A cryogenic propellant space on-orbit liquid acquisition device

Abstract

An on-orbit liquid acquisition device for low-temperature propellant space, including a pressurization chamber, a liquid collection chamber and a set of movable vane plates. The outer container structure of the pressurization chamber and liquid collection chamber is integrated and installed at the bottom of the cryogenic propellant tank The pressurization chamber and the liquid collection chamber are separated into two independent areas by the moving piston; the upper end of the pressurization chamber is provided with a pressurization port, which is connected to the pressurization system; the liquid collection chamber is filled with a liquid collection sponge, and the lower end of the liquid collection chamber is provided with a There is a liquid outlet of the low-temperature propellant storage tank, and a layer of porous metal mesh is installed between the liquid collection chamber and the liquid discharge port; the side wall of the liquid collection chamber is divided into two parts, the upper wall is a perforated wall, and the lower wall is a solid wall The movable blade plate is installed on the outer periphery of the perforated wall to ensure that the blade group can completely wrap the perforated wall when it is rotated to attach to the perforated wall; The propellant liquid acquisition system has become more stable and reliable, and the applicable range of working conditions is wider.

Description

technical field [0001] The invention relates to the technical field of low-temperature propellant space fluid management, in particular to an on-orbit liquid acquisition device for low-temperature propellant space. Background technique [0002] On-orbit ignition of spacecraft engines, on-orbit pressurization and transmission of propellants all require a continuous and stable supply of single-phase liquid propellants. Under ground conditions, the gas-liquid phase can be well stratified by gravity. Under orbital microgravity conditions, the distribution of gas-liquid phases is highly random, and gas-liquid positioning and separation must be realized through gas-liquid management technology. In recent years, low-temperature propellants such as liquid hydrogen and liquid oxygen have been widely used in large-scale launch vehicle systems due to their high specific impulse, high thrust, non-toxic and non-polluting advantages, and are the preferred propellants for future large-sca...

AI Technical Summary

Problems solved by technology

Active management technologies such as inertial type and spin type require continuous consumption of high-cost low-temperature propellants, which are not economical for large-scale systems

The flexible diaphragm storage tank used for normal temperature propellants is no longer suitable for low temperature propellants that are easy to evaporate because they cannot eliminate the gas evaporated on the liquid side

Passive gas-liquid management technologies mainly include trough type, trap type, sponge type, blade plate type, screen channel type, etc. Among them, the trough type gas-liquid management device can be refilled, but it is very sensitive to the direction of acceleration; the reaction of the trap type device The acceleration bearing capacity is strong, but the structure is complex and the flow rate is small; the sponge type and the vane type device are simple in structure, light in weight, and low in cost, but for low-temperature propellants with low surface tension, they can only be used under very low gravity levels. Stable and reliable; screen channel device is less sensitive to gravity level and thermal environment, but has complex structure, heavy weight and low reliability

[0004] At this stage, for large-scale cryogenic spacecraft systems, there is no mature on-orbit application scheme for realizing cryogenic propellant gas-liquid separation and full liquid acquisition in complex orbital environments.

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