CN111076582B - Anti-reflux multi-core capillary pump assembly for spacecraft - Google Patents
Anti-reflux multi-core capillary pump assembly for spacecraft Download PDFInfo
- Publication number
- CN111076582B CN111076582B CN201911156824.7A CN201911156824A CN111076582B CN 111076582 B CN111076582 B CN 111076582B CN 201911156824 A CN201911156824 A CN 201911156824A CN 111076582 B CN111076582 B CN 111076582B
- Authority
- CN
- China
- Prior art keywords
- capillary
- liquid
- shell
- core
- guide rail
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
- F28D15/00—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies
- F28D15/02—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes
- F28D15/04—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes with tubes having a capillary structure
- F28D15/043—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes with tubes having a capillary structure forming loops, e.g. capillary pumped loops
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
- F28D15/00—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies
- F28D15/02—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes
- F28D15/04—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes with tubes having a capillary structure
- F28D15/046—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes with tubes having a capillary structure characterised by the material or the construction of the capillary structure
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/2029—Modifications to facilitate cooling, ventilating, or heating using a liquid coolant with phase change in electronic enclosures
- H05K7/20336—Heat pipes, e.g. wicks or capillary pumps
Abstract
The invention discloses an anti-reflux multi-core capillary pump assembly for a spacecraft, which comprises a liquid return pipeline, a liquid accumulator shell, an evaporator shell, a main capillary core, a secondary capillary core and a gas phase outlet pipeline, wherein the liquid return pipeline is connected with the liquid accumulator shell; a capillary net is embedded in the part of the secondary capillary core extending into the shell of the liquid reservoir; and a flow state adjusting device is arranged at the part of the liquid return pipeline extending into the shell of the evaporator. The capillary network can capture liquid working media suspended between the cavities in a small droplet mode in a space microgravity environment and convey the liquid working media to the secondary capillary core, so that system failure caused by liquid shortage of the evaporator is prevented; the secondary capillary core is beneficial to dynamically controlling a backflow working medium, assists in supplying liquid to the main capillary core, forms thermal lock and increases the operation efficiency of the system; when the counter flow occurs, the flow state adjusting device can effectively lock the liquid return pipeline, prevent the counter flow from further developing towards an upstream pipeline and prevent the failure of the whole system. The invention can effectively prevent the system failure problem in the operation process of the space microgravity environment.
Description
Technical Field
The invention relates to the technical field of thermal control of spacecrafts, in particular to an anti-reflux multi-core capillary pump assembly for a spacecraft.
Background
The space optical remote sensor has a plurality of internal heat source structures, is influenced by the compact structure of the space remote sensor, has small structures, large power consumption and long working time, wherein a CCD (charge coupled device) component of a visible light camera needs to ensure higher temperature stability while radiating, and the requirement of accurate temperature control of the internal heat source is a key problem which needs to be solved by a thermal control system.
The traditional channel heat pipe is difficult to meet the layout requirements of a space remote sensor with a plurality of heat sources and a compact structure and ensure the stable operation of a system in a space microgravity environment; compared with a common heat pipe, the loop heat pipe has the characteristics of small heat transfer temperature difference, large heat transfer power, long heat transfer distance, high temperature control precision, flexible heat conduction, flexible installation and the like, has wide application prospects in aerospace and ground electronic equipment heat dissipation, and has the working principle as shown in fig. 1.
The capillary pump assembly is a core component of the loop heat pipe, the capillary pressure head provided by the capillary pump assembly drives the working medium to circulate so as to realize the heat exchange of the two-phase flow temperature control system, and the performance of the capillary pump assembly directly influences the operation stability of the system.
The capillary pump component with reasonable design can better provide the capillary pressure head required by the heat exchange circulation of the system and maintain the stable work of the system. But through previous operational feedback it was found that: when the temperature of the loop heat pipe evaporator reaches 30 ℃ in the working process of the satellite, the operation is interrupted.
Through problem positioning analysis, whether the evaporator can obtain stable and continuous liquid working medium supply or not is a key factor of stable operation of the whole system in a core component capillary pump component of a two-phase flow heat exchange system for an aircraft, when the temperature of a radiating surface is sharply reduced, a gas-liquid two-phase working medium area in a condensing pipeline on the radiating surface is shortened, the pressure is sharply reduced, liquid in a liquid return pipeline is caused to generate reverse flow, the liquid supply amount in the evaporator is reduced, even the liquid is sucked back, the temperature of the evaporator is sharply increased due to liquid shortage of the evaporator, the operation is interrupted, and therefore the system is caused to fail.
Disclosure of Invention
The invention aims to provide an anti-reflux multi-core capillary pump assembly for a spacecraft, which can meet the requirement of a capillary pressure head required by the operation of a multi-heat-source precise temperature control system of the spacecraft, inhibit the generation of reflux, enhance the liquid working medium supply of an evaporator and effectively prevent the system failure problem in the operation process of a space microgravity environment.
The technical scheme adopted by the invention is as follows: an anti-reflux multi-wick capillary pump assembly for a spacecraft, comprising: the device comprises a liquid return pipeline, a liquid storage device shell, an evaporator shell, a main capillary core, a secondary capillary core and a gas phase outlet pipeline; the liquid storage device shell is axially connected with the evaporator shell, a liquid return pipe end cover is arranged at the end part of the liquid storage device shell, an outlet pipeline end cover is arranged at the end part of the evaporator shell, and a gas phase outlet pipeline is arranged at the center of the outlet pipeline end cover; the liquid return pipeline extends into the liquid reservoir shell and the evaporator shell from the center of the liquid return pipe end cover, and the secondary capillary core is sleeved on the liquid return pipeline; the main capillary core is positioned in the evaporator shell; the secondary capillary core is positioned in the liquid reservoir shell and the evaporator shell, and the part of the secondary capillary core positioned in the evaporator shell is inserted into the primary capillary core; the part of the secondary capillary core extending into the shell of the liquid reservoir is embedded into the capillary network; a plurality of groups of capillary networks are distributed along the axial direction of the secondary capillary core, and the outer diameter side of each group of capillary networks is connected with a capillary network bracket; the capillary net support is sleeved in the liquid storage device shell and is positioned on the inner wall of the liquid storage device shell; and charging working medium into the liquid storage device shell.
Liquid outlet hole structures are arranged on the parts, extending into the secondary capillary cores, of the liquid return pipelines, the liquid outlet holes are through holes perpendicular to the axial direction of the liquid return pipelines, and 9-11 groups are arranged at intervals.
The outer wall of the secondary capillary core is of a cylindrical structure, the inner wall of the secondary capillary core is provided with a plurality of grooves along the axial direction, four grooves are uniformly arranged on the inner wall of the secondary capillary core along the circumferential direction when seen from the longitudinal section, and each groove occupies 1/8 circumferential width.
The pore diameter of the secondary capillary wick is smaller than that of the primary capillary wick, and the porosity of the secondary capillary wick is larger than that of the primary capillary wick.
The multiple groups of the capillary networks are arranged along the axial direction of the secondary capillary cores, each group comprises four capillary networks, the four capillary networks in each group are uniformly arranged along the circumferential direction of the secondary capillary cores, and each capillary network occupies 1/8 circumferential width.
The capillary net support is of a cylindrical structure, and the surface of the capillary net support, which is in contact with the working medium, is plated with a lyophobic material coating film.
The part of the liquid return pipeline extending into the liquid reservoir shell is provided with a flow state adjusting device, and the flow state adjusting device comprises an upstream limiting block, a first linear guide rail, a flow dividing cavity shell, a sliding sleeve bracket, a second linear guide rail, a third linear guide rail, a downstream limiting block and a sliding sleeve; a raised shunting cavity shell is arranged on the liquid return pipeline; the upstream limiting block is arranged on the inner wall of the liquid return pipeline, is positioned on the upstream side of the shunting cavity shell and is used for limiting the movement of the sliding sleeve to the upstream side; the downstream limiting block is arranged on the inner wall of the liquid return pipeline, is positioned on the downstream side of the shell of the flow dividing cavity and is used for limiting the movement of the sliding sleeve to the downstream side; the inner wall of the liquid return pipeline between the upstream limiting block and the diversion cavity shell is provided with a first linear guide rail, and the inner wall of the diversion cavity shell between the diversion cavity shell and the downstream limiting block is provided with a third linear guide rail; a sliding sleeve support is radially arranged in the shunting cavity shell; a second linear guide rail is arranged on the inner wall of the central hole of the sliding sleeve support; the sliding sleeve is arranged in the first linear guide rail, the second linear guide rail and the third linear guide rail, can move along the first linear guide rail, the second linear guide rail and the third linear guide rail, and is constrained by the upstream limiting block and the downstream limiting block in the axial position; the sliding sleeve is a cylindrical shell with one end sealed, and four liquid inlet holes are uniformly arranged at the sealed end along the circumferential direction.
Compared with the prior art, the invention has the following beneficial effects:
(1) in the invention, the liquid return pipeline extends into the shell of the evaporator, and the part connected with the secondary capillary core is provided with a plurality of groups of liquid outlet hole structures, thereby enhancing the uniform supply of liquid working medium at the evaporator section and inhibiting the problems of local liquid shortage and uneven liquid supply.
(2) In the invention, a secondary capillary core structure is arranged between the main capillary core and the liquid return pipe, one side of the secondary capillary core extends into the liquid storage device, and the other side of the secondary capillary core is connected with the outer wall of the liquid return pipe and the inner diameter side of the main capillary core, so that the dynamic control of a backflow working medium is facilitated, and the liquid supply for the main capillary core is assisted; when the liquid supply of the main capillary core is insufficient, the secondary capillary core collects the liquid working medium in the liquid reservoir and conveys the liquid working medium to the main capillary core, and the liquid suction capacity is enhanced and the infusion resistance is reduced by the porosity of the secondary capillary core which is smaller than the pore diameter of the main capillary core and larger than the pore diameter of the main capillary core; meanwhile, the secondary capillary core has a thermal locking effect, so that the temperature and pressure in the liquid reservoir are prevented from being directly transmitted to the outlet side of the liquid return pipe, the early vaporization of the liquid return pipe is avoided, and the system operation efficiency is increased.
(3) According to the invention, a capillary network structure is arranged between the part of the secondary capillary core extending into the liquid reservoir and the liquid reservoir shell, and the capillary network is beneficial to capturing small liquid drops suspended in the liquid reservoir under the condition of space microgravity and conveying the small liquid drops to the secondary capillary core, so that the secondary capillary core can still effectively obtain sufficient liquid working medium supply under the microgravity environment, and the liquid shortage condition is avoided; meanwhile, the capillary net support and the capillary net support the secondary capillary core, so that the mechanical strength of the system is improved.
(4) In the invention, the part of the liquid return pipeline extending into the shell of the liquid storage device is provided with a flow state adjusting device, and the flow state adjustment of forward flow and reverse flow is realized through the sliding sleeve which can automatically adjust the position; when the working medium flows in the forward direction, the sliding sleeve is positioned to enable the shunting cavity to be in a working state, and the working medium can be supplied to the whole capillary pump assembly through the liquid return pipeline; when the liquid return pipeline generates counter flow, the sliding sleeve moves to the position for closing the flow dividing cavity under the impact of the working medium flowing reversely, the liquid return pipeline is effectively locked, and the counter flow is prevented from further developing to an upstream pipeline; at the moment, the evaporator continues to work by the liquid supplied by the multiple capillary cores from the liquid storage device until the evaporator returns to a normal working state, and the occurrence of system failure is effectively prevented.
Drawings
FIG. 1 is a schematic diagram of a loop heat pipe system for a spacecraft;
FIG. 2 is a cross-sectional view of the anti-reflux multi-wick capillary pump assembly of the present invention;
FIG. 3 is a cross-sectional view taken along line A-A of FIG. 2;
FIG. 4 is a partial enlarged view of portion I of FIG. 2 illustrating a forward flow condition;
FIG. 5 is a partial enlarged view of portion I of FIG. 2 illustrating the structure of the reverse flow operation;
FIG. 6 is a cross-sectional view taken along line B-B of FIG. 4;
FIG. 7 is a cross-sectional view taken along line C-C of FIG. 4;
in the figure, 1: a return line; 2: a reservoir housing; 3: an evaporator housing; 4: a primary wick; 5: a secondary wick; 6: a gas phase outlet line; 7: an outlet pipeline end cover; 8: a liquid outlet hole; 9: a capillary network; 10: a capillary network support; 11: a liquid return pipe end cover; 12: an upstream stopper; 13: a first linear guide rail; 14: a shunt chamber housing; 15: a sliding sleeve support; 16: a second linear guide; 17: a third linear guide rail; 18: a downstream limiting block; 19: a sliding sleeve; 20: and a liquid inlet hole.
Detailed Description
The following detailed description of the present invention will be made in conjunction with the accompanying drawings and examples. The following examples are intended to illustrate the invention but are not intended to limit the scope of the invention.
As shown in fig. 2 and fig. 3, the anti-reflux multi-core capillary pump assembly for spacecraft of the present invention comprises a liquid return pipeline 1, a liquid reservoir housing 2, an evaporator housing 3, a primary capillary core 4, a secondary capillary core 5, a gas phase outlet pipeline 6 and a flow state adjusting device, wherein the liquid reservoir housing 2 and the evaporator housing 3 are axially connected, and both are cylindrical structures; a liquid return pipe end cover 11 is arranged at the end part of the liquid storage device shell 2; the gas phase outlet pipeline 6 is fixed at the end cover of the evaporator shell 3 which is not connected with the liquid storage device shell 2 through an outlet pipeline end cover 7; micro channels which are uniformly distributed are arranged on the inner wall of the evaporator shell 3 along the axial direction and the circumferential direction, the outer diameter side of the main capillary core 4 is tightly matched with the inner wall of the evaporator shell 3, and a steam channel is formed in the micro channels on the inner wall of the evaporator shell 3; the liquid return pipeline 1 extends into the liquid reservoir shell 2 and the evaporator shell 3 from the center of the liquid return pipe end cover 11, and 9-11 groups of liquid outlet holes 8 vertical to the axial direction are uniformly distributed on the part of the liquid return pipeline extending into the evaporator shell 3; the outer ring of the secondary capillary core 5 is of a cylindrical structure, the inner ring of the secondary capillary core is of a groove-shaped structure, four grooves are uniformly distributed, and each groove occupies 1/8 circumferential width; the liquid return pipeline 1 is sleeved in the groove-shaped structure of the inner ring of the secondary capillary core 5, and the part of the outer ring of the secondary capillary core 5, which extends into the evaporator shell 3, is contacted with the inner ring of the main capillary core 4; preferably, the pore diameter of the secondary capillary wick 5 is smaller than that of the primary capillary wick 4, and the porosity is larger than that of the primary capillary wick 4; a plurality of groups of capillary networks 9 are radially distributed on the part of the secondary capillary core 5 in the liquid reservoir shell 2, each group comprises four capillary networks 9 which are uniformly distributed along the circumference of the secondary capillary core 5, each capillary network occupies 1/8 circumferential width, the inner diameter side of each capillary network 9 is embedded into the part of the secondary capillary core 5 extending into the liquid reservoir shell 2, and the outer side of each capillary network is connected with the capillary network bracket 10; the capillary net support 10 is in a cylindrical structure, is sleeved in the liquid reservoir shell 2, and structurally supports the capillary net 9 and the secondary capillary core 5; preferably, the surface of the capillary network support 10, which is in contact with the working medium, is plated with a lyophobic material coating film; working medium is charged into the liquid reservoir shell 2.
As shown in fig. 4, 6 and 7, a fluid state adjusting device is disposed at a portion of the liquid return pipeline 1 extending into the reservoir housing, and includes an upstream limiting block 12, a first linear guide rail 13, a diversion chamber housing 14, a sliding sleeve bracket 15, a second linear guide rail 16, a third linear guide rail 17, a downstream limiting block 18 and a sliding sleeve 19; a raised shunting cavity shell 14 is arranged on the liquid return pipeline 1; the upstream limiting block 12 is arranged on the inner wall of the liquid return pipeline 1, is positioned on the upstream side of the flow dividing cavity shell 14 and is used for limiting the movement of the sliding sleeve 19 to the upstream side; the downstream limiting block 18 is arranged on the inner wall of the liquid return pipeline 1 and positioned on the downstream side of the flow dividing cavity shell 14, and is used for limiting the movement of the sliding sleeve 19 to the downstream side; a first linear guide rail 13 is arranged on the inner wall of the liquid return pipeline 1 between the upstream limiting block 12 and the diversion chamber shell 14, and a third linear guide rail 17 is arranged on the inner wall of the diversion chamber shell 14 and the downstream limiting block 18; the split chamber housing 14 is radially arranged with a sliding sleeve holder 15; a second linear guide rail 16 is arranged on the inner wall of the central hole of the sliding sleeve support 15; the sliding sleeve 19 is arranged in the first linear guide rail 13, the second linear guide rail 16 and the third linear guide rail 17, can flexibly move along the first linear guide rail 13, the second linear guide rail 16 and the third linear guide rail 17, and is constrained by the upstream limiting block 12 and the downstream limiting block 18 in axial position; when the sliding sleeve 19 is a cylindrical shell with one sealed end, four liquid inlet holes 20 are uniformly arranged at the sealed end along the circumferential direction.
As shown in fig. 2, in the operation process of the capillary pump assembly, the evaporator shell 3 is heated to evaporate the liquid working medium in the main capillary wick 4 in contact with the evaporator shell, a meniscus is formed inside the pore structure in the main capillary wick 4, a capillary head is generated, and the whole system is driven to work; the gaseous working medium obtained under the driving of capillary force is converged into a cavity at the side of an outlet pipeline end cover 7 along a micro channel distributed on the inner wall of the evaporator shell 3 and enters the whole loop heat pipe system for the spacecraft to circulate along a gas phase outlet pipeline 6; liquid working medium formed by condensation after heat is released by a condenser assembly and the like enters a capillary pump assembly through a liquid return pipeline 1, the liquid return working medium flows through a flow state adjusting device, then flows out of a liquid outlet hole 8 formed in the part of the liquid return pipeline 1, which is positioned in an evaporator shell 3, and is absorbed by a secondary capillary core 5, and the secondary capillary core 5 supplies part of the liquid working medium to a main capillary core 4 along the radial direction, vaporizes under the heating action of the evaporator shell 3, and enters a system for circulation along a gas phase outlet pipeline 6; excessive backflow liquid working medium which is not absorbed by the secondary capillary core 5 flows into a liquid storage device cavity contained in the liquid storage device shell 2 along a groove-shaped structure of an inner ring of the secondary capillary core 5 to be stored; controlling the temperature of the liquid storage device shell 2, wherein the working medium is in a gas-liquid mixed state at the controlled temperature; the capillary net 9 captures a liquid working medium which is suspended in a liquid reservoir cavity contained in the liquid reservoir shell 2 in a space microgravity environment in a small liquid droplet mode and conveys the liquid working medium to a part of the secondary capillary core 5 positioned in the liquid reservoir shell 2; when the liquid supply of the primary capillary core 4 is insufficient, the capillary network 9 captures and transports the liquid working medium which is positioned in the liquid reservoir shell 2 by the secondary capillary core 5 to the primary capillary core 4 along the part of the secondary capillary core 5 positioned in the evaporator shell 3 for liquid supply supplement, and the liquid working medium is vaporized under the heating action of the evaporator shell 3 and enters the system for circulation along the gas phase outlet pipeline 6.
As shown in fig. 4, 6 and 7, when the liquid working medium in the liquid return pipeline 1 flows downstream through the flow state adjusting device, the sliding sleeve 19 is pushed to the position contacting with the downstream limiting block 18 along the first linear guide rail 13, the second linear guide rail 16 and the third linear guide rail 17 under the action of the driving force of the flow direction of the liquid working medium; the incoming liquid working medium enters the space of the shunting cavity shell 14 after passing through the upstream limiting block 12, returns to the pipeline along a liquid inlet hole 20 arranged on the sliding sleeve 19 after passing through the sliding sleeve support 15, and continues to be conveyed to a liquid outlet hole 8 along the liquid return pipeline 1 after passing through the downstream limiting block 18, thereby realizing the forward circulation of the whole system.
As shown in fig. 5, when the backflow pipeline 1 occurs, the sliding sleeve 19 moves to a position contacting with the upstream limiting block 12 along the first linear guide rail 13, the second linear guide rail 16 and the third linear guide rail 17 under the impact of the working medium flowing in the reverse direction to close the diversion cavity, so as to effectively lock the backflow pipeline 1 and prevent the backflow from further developing towards the upstream pipeline; at this time, the primary capillary wick 4 continues to operate by the liquid working medium sucked from the reservoir containing cavity contained in the reservoir housing 2 by the capillary net 9 and the secondary capillary wick 5 under the heating action of the evaporator housing 3 until the normal downstream operating state is recovered, thereby effectively preventing the occurrence of system failure.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
The present invention has not been described in detail, partly as is known to the person skilled in the art.
Claims (7)
1. An anti-reflux multi-wick capillary pump assembly for a spacecraft, comprising: the device comprises a liquid return pipeline (1), a liquid reservoir shell (2), an evaporator shell (3), a main capillary core (4), a secondary capillary core (5) and a gas phase outlet pipeline (6); the liquid storage device shell (2) is axially connected with the evaporator shell (3), a liquid return pipe end cover (11) is installed at the end part of the liquid storage device shell (2), an outlet pipeline end cover (7) is installed at the end part of the evaporator shell (3), and the gas phase outlet pipeline (6) is installed at the center of the outlet pipeline end cover (7); the liquid return pipeline (1) extends into the liquid reservoir shell (2) and the evaporator shell (3) from the center of the liquid return pipe end cover (11), and the secondary capillary core (5) is sleeved on the liquid return pipeline (1); the main capillary core (4) is positioned in the evaporator shell (3); the secondary capillary core (5) is positioned in the liquid reservoir shell (2) and the evaporator shell (3), and the part of the secondary capillary core positioned in the evaporator shell (3) is inserted into the primary capillary core (4); the part of the secondary capillary core (5) extending into the liquid reservoir shell (2) is embedded into the capillary network (9); a plurality of groups of capillary networks (9) are distributed along the axial direction of the secondary capillary core (5), and the outer diameter side of each group of capillary networks is connected with a capillary network bracket (10); the capillary net support (10) is sleeved in the liquid storage device shell (2) and is positioned on the inner wall of the liquid storage device shell (2); working medium is charged into the liquid storage device shell (2).
2. The anti-reflux multi-wick capillary pump assembly for the spacecraft as claimed in claim 1, wherein the part of the liquid return pipeline (1) extending into the secondary capillary wick (5) is provided with a structure of liquid outlet holes (8), the liquid outlet holes (8) are through holes perpendicular to the axial direction of the liquid return pipeline (1), and 9-11 groups are arranged at intervals.
3. The anti-reflux multi-wick capillary pump assembly for the spacecraft as set forth in claim 1 or 2, wherein the outer wall of the secondary capillary core (5) is cylindrical, the inner wall is axially provided with a plurality of grooves, and when viewed in a longitudinal section, the inner wall of the secondary capillary core (5) is uniformly provided with four grooves along the circumferential direction, and each groove occupies 1/8 circumferential width.
4. The anti-reflux multi-wick capillary pump assembly for spacecraft of claim 3, wherein the pore diameter of the secondary capillary wick (5) is smaller than the pore diameter of the primary capillary wick (4), and the porosity of the secondary capillary wick (5) is larger than the porosity of the primary capillary wick (4).
5. The anti-reflux multicore capillary pump assembly for spacecraft of claim 4, wherein the capillary networks (9) are arranged in multiple groups along the axial direction of the secondary capillary core (5), each group comprising four capillary networks (9), and the four capillary networks (9) in each group are uniformly arranged along the circumference of the secondary capillary core (5), and each occupy 1/8 circumferential widths.
6. The anti-reflux multi-wick capillary pump assembly for the spacecraft as claimed in claim 5, wherein the capillary network support (10) is a cylindrical structure, and the surface of the capillary network support, which is in contact with the working medium, is coated with a lyophobic material.
7. The anti-backflow multi-core capillary pump assembly for the spacecraft as claimed in claim 6, wherein a flow state adjusting device is arranged on a part of the liquid return pipeline (1) extending into the reservoir shell (2), and comprises an upstream limiting block (12), a first linear guide rail (13), a shunt cavity shell (14), a sliding sleeve bracket (15), a second linear guide rail (16), a third linear guide rail (17), a downstream limiting block (18) and a sliding sleeve (19); a raised shunting cavity shell (14) is arranged on the liquid return pipeline (1); the upstream limiting block (12) is arranged on the inner wall of the liquid return pipeline (1), is positioned on the upstream side of the flow dividing cavity shell (14) and is used for limiting the movement of the sliding sleeve (19) to the upstream side; the downstream limiting block (18) is arranged on the inner wall of the liquid return pipeline (1), is positioned on the downstream side of the flow dividing cavity shell (14), and is used for limiting the movement of the sliding sleeve (19) to the downstream side; a first linear guide rail (13) is arranged on the inner wall of the liquid return pipeline (1) between the upstream limiting block (12) and the shunting cavity shell (14), and a third linear guide rail (17) is arranged on the inner wall of the shunting cavity shell (14) between the downstream limiting block (18); a sliding sleeve support (15) is radially arranged in the flow dividing cavity shell (14); a second linear guide rail (16) is arranged on the inner wall of the central hole of the sliding sleeve bracket (15); the sliding sleeve (19) is arranged in the first linear guide rail (13), the second linear guide rail (16) and the third linear guide rail (17), can move along the first linear guide rail (13), the second linear guide rail (16) and the third linear guide rail (17), and is constrained by the upstream limiting block (12) and the downstream limiting block (18) at the axial position; the sliding sleeve (19) is a cylindrical shell with one end sealed, and four liquid inlet holes (20) are uniformly arranged at the sealed end along the circumferential direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911156824.7A CN111076582B (en) | 2019-11-22 | 2019-11-22 | Anti-reflux multi-core capillary pump assembly for spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911156824.7A CN111076582B (en) | 2019-11-22 | 2019-11-22 | Anti-reflux multi-core capillary pump assembly for spacecraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111076582A CN111076582A (en) | 2020-04-28 |
| CN111076582B true CN111076582B (en) | 2021-03-26 |
Family
ID=70311350
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911156824.7A Active CN111076582B (en) | 2019-11-22 | 2019-11-22 | Anti-reflux multi-core capillary pump assembly for spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111076582B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113251839B (en) * | 2021-05-20 | 2022-07-22 | 北京空间飞行器总体设计部 | Evaporator, liquid storage device and loop heat pipe |
| CN114710923A (en) * | 2022-02-10 | 2022-07-05 | 中国科学院上海技术物理研究所 | Evaporator based on high-permeability high-capillary-force multi-scale capillary core |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2117893C1 (en) * | 1995-11-17 | 1998-08-20 | Научно-производственное объединение им.С.А.Лавочкина | Heat-transfer two-phase loop (versions) |
| FR2783313A1 (en) * | 1998-09-15 | 2000-03-17 | Matra Marconi Space France | HEAT TRANSFER DEVICE |
| ATE319972T1 (en) * | 2000-06-30 | 2006-03-15 | Swales Aerospace | PHASE CONTROL IN A CAPILLARY EVAPORATOR |
| CN2788115Y (en) * | 2005-03-10 | 2006-06-14 | 中国科学院理化技术研究所 | Deep cryogenic loop heat pipe for cryogenic integrated system |
| JP2007107784A (en) * | 2005-10-12 | 2007-04-26 | Fujikura Ltd | Loop type heat pipe |
| FR2949642B1 (en) * | 2009-08-27 | 2012-05-04 | Alstom Transport Sa | ELECTRIC POWER CONVERTER FOR A RAILWAY VEHICLE |
| EP2940416B1 (en) * | 2012-12-28 | 2017-09-27 | Ibérica del Espacio, S.A. | Loop heat pipe apparatus for heat transfer and thermal control |
| CN106225535B (en) * | 2016-07-22 | 2018-12-21 | 北京空间机电研究所 | A kind of cylindrical type loop circuit heat pipe capillary pump assembly |
| CN108253830B (en) * | 2018-01-30 | 2023-11-14 | 中国科学院理化技术研究所 | Loop heat pipe with auxiliary infusion pipeline |
| CN108267036A (en) * | 2018-01-30 | 2018-07-10 | 中国科学院理化技术研究所 | The loop heat pipe of micro-channel structure auxiliary drive |
| CN208398694U (en) * | 2018-01-30 | 2019-01-18 | 中国科学院理化技术研究所 | Cryogenic loop heat pipe |
-
2019
- 2019-11-22 CN CN201911156824.7A patent/CN111076582B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN111076582A (en) | 2020-04-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111076582B (en) | Anti-reflux multi-core capillary pump assembly for spacecraft | |
| US10996003B2 (en) | Loop heat pipe with vapor-liquid two-phase flow injector | |
| US6990816B1 (en) | Hybrid capillary cooling apparatus | |
| CN100424457C (en) | Controllable bi-circulating hot-pipe system | |
| US10842044B2 (en) | Cooling system in hybrid electric propulsion gas turbine engine | |
| CN103344143B (en) | Evaporator and liquid reservoir used for loop heat pipe and application thereof | |
| US4470450A (en) | Pump-assisted heat pipe | |
| US6810946B2 (en) | Loop heat pipe method and apparatus | |
| US6948556B1 (en) | Hybrid loop cooling of high powered devices | |
| CN109870053B (en) | Multi-flexible evaporator loop heat pipe temperature control system and method for space station scientific load cabinet | |
| CN111642103A (en) | High heat flow density porous heat sink flow cooling device | |
| CN101534627A (en) | High-effective integral spray cooling system | |
| US4492266A (en) | Manifolded evaporator for pump-assisted heat pipe | |
| US4252185A (en) | Down pumping heat transfer device | |
| CN110530185A (en) | A kind of micro-structure liquid self-propelled plates formula loop circuit heat pipe with branch | |
| JPH10503580A (en) | Energy transfer system between hot and cold heat sources | |
| US20020092758A1 (en) | Distiller employing separate condensate and concentrate heat-exchange paths | |
| CN107726904A (en) | A kind of Micropump secondary ring heat pipe for multi-heat source radiating | |
| CN109458864B (en) | Capillary pump loop heat pipe with outer space working capacity and working method | |
| US10859318B2 (en) | Serial thermosyphon | |
| CN211903867U (en) | Waste heat discharge heat exchanger device using heat pipe as heat conducting element | |
| CN112000206A (en) | Heat radiation system based on pump-driven capillary phase change loop | |
| CN112432532A (en) | Evaporator assembly and loop heat pipe | |
| US4231720A (en) | Pump for fluid media having different temperatures | |
| CN108457826B (en) | Working medium supply device of electric propeller and electric propeller |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |