; Equivalent length-to-depth ratio and the method of optimizing the setting of the metal mesh screen improve the liquid acquisition rate without changing the weight of the device.

Description

technical field [0001] The invention relates to the technical field of low-temperature propellant space storage and management, in particular to a screen-type liquid acquisition device for low-temperature propellant on-orbit management. Background technique [0002] The gas-liquid separation technology of rocket propellant under microgravity is a key technology in aerospace engineering. The propellant is in a gas-liquid two-phase mixed state in the tank. During on-rail storage, due to the lack of gravity constraints, the dominant surface tension guides the liquid to distribute along the inner wall of the tank, which makes the tank drain very easy to access To the gas, causing air entrainment and drainage. Therefore, it is necessary to obtain pure liquid propellant by means of gas-liquid separation, so as to ensure the efficient transmission of propellant and the safe operation of the rocket engine in the microgravity environment. [0003] At present, among many pure liquid...

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Problems solved by technology

[0004] But when this device is used for cryogenic propellant (comprising liquid hydrogen, liquid oxygen, liquid methane), there is following shortcoming: the low surface tension coefficient of cryogenic propellant has reduced the barrier effect of liquid film on the screen to bubble, makes the net The two sides of the screen cannot withstand a high pressure difference. At this time, because a high driving pressure cannot be applied to the device, the amount of liquid that can be obtained by the screen screen per unit area is low; in order to obtain a larger total liquid extraction rate, it is necessary to The volume of the device has to be increased to expand the total area of ​​the screen, which greatly increases the weight of the device and reduces the effective volume of the storage tank

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