CN118833420B - Aircraft liquid cooling device and working method thereof - Google Patents
Aircraft liquid cooling device and working method thereof Download PDFInfo
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- CN118833420B CN118833420B CN202411311637.2A CN202411311637A CN118833420B CN 118833420 B CN118833420 B CN 118833420B CN 202411311637 A CN202411311637 A CN 202411311637A CN 118833420 B CN118833420 B CN 118833420B
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- 239000007788 liquid Substances 0.000 title claims abstract description 242
- 238000001816 cooling Methods 0.000 title claims abstract description 26
- 238000000034 method Methods 0.000 title claims abstract description 21
- 230000005540 biological transmission Effects 0.000 claims abstract description 64
- 238000001914 filtration Methods 0.000 claims abstract description 18
- 239000012535 impurity Substances 0.000 claims abstract description 11
- 238000007789 sealing Methods 0.000 claims description 41
- 230000001105 regulatory effect Effects 0.000 claims description 13
- 238000010992 reflux Methods 0.000 claims description 5
- 230000007306 turnover Effects 0.000 claims description 5
- 239000002245 particle Substances 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 6
- 230000017525 heat dissipation Effects 0.000 description 3
- 101100298222 Caenorhabditis elegans pot-1 gene Proteins 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000004146 energy storage Methods 0.000 description 2
- 230000014509 gene expression Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000005514 two-phase flow Effects 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 238000009833 condensation Methods 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000005338 heat storage Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
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- Life Sciences & Earth Sciences (AREA)
- Biodiversity & Conservation Biology (AREA)
- Environmental & Geological Engineering (AREA)
- Environmental Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Toxicology (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to the technical field of heat exchange, and particularly relates to an aircraft liquid cooling device and a working method thereof. The liquid cooling device for the aircraft comprises a storage tank and a conveying part arranged at the lower end of the storage tank, wherein the conveying part is suitable for conveying liquid in the storage tank to the aircraft, an exchange adjusting component is arranged on a transmission shaft of the conveying part in a sliding mode, the liquid in the storage tank is conveyed to the aircraft, the liquid is gasified in the aircraft to perform heat exchange on the aircraft, and the exchange adjusting component is suitable for filtering the liquid when the condensed liquid flows back upwards through the transmission shaft. Through the setting of exchange regulation subassembly, not only can filter the impurity in the interception backward flow liquid, can also avoid the increase of liquid storage tank internal pressure.
Description
Technical Field
The invention belongs to the technical field of heat exchange, in particular to the technical field of heat storage by using liquid, and particularly relates to an aircraft liquid cooling device and a working method thereof.
Background
The two-phase flow technique is a heat dissipation technique using characteristics of liquid and gas two-phase flows. In the operation process, the liquid obtains heat at a heat source, the form evaporates into gas, and the gas is cooled and condensed back to the liquid state in an energy accumulator (commonly called a cooler) to form a closed loop. Through the circulation process of liquid evaporation and gas condensation, heat on a heat source can be efficiently taken away, and the purpose of heat dissipation is achieved. The technology is mostly used in the field of spaceflight airborne to realize heat dissipation.
The liquid storage tank is fixed on the aircraft, and in the process of conveying liquid to the aircraft by the water pump in the liquid storage tank, the pressure in the liquid storage tank is suddenly increased due to the opening of the water outlet and the high rotating speed of the water pump, and the increased pressure is not discharged in time, so that the sealing at the joint of the liquid storage tank and the aircraft can be greatly pressurized, and the liquid leakage condition is caused. And the liquid in the liquid storage tank is directly discharged outwards, and the waste of materials is caused.
Therefore, how to avoid the leakage of the liquid at the joint caused by the excessive pressure in the liquid storage tank is a technical problem to be solved in the art.
It should be noted that the above information disclosed in this background section is only for understanding the background of the inventive concept and therefore the above description is not to be construed as constituting prior art information.
Disclosure of Invention
The embodiment of the disclosure at least provides an aircraft liquid cooling device and a working method thereof.
In a first aspect, embodiments of the present disclosure provide an aircraft liquid cooling apparatus, comprising:
The device comprises a storage tank, a conveying part arranged at the lower end of the storage tank, an exchange adjusting component and an exchange adjusting component, wherein the conveying part is suitable for conveying liquid in the storage tank to an aircraft, the exchange adjusting component is arranged on a transmission shaft of the conveying part in a sliding mode, the liquid in the storage tank is conveyed to the aircraft, the liquid is gasified in the aircraft to perform heat exchange on the aircraft, and the exchange adjusting component is suitable for filtering the liquid when the condensed liquid flows back upwards through the transmission shaft.
In an alternative embodiment, a liquid suction pipe is vertically fixed in the liquid storage tank, and the liquid suction pipe is communicated with the conveying part;
the liquid level of the liquid in the liquid storage tank is not less than 2/3 of the volume of the liquid storage tank;
the transmission shaft is hollow, and one end of the transmission shaft, which is close to the liquid storage tank, is provided with a row of pressure holes.
In an alternative embodiment, the exchange adjusting assembly comprises two adjusting pipes which are oppositely arranged, and a telescopic piece which is fixed between the two adjusting pipes;
the transmission shaft is provided with an accommodating hole along the radial direction, and the adjusting pipe is arranged in the accommodating hole in a sliding manner.
In an alternative embodiment, the outer wall of the adjusting tube is circumferentially provided with a plurality of filtering holes, and the filtering holes are suitable for filtering large-particle impurities in the liquid;
and a sealing plate is fixed at the outer end of the adjusting pipe and is suitable for sealing the adjusting pipe.
In an alternative embodiment, two spiral grooves are axially formed in the inner wall of the accommodating hole, one spiral groove corresponds to one adjusting pipe, and the spiral directions of the spiral grooves are opposite.
In an alternative embodiment, a projection is fixed to the outer wall of the adjusting tube, which projection is adapted to the spiral groove and is adapted to slide in the spiral groove.
In an alternative embodiment, the exchange adjustment assembly further includes a sealing plate rotatably disposed within the receiving bore and adapted to seal the relief bore.
In an alternative embodiment, a limiting block is fixed at the lower end of the sealing piece, and the telescopic piece is suitable for being abutted with the limiting block;
when the two regulating pipes move in opposite directions in a spiral mode, the telescopic piece is suitable for pushing the limiting block to turn over, so that the sealing piece opens the pressure discharge hole.
In an alternative embodiment, the side wall of the conveying part is provided with a liquid outlet pipe, the liquid outlet pipe is communicated with the aircraft, and the impeller rotates circumferentially to convey the liquid in the liquid storage tank to the aircraft through the liquid outlet pipe.
In an alternative implementation, an embodiment of the present disclosure provides an aircraft liquid cooling apparatus, including:
A reservoir for storing a liquid;
one end of the conveying part is communicated with the liquid storage tank, and the other end of the conveying part is communicated with the aircraft;
the exchange adjusting assembly is arranged on the transmission shaft of the conveying part in a sliding manner and is suitable for sliding in a spiral manner relative to the transmission shaft;
the transmission shaft drives the impeller to rotate circumferentially so as to convey the liquid in the liquid storage tank to the aircraft, so that the aircraft is subjected to heat exchange;
When the pressure in the conveying part is increased, the liquid pushes the exchange adjusting assembly to spirally slide towards the axis direction of the transmission shaft, so that the liquid in the liquid storage tank is decompressed into the transmission shaft of the conveying part.
In a second aspect, an embodiment of the present disclosure further provides a working method of an aircraft liquid cooling device, including:
the transmission shaft drives the impeller to rotate circumferentially so as to convey the liquid in the liquid storage tank to the aircraft, and the liquid is gasified and absorbed in the aircraft so as to dissipate heat of the aircraft;
The gasified gas is cooled and condensed back into liquid in an energy accumulator in the aircraft, and the liquid is conveyed back into a liquid storage tank by a reflux pump;
the liquid flowing back passes through the exchange regulating assembly, and is suitable for filtering and intercepting impurities in the liquid flowing back;
When the pressure in the conveying part is increased, the liquid pushes the exchange adjusting assembly to spirally slide towards the axis direction of the transmission shaft, so that the liquid in the liquid storage tank is decompressed inwards after the transmission shaft of the conveying part.
The liquid cooling device for the aircraft and the working method thereof have the advantages that through the arrangement of the exchange adjusting component, impurities in the backflow liquid can be filtered and intercepted when the backflow liquid in the aircraft flows to the liquid storage tank, and when the pressure of the liquid in the liquid storage tank is increased when the liquid is conveyed into the aircraft, the pressure in the liquid storage pipe can be released into the transmission shaft, so that the situation that the liquid leakage occurs at the joint of the liquid storage tank and the aircraft due to the increase of the pressure in the liquid storage tank is avoided. Meanwhile, the liquid suction pipe arranged in the liquid storage tank can ensure that the conveying part can pump liquid in the liquid storage tank under any gesture of the aircraft.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
In order to make the above objects, features and advantages of the present invention more comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a perspective view of an aircraft liquid cooling apparatus provided in an embodiment of the present disclosure;
FIG. 2 is an interior cross-sectional view of an aircraft liquid cooling device provided in an embodiment of the present disclosure;
FIG. 3 is a perspective view of a drive shaft and exchange adjustment assembly provided by an embodiment of the present disclosure;
FIG. 4 is a cutaway perspective view of a delivery portion and exchange adjustment assembly provided by an embodiment of the present disclosure;
FIG. 5 is a perspective view of a telescoping member and a seal plate within a drive shaft provided in an embodiment of the present disclosure;
fig. 6 is a schematic view illustrating an outward movement state of an adjusting tube according to an embodiment of the present disclosure.
In the figure:
1. 10, a liquid storage tank and a liquid suction pipe;
2. the device comprises a conveying part, a transmission shaft, a pressure discharge hole, a liquid outlet pipe, an impeller and a transmission shaft, wherein the transmission shaft is arranged at the bottom of the conveying part;
3. The device comprises an exchange adjusting component, 31, an adjusting pipe, 32, a telescopic piece, 33, a filtering hole, 34, a sealing plate, 35, a sealing piece, 36 and a limiting block.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In this context, when it is mentioned that a first component is located on a second component, this may mean that the first component may be formed directly on the second component, or that a third component may be interposed between the first component and the second component. In addition, in the drawings, the thickness of the parts may be exaggerated or reduced for effective description of technical contents.
In this document, when an element or layer is referred to as being "on," "engaged to," "connected to," "attached to," or "coupled to" another element or layer, it can be directly on, engaged, connected, attached, or coupled to the other element or layer, or intervening elements or layers may be present. In contrast, when an element is referred to as being "directly on," "directly engaged to," "directly connected to," "directly attached to" or "directly coupled to" another element or layer, there may be no intervening elements or layers present. Other words used to describe the relationship between elements should be interpreted in a similar fashion (e.g., "between" pairs "directly between," "adjacent" pairs "directly adjacent," etc.). As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
Example embodiments of the present disclosure will be described in more detail herein with reference to the accompanying drawings. As used herein, expressions such as "at least one of a..once more, modify an entire list of elements when following a list of elements, rather than modifying individual elements in the list. For example, the expression "at least one of a, b and c" should be understood to include a only a, b only, c only, both a and b, both a and c, both b and c, or all of a, b and c.
The terminology used herein is for the purpose of describing particular example configurations only and is not intended to be limiting. As used herein, the singular articles "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. The terms "comprises," "comprising," and "having" are inclusive and therefore specify the presence of stated features, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and/or groups thereof. The method steps, processes, and operations described herein should not be construed as necessarily requiring their performance in the particular order discussed or illustrated, unless specifically identified as an order of performance. Additional or alternative steps may be employed.
As used herein, the phrases "in one embodiment," "according to one embodiment," "in some embodiments," and the like generally refer to the fact that a particular feature, structure, or characteristic following the phrase may be included in at least one embodiment of the present disclosure. Thus, a particular feature, structure, or characteristic may be included within more than one embodiment of the disclosure, such that the phrases are not necessarily referring to the same embodiment. As used herein, the terms "exemplary," "exemplary," and the like are used for purposes of illustration, example, or description. Any embodiment, aspect, or design described herein as "example" or "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments, aspects, or designs. Rather, use of the terms "example," "exemplary," and the like are intended to present concepts in a concrete fashion.
Because the liquid storage tank is fixed on the aircraft, the opening of the water outlet and the high rotating speed of the water pump can lead to the sudden increase of the pressure in the liquid storage tank in the process of conveying the liquid to the aircraft by the water pump in the liquid storage tank, and the untimely discharge of the increased pressure can lead to great pressure on the seal of the joint of the liquid storage tank and the aircraft, thereby leading to the leakage condition of the liquid. And the liquid in the liquid storage tank is directly discharged outwards, and the waste of materials is caused.
Therefore, how to avoid the leakage of the liquid at the joint caused by the excessive pressure in the liquid storage tank is a technical problem to be solved in the art.
The defects of the scheme are all results obtained by the inventor after practice and careful study, and therefore, the discovery process of the above problems, and the solutions proposed herein by the present disclosure for the above problems, should be all the contribution of the inventors to the present disclosure in the process of the present disclosure.
It should be noted that like reference numerals and letters refer to like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.
Some embodiments of the invention are described in detail below with reference to the accompanying drawings. The following embodiments and features of the embodiments may be combined with each other without conflict.
As shown in fig. 1-6, in some embodiments, an aircraft liquid cooling apparatus is provided, comprising:
The device comprises a liquid storage tank 1 for storing liquid, a conveying part 2 fixed at the lower end of the liquid storage tank 1, wherein the inner cavity of the liquid storage tank 1 is approximately spherical and is high-pressure resistant, one end of the conveying part 2 is communicated with the liquid storage tank 1, the other end of the conveying part is communicated with an aircraft, and the conveying part 2 is integrated at the lower end of the liquid storage tank 1, so that not only can space be saved, but also the whole weight of the device can be reduced. The exchange adjusting assembly 3 is slidably arranged on the transmission shaft 20 of the conveying part 2 and is suitable for sliding in a spiral manner relative to the transmission shaft 20, a motor is arranged at the lower end of the conveying part 2, the transmission shaft 20 penetrates through the motor, the transmission shaft 20 is communicated with the aircraft, the motor is suitable for driving the transmission shaft 20 to drive the impeller 24 to rotate, and the impeller 24 rotates circumferentially to convey liquid in the liquid storage tank 1 into the aircraft. The transmission shaft 20 drives the impeller 24 to circumferentially rotate so as to convey the liquid in the liquid storage tank 1 to the aircraft, the liquid in the liquid storage tank 1 is heated and gasified after entering the aircraft so as to radiate the heat of the aircraft, the gasified liquid flows in a pipeline in the aircraft until the gas flows through the energy storage, the energy storage is suitable for condensing the gas into the liquid, and the reflux pump in the aircraft is suitable for conveying the condensed liquid to the liquid storage tank 1 through the transmission shaft 20. The flying height of the aircraft, the rotating speed of the impeller 24 and the opening of the liquid outlet pipe 22 can influence the flow speed of the liquid in the liquid storage tank 1 to the aircraft, and after the flow speed is smaller than the conveying speed of the impeller 24 to the liquid, the pressure in the liquid storage tank 1 and the conveying part 2 can be increased. When the pressure in the conveying part 2 increases, the liquid pushes the exchange adjusting assembly 3 to spirally slide towards the axis direction of the transmission shaft 20, so that the liquid in the liquid storage tank 1 is decompressed into the transmission shaft 20 of the conveying part 2. Through the arrangement of the exchange adjusting component 3, impurities in the backflow liquid can be filtered and intercepted when the backflow liquid in the aircraft flows to the liquid storage tank 1, and when the pressure of the liquid in the liquid storage tank 1 is increased when the liquid is conveyed into the aircraft, the pressure in the liquid storage pipe can be released into the transmission shaft 20, so that the condition that the liquid leakage occurs at the joint of the liquid storage tank 1 and the aircraft due to the increase of the pressure in the liquid storage tank 1 is avoided. At the same time, the liquid suction pipe 10 arranged in the liquid storage tank 1 can ensure that the conveying part 2 can pump the liquid in the liquid storage tank 1 under any posture of the aircraft.
Referring to fig. 2, a pipette 10 is vertically fixed in the liquid storage tank 1, and the pipette 10 is communicated with the conveying part 2. The liquid level of the liquid in the liquid storage tank 1 is not less than 2/3 of the volume of the liquid storage tank 1.
The liquid outlet is offered to traditional liquid storage pot 1, and it is close to the bottom of conveying part 2 at liquid storage pot 1, realizes the rotatory in-process of different flight attitudes at the aircraft, can appear conveying part 2 can not pump to the liquid, leads to the cooling effect to reduce. In the present embodiment, the arrangement of the pipette 10 can ensure that the liquid is pumped to the conveying part 2, regardless of the flight attitude of the aircraft, and the cooling effect is improved.
In order to realize that the condensed liquid flows back to the liquid storage tank 1, the transmission shaft 20 is arranged in a hollow mode, and one end, close to the liquid storage tank 1, of the transmission shaft 20 is provided with a row of pressure holes 21. The lower end of the transmission shaft 20 is communicated with an energy accumulator, the energy accumulator condenses the gas into liquid, and the reflux pump is suitable for conveying the condensed liquid to the liquid storage tank 1 through the transmission shaft 20. After the liquid passes through the exchange regulating assembly 3, the exchange regulating assembly 3 is suitable for filtering and intercepting impurities in the liquid. Such impurities include, but are not limited to, scale.
Referring to fig. 4, the exchange adjusting assembly 3 includes two adjusting tubes 31 disposed opposite to each other, and a telescopic member 32 fixed between the two adjusting tubes 31, wherein two ends of the telescopic member 32 are respectively fixed on side walls of the two adjusting tubes 31, and the telescopic member 32 is adapted to be compressed when the two adjusting tubes 31 move in opposite directions, and is adapted to be stretched when the two adjusting tubes 31 move in opposite directions. The transmission shaft 20 is provided with a containing hole along the radial direction, the containing hole is communicated with the liquid storage tank 1, and the adjusting pipe 31 is arranged in the containing hole in a sliding way. The liquid is adapted to pass through the regulator tube 31 when the returning liquid flows from bottom to top to the reservoir 1.
The outer wall of the adjusting tube 31 is circumferentially provided with a plurality of filtering holes 33, the filtering holes 33 are suitable for filtering large-particle impurities in liquid, a sealing plate 34 is fixed at the outer end of the adjusting tube 31, and the sealing plate 34 is suitable for sealing the adjusting tube 31. After the liquid flows into the regulating tube 31, the regulating tube 31 is adapted to be pushed to move outwards, and the regulating tube 31 is adapted to rotate spirally relative to the transmission shaft 20 in the outwards moving process until the regulating tube 31 protrudes out of the transmission shaft 20, and the liquid in the regulating tube 31 flows to the liquid storage tube through the filtering holes 33. The drive shaft 20 stops rotating during the flow of liquid from bottom to top.
Further, two spiral grooves are axially formed in the inner wall of the accommodating hole, one spiral groove corresponds to one adjusting tube 31, and the spiral directions of the spiral grooves are opposite. The outer wall of the adjusting tube 31 is fixed with a protruding block adapted to the spiral groove, and the protruding block is adapted to slide in the spiral groove. The engagement of the projections with the helical grooves causes the adjustment tube 31 to move helically outwardly relative to the drive shaft 20 during the movement of the liquid out of the adjustment tube 31.
Referring to fig. 5, in order to realize the pressure relief of the liquid storage tank 1, the exchange adjusting assembly 3 further comprises a sealing piece 35, wherein the sealing piece 35 is rotatably arranged in the accommodating hole, and the sealing piece 35 is suitable for sealing the pressure relief hole 21. A spring is arranged between the sealing plate 35 and the transmission shaft 20, and the spring is suitable for pulling the sealing plate 35 to seal the pressure discharge hole 21. When the pressure at the communication position of the liquid storage tank 1 and the conveying part 2 is too high, the outside of the transmission shaft 20 horizontally pushes the adjusting pipe 31 to move spirally towards the axis of the transmission shaft 20, the adjusting pipe 31 moves spirally until the telescopic piece 32 is abutted with the limiting block 36, the telescopic piece 32 is suitable for pushing the limiting block 36 so that the sealing piece 35 opens the pressure discharge hole 21, and the liquid in the liquid storage tank 1 is suitable for flowing into the transmission shaft 20;
A limiting block 36 is fixed at the lower end of the sealing piece 35, the telescopic piece 32 is suitable for abutting against the limiting block 36, wherein when the two adjusting pipes 31 move in a spiral shape in opposite directions, the telescopic piece 32 is suitable for pushing the limiting block 36 to turn over so that the sealing piece 35 opens the pressure discharge hole 21.
Optionally, a liquid outlet pipe 22 is disposed on the side wall of the conveying part 2, the liquid outlet pipe 22 is communicated with the aircraft, and the impeller 24 rotates circumferentially to convey the liquid in the liquid storage tank 1 to the aircraft through the liquid outlet pipe 22.
Some embodiments provide an aircraft liquid cooling device, comprising a liquid storage tank 1 for storing liquid, a conveying part 2 fixed at the lower end of the liquid storage tank 1, an exchange adjusting component 3 arranged on a transmission shaft 20 of the conveying part 2 in a sliding manner and suitable for sliding spirally relative to the transmission shaft 20, wherein the transmission shaft 20 drives an impeller 24 to rotate circumferentially so as to convey the liquid in the liquid storage tank 1 to an aircraft for heat exchange;
when the pressure in the conveying part 2 increases, the liquid pushes the exchange adjusting assembly 3 to spirally slide towards the axial direction of the transmission shaft 20, so that the liquid in the liquid storage tank 1 is decompressed into the transmission shaft 20 of the conveying part 2.
The exchange adjusting assembly 3 comprises two adjusting pipes 31 which are oppositely arranged, and a telescopic piece 32 which is fixed between the two adjusting pipes 31;
The transmission shaft 20 is provided with a receiving hole along the radial direction, and the adjusting tube 31 is slidably disposed in the receiving hole.
The exchange adjusting assembly 3 further comprises a sealing piece 35, wherein the sealing piece 35 is rotatably arranged in the accommodating hole, and the sealing piece 35 is suitable for sealing the pressure discharge hole 21 at the upper end of the transmission shaft;
a limiting block 36 is fixed at the lower end of the sealing piece 35, and the telescopic piece 32 is suitable for being abutted against the limiting block 36;
When the two adjusting pipes 31 are moved in a spiral manner, the telescopic member 32 is adapted to push the limiting block 36 to turn over, so that the sealing plate 35 opens the pressure discharge hole 21.
Some embodiments provide a method of operating an aircraft liquid cooling apparatus, comprising:
The transmission shaft 20 drives the impeller 24 to circumferentially rotate so as to convey the liquid in the liquid storage tank 1 to the aircraft, and the liquid is gasified and absorbed in the aircraft so as to dissipate heat of the aircraft;
The gasified gas is cooled and condensed back into liquid in an energy accumulator in the aircraft, and the liquid is conveyed back into the liquid storage tank 1 by a reflux pump;
the liquid which flows back passes through the exchange regulating assembly 3, and is suitable for filtering and intercepting impurities in the liquid which flows back;
When the pressure in the conveying part 2 increases, the liquid pushes the exchange adjusting assembly 3 to spirally slide towards the axial center direction of the transmission shaft 20, so that the liquid in the liquid storage tank 1 is decompressed inwards after the transmission shaft 20 of the conveying part 2.
In describing embodiments of the present invention, unless explicitly stated or limited otherwise, the terms "mounted," "connected," "coupled," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected, mechanically connected, electrically connected, directly connected, indirectly connected via an intervening medium, or in communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Moreover, terms such as "first," "second," and other numerical terms when used herein do not imply a sequence or order unless clearly indicated by the context. Thus, a first element, component, region, layer or section discussed above could be termed a second element, component, region, layer or section without departing from the teachings of the example embodiments.
Spatially relative terms, such as "inner," "outer," "lower," "upper," and the like, may be used herein to facilitate the description of one element or feature's relationship to another element or feature as illustrated in the figures. Spatially relative terms may be intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "below" or "beneath" other elements or features would then be oriented "above" the other elements or features. Thus, the example term "below" may encompass both an orientation of above and below. The device may be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
In the discussion above, the terms "about," "approximately," "substantially," and the like, when used to describe a value, mean a variation of +/-10% of the value, unless otherwise indicated.
With the above-described preferred embodiments according to the present invention as an illustration, the above-described descriptions can be used by persons skilled in the relevant art to make various changes and modifications without departing from the scope of the technical idea of the present invention. The technical scope of the present invention is not limited to the description, but must be determined according to the scope of claims.
Claims (9)
1. An aircraft liquid cooling apparatus, comprising:
A liquid storage tank (1) with a conveying part (2) arranged at the lower part,
The conveying part (2) is suitable for conveying the liquid in the liquid storage tank (1) to an aircraft;
an exchange adjustment assembly (3) slidingly disposed on a transmission shaft (20) of the conveying section (2);
wherein, the liquid in the liquid storage tank (1) is conveyed to the aircraft, and the liquid is gasified in the aircraft to perform heat exchange on the aircraft;
When the condensed liquid flows back upwards through the transmission shaft (20), the exchange adjusting component (3) is suitable for filtering the liquid;
A liquid suction pipe (10) is vertically fixed in the liquid storage tank (1), and the liquid suction pipe (10) is communicated with the conveying part (2);
the liquid level of the liquid in the liquid storage tank (1) is not less than 2/3 of the volume of the liquid storage tank (1);
one end of the transmission shaft (20) close to the liquid storage tank (1) is provided with a row of pressure holes (21);
the exchange adjusting assembly (3) comprises two adjusting pipes (31) which are oppositely arranged, and a telescopic piece (32) which is fixed between the two adjusting pipes (31);
The transmission shaft (20) is provided with an accommodating hole along the radial direction, and the adjusting pipe (31) is arranged in the accommodating hole in a sliding manner.
2. The aircraft liquid cooling device of claim 1, wherein,
A plurality of filtering holes (33) are formed in the circumferential direction of the outer wall of the adjusting pipe (31), and the filtering holes (33) are suitable for filtering large-particle impurities in liquid;
a sealing plate (34) is fixed at the outer end of the adjusting tube (31), and the sealing plate (34) is suitable for sealing the adjusting tube (31).
3. The aircraft liquid cooling device according to claim 2, wherein,
Two spiral grooves are formed in the inner wall of the accommodating hole along the axial direction, one spiral groove corresponds to one adjusting pipe (31), and the spiral directions of the two spiral grooves are opposite.
4. An aircraft liquid cooling device according to claim 3,
The outer wall of the adjusting pipe (31) is fixedly provided with a lug matched with the spiral groove, and the lug is suitable for sliding in the spiral groove.
5. The aircraft liquid cooling device of claim 1, wherein,
The exchange adjusting assembly (3) further comprises a sealing piece (35), the sealing piece (35) is rotatably arranged in the accommodating hole, and the sealing piece (35) is suitable for sealing the pressure discharge hole (21).
6. The aircraft liquid cooling device according to claim 5, wherein,
A limiting block (36) is fixed at the lower end of the sealing piece (35), and the telescopic piece (32) is suitable for being abutted with the limiting block (36);
when the two regulating pipes (31) move in a spiral mode in opposite directions, the telescopic piece (32) is suitable for pushing the limiting block (36) to turn over, so that the sealing piece (35) opens the pressure discharge hole (21).
7. A liquid cooling device for an aircraft is characterized in that,
A liquid storage tank (1) for storing liquid;
a conveying part (2) fixed at the lower end of the liquid storage tank (1), one end of which is communicated with the liquid storage tank (1) and the other end of which is communicated with the aircraft;
an exchange adjustment assembly (3) slidingly arranged on the transmission shaft (20) of the conveying part (2) and adapted to slide helically with respect to the transmission shaft (20);
the transmission shaft (20) drives the impeller (24) to circumferentially rotate so as to convey the liquid in the liquid storage tank (1) to the aircraft, so that the aircraft is subjected to heat exchange;
When the pressure in the conveying part (2) is increased, the liquid pushes the exchange adjusting assembly (3) to spirally slide towards the axial direction of the transmission shaft (20), so that the liquid in the liquid storage tank (1) is decompressed into the transmission shaft (20) of the conveying part (2);
the exchange adjusting assembly (3) comprises two adjusting pipes (31) which are oppositely arranged, and a telescopic piece (32) which is fixed between the two adjusting pipes (31);
The transmission shaft (20) is provided with an accommodating hole along the radial direction, and the adjusting pipe (31) is arranged in the accommodating hole in a sliding manner.
8. The aircraft liquid cooling device according to claim 7, wherein,
The exchange adjusting assembly (3) further comprises a sealing piece (35), the sealing piece (35) is rotatably arranged in the accommodating hole, and the sealing piece (35) is suitable for sealing a pressure discharge hole (21) at the upper end of the transmission shaft;
A limiting block (36) is fixed at the lower end of the sealing piece (35), and the telescopic piece (32) is suitable for being abutted with the limiting block (36);
when the two regulating pipes (31) move in a spiral mode in opposite directions, the telescopic piece (32) is suitable for pushing the limiting block (36) to turn over, so that the sealing piece (35) opens the pressure discharge hole (21).
9. A method of operating an aircraft liquid cooling device according to any one of claims 1-6 or 7-8, comprising:
The transmission shaft (20) drives the impeller (24) to circumferentially rotate so as to convey the liquid in the liquid storage tank (1) to the aircraft, and the liquid is gasified and absorbed in the aircraft so as to radiate heat of the aircraft;
the gasified gas is cooled and condensed back into liquid in an energy accumulator in the aircraft, and the liquid is conveyed back into a liquid storage tank (1) by a reflux pump;
The liquid flowing back passes through the exchange regulating assembly (3), and is suitable for filtering and intercepting impurities in the liquid flowing back;
when the pressure in the conveying part (2) is increased, the liquid pushes the exchange adjusting assembly (3) to spirally slide towards the axis direction of the transmission shaft (20), so that the liquid in the liquid storage tank (1) is decompressed inwards after the liquid in the liquid storage tank is decompressed towards the transmission shaft (20) of the conveying part (2).
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| CN202411311637.2A CN118833420B (en) | 2024-09-20 | 2024-09-20 | Aircraft liquid cooling device and working method thereof |
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Citations (2)
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|---|---|---|---|---|
| CN101730437A (en) * | 2008-10-24 | 2010-06-09 | 南京理工大学 | Radiation cooling system for temperature control of electronic equipment close to space vehicle |
| CN116839403A (en) * | 2023-09-01 | 2023-10-03 | 常州贺斯特科技股份有限公司 | Energy storage and liquid cooling device for aircraft and working method thereof |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07315299A (en) * | 1994-05-27 | 1995-12-05 | Ishikawajima Harima Heavy Ind Co Ltd | Space shuttle resource supply device |
| RU2494933C1 (en) * | 2012-02-06 | 2013-10-10 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | Spacecraft equipment thermal control system |
| JP2015055380A (en) * | 2013-09-10 | 2015-03-23 | 株式会社東芝 | Cooling device |
| CN113771699B (en) * | 2021-09-10 | 2023-07-18 | 大连理工大学 | A two-phase immersion liquid-cooled electric vehicle cold start system based on eddy current heating |
| FR3129661A1 (en) * | 2021-11-29 | 2023-06-02 | Airbus | COMBINED DIHYDROGEN HEATING AND FLUID COOLING SYSTEM FOR AIRCRAFT, AND AIRCRAFT COMPRISING SUCH SYSTEM |
| WO2023239965A2 (en) * | 2022-06-10 | 2023-12-14 | Zeroavia Ltd | Turbo-evaporative cooled ht-pem fuel-cell system |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101730437A (en) * | 2008-10-24 | 2010-06-09 | 南京理工大学 | Radiation cooling system for temperature control of electronic equipment close to space vehicle |
| CN116839403A (en) * | 2023-09-01 | 2023-10-03 | 常州贺斯特科技股份有限公司 | Energy storage and liquid cooling device for aircraft and working method thereof |
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