CN111076584A - Truss heat pipe and loop heat pipe coupling heat transfer assembly for spacecraft - Google Patents
Truss heat pipe and loop heat pipe coupling heat transfer assembly for spacecraft Download PDFInfo
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- CN111076584A CN111076584A CN201911195085.2A CN201911195085A CN111076584A CN 111076584 A CN111076584 A CN 111076584A CN 201911195085 A CN201911195085 A CN 201911195085A CN 111076584 A CN111076584 A CN 111076584A
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- heat exchanger
- heat
- heat pipe
- shell
- truss
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- 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
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- G—PHYSICS
- G03—PHOTOGRAPHY; CINEMATOGRAPHY; ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ELECTROGRAPHY; HOLOGRAPHY
- G03B—APPARATUS OR ARRANGEMENTS FOR TAKING PHOTOGRAPHS OR FOR PROJECTING OR VIEWING THEM; APPARATUS OR ARRANGEMENTS EMPLOYING ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ACCESSORIES THEREFOR
- G03B17/00—Details of cameras or camera bodies; Accessories therefor
- G03B17/55—Details of cameras or camera bodies; Accessories therefor with provision for heating or cooling, e.g. in aircraft
Abstract
A truss heat pipe and loop heat pipe coupling heat transfer assembly for a spacecraft comprises a heat exchanger shell (2), a heat exchanger core, a packaging end (1), a switching joint (4) and an end cover (3); the heat exchanger shell (2) is coupled with the loop heat pipe condensation pipeline in a coil pipe welding mode, the heat exchanger core is coupled with the heat exchanger shell (2) in a circumferential fin (11) inserting mode, one end of the heat exchanger core is connected with the truss heat pipe shell (5) through the adapter joint (4), and the other end of the heat exchanger core is sealed by the packaging end (1); the heat exchanger core is arranged in a heat exchanger shell (2), fins on the inner side of the heat exchanger shell (2) are in plug-in coupling with fins (11) on the outer side of the heat exchanger core, heat-conducting silicone grease is coated on the coupling part, and two ends of the heat exchanger shell (2) are packaged by end covers (3); the heat exchanger core, the adapter joint (4), the truss heat pipe shell (5) and the packaging end (1) are connected in a sealing manner to form a sealing system.
Description
Technical Field
The invention belongs to the technical field of vapor-liquid phase change heat transfer of spacecrafts, and relates to a component for coupling heat transfer of a truss heat pipe and a loop heat pipe.
Background
Along with the development of a spacecraft to a comprehensive and integrated system direction, the increase of the number of effective loads of the spacecraft and the multi-channel and multi-angle development of a single load are brought, higher requirements are increasingly provided for power consumption resources, the increasing power consumption resource requirements cannot be met without limit due to the limitation of the on-orbit power generation capacity of the solar sailboard, and under the condition, the thermal management concept of the spacecraft highlights the advantages. The important characteristic of the thermal management concept of the spacecraft is that from the perspective of the system, the thermal behavior of the relevant thermal environment and subsystems of the spacecraft is uniformly allocated and comprehensively utilized, so that the energy consumption and the waste heat emission are minimized. The key of the spacecraft thermal management is how to use the available heat source heat consumption for the self thermal insulation of the spacecraft so as to save the thermal control power consumption.
The long-term working heat consumption of a focal plane refrigerator of a certain space camera is 150W, and the long-term working heat consumption of the refrigerator can be used for heat preservation of a front lens barrel of the camera based on a heat management idea. The focal plane of the space camera needs to move when focusing on the track, the focal plane refrigerator is directly coupled with the focal plane structurally, and the focal plane refrigerator also needs to move when focusing on the focal plane, so that a flexible heat conduction link is needed in a heat conduction path between the focal plane refrigerator and a lens barrel in front of the camera, and a loop heat pipe with a flexible pipeline is inevitably selected under the condition.
In the traditional mode, when the loop heat pipe is used for heat transfer, a condensation pipeline of the loop heat pipe needs to be coupled with a heat dissipation surface in a coil pipe welding mode. Aiming at the space camera, a flexible heat conducting link can be added between a focal plane refrigerator and a heat transfer path of a front lens cone by a flexible pipeline of a loop heat pipe, and the moving requirement of the refrigerator during focusing of the camera is met, however, on one hand, the heat transfer path between the focal plane refrigerator and the front lens cone is longer, on the other hand, the front lens cone is a cylinder with the diameter of 1.6 meters and the height of 2.0 meters, and the material is a composite material. On one hand, because the required pipeline is long, the flow resistance which needs to be overcome by the loop heat pipe capillary pump is large, and the maximum heat transfer power of the loop heat pipe capillary pump is reduced; on the other hand, the loop heat pipe condensation pipeline and the composite panel cannot be welded and coupled, the heat conduction resistance between the condensation pipeline and the composite panel is very large, and the heat consumption utilization efficiency of the refrigerator is reduced.
The patent 'a channel heat pipe with circumferential channel and its connection method' (201811022907.2) discloses an axial channel heat pipe with circumferential channel and its connection method, wherein multiple axial channel heat pipe shells with circumferential channel can be combined into a special-shaped channel heat pipe system with internal axial channel and steam channel communicated with each other through uniform temperature joints. The truss type channel heat pipe can be formed by the axial channel heat pipe shell and the temperature equalizing joint, the truss type channel heat pipe shell is provided with fins, and the fins of the pipe shell and the front lens barrel of the camera can be directly installed in a heat conducting mode. If the loop heat pipe firstly transfers the heat of the refrigerator to the truss heat pipe and then transfers the heat to the front lens cone through the truss heat pipe, the problems caused by long loop heat pipe pipelines and incapability of welding and coupling the pipelines and the front lens cone composite plate can be solved.
However, how to couple the loop heat pipe condensation pipeline and the truss heat pipe becomes a problem to be solved.
Disclosure of Invention
The technical problem solved by the invention is as follows: the coupling heat transfer assembly of the truss heat pipe and the loop heat pipe for the spacecraft overcomes the defects of the prior art, realizes the coupling heat transfer of large power consumption, long distance and low thermal resistance between the loop heat pipe and the truss heat pipe, and meets the application requirement of large power consumption and long distance heat management of a mobile heat source of a space camera.
The technical scheme adopted by the invention is as follows: a truss heat pipe and loop heat pipe coupling heat transfer assembly for a spacecraft comprises a heat exchanger shell, a heat exchanger core, a packaging end, an adapter joint and an end cover;
the heat exchanger shell is coupled with the loop heat pipe condensation pipeline in a coil pipe welding mode, the heat exchanger core is coupled with the heat exchanger shell in a circumferential fin splicing mode, one end of the heat exchanger core is connected with the truss heat pipe shell through a switching joint, and the other end of the heat exchanger core is sealed by a packaging end; the heat exchanger core is arranged in the heat exchanger shell, fins on the inner side of the heat exchanger shell are in plug-in coupling with fins on the outer side of the heat exchanger core, heat-conducting silicone grease is coated on the coupling part, and two ends of the heat exchanger shell are packaged by end covers; the heat exchanger core, the adapter joint, the truss heat pipe shell and the packaging end are connected in a sealing manner to form a sealing system.
The heat exchanger shell is of a hollow structure, two sides of the heat exchanger shell are provided with sinking grooves used for placing end covers, spiral grooves for the loop heat pipe condensation pipeline coil pipes are machined on the outer surface of the heat exchanger shell, fins coupled with a heat exchanger core are machined on the inner surface of the heat exchanger shell, the fins on the inner side of the heat exchanger shell are divided into two parts, the first part is short fins, the second part is long fins, the short fins and the long fins are uniformly arranged at intervals along the circumferential direction, and one short fin is arranged between every two adjacent long fins.
The heat exchanger core is of a hollow structure, the inner wall surface of the heat exchanger core is processed with capillary cores, and the sectional size, the circumferential quantity and the circumferential position distribution of the capillary cores are completely consistent with those of the capillary cores in the truss heat pipe shell; the heat exchanger core external structure is divided into three parts along the axial direction, and the first part is a hollow cylindrical structure used for being connected with the adapter connector; the second part is a fin coupled with a fin inside the heat exchanger shell, and the third part is a hollow cylindrical structure for matching with the packaging end.
The fins on the heat exchanger core are distributed along the circumferential direction of the heat exchanger core, a gap for coupling with the long fin is formed between every two adjacent fins when viewed from the cross section, and a groove for coupling with the short fin is formed in the end part of each fin.
The adapter joint is of a hollow structure and is divided into three parts along the axial direction, the two ends of the adapter joint are respectively of hollow cylindrical structures, the inner wall surface of the adapter joint is free of a hair core, one end of the adapter joint is connected with the truss heat pipe shell, and a cylinder matched with the adapter joint on the truss heat pipe shell is inserted into the adapter joint; the other end of the hollow cylindrical structure is connected with one end of the heat exchanger core, and a cylinder matched with the heat exchanger core is inserted into the hollow cylindrical structure; the middle part of the adapter is of a hollow round table-shaped structure, and the inner wall surface of the adapter is provided with a round table inner wall surface capillary core.
The cross section size, the number and the circumferential distribution of the round-truncated-cone-shaped inner wall surface capillary cores at one end of the adapter joint connected with the truss heat pipe shell are consistent with the cross section size, the number and the circumferential distribution of the round-truncated-cone-shaped inner wall surface capillary cores at the inner wall surface of the truss heat pipe shell; the capillary core on the inner wall surface of the circular truncated cone extends to one end of the cylindrical part inserted into the heat exchanger core along the inner wall surface of the circular truncated cone, and the size, the number and the circumferential distribution of the cross section of the capillary core on the wall surface of the side rotary joint are consistent with those of the capillary core in the heat exchanger core; after the truss heat pipe shell is inserted into the adapter joint, the capillary cores of the truss heat pipe shell correspond to the capillary cores on the inner wall surface of the circular truncated cone on the side of the adapter joint one by one and are communicated with each other; after the heat exchanger cores are inserted into the adapter joint, the capillary cores on the wall surface of the heat exchanger cores correspond to the capillary cores on the inner wall surface of the circular table on the side of the adapter joint one by one and are communicated with each other.
Compared with the prior art, the invention has the advantages that:
(1) the coupling heat exchange assembly provided by the invention can realize the coupling heat exchange of the truss heat pipe and the loop heat pipe, and meets the application requirement of long-distance heat management of a high-power mobile heat source;
(2) by using the coupling heat exchange assembly provided by the invention, the loop heat pipe condensation pipeline only needs to be in coil pipe welding coupling with the cylindrical heat exchanger shell, and does not need to be in coil pipe coupling with the large-size front lens cone any more, but the truss heat pipe shell fin and the camera front lens cone are directly installed in a heat conduction manner. Therefore, the length of a loop heat pipe condensation pipeline is shortened, the working medium flow resistance of the loop heat pipe is reduced, the applicable heat transfer power of the coupling heat transfer device is improved, the total thermal resistance between the refrigerating machine and the front lens cone is reduced, and the overall heat transfer efficiency is improved;
(3) by using the adapter joint provided by the invention, the heat exchanger core and the truss heat pipe shell can be directly welded into a whole, and the capillary core on the inner wall surface of the heat exchanger core can be mutually communicated with the capillary core on the inner wall surface of the truss heat pipe shell through the adapter joint capillary core, so that the heat exchanger core directly becomes an evaporation section of the truss heat pipe, heat consumption of a heat source transferred to the heat exchanger core is efficiently and uniformly transferred to a front lens cone of a camera through vapor-liquid phase change heat transfer of working media in the truss heat pipe, and the heat consumption utilization rate of the heat source is greatly improved.
Drawings
FIG. 1 is a schematic view of a heat transfer system with coupled truss heat pipes and loop heat pipes;
FIG. 2 is a schematic connection diagram of a coupled heat exchange assembly;
FIG. 3 is a schematic view of the structure of the two end covers after the heat exchanger shell and the heat exchanger core are combined
FIG. 4 is an axial cross-sectional view of the heat exchanger shell;
FIG. 5 is a cross-sectional view of a heat exchanger shell;
FIG. 6 is a cross-sectional view of a heat exchanger core;
FIG. 7 is an axial cross-sectional view of a heat exchanger core;
FIG. 8 is a schematic axial cross-sectional view of an adapter;
FIG. 9 is a schematic circumferential cross-sectional view of an adapter.
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.
A schematic diagram of a truss heat pipe and loop heat pipe coupled heat transfer system is shown in fig. 1.
As shown in fig. 2 and fig. 3, the truss heat pipe and loop heat pipe coupled heat transfer assembly provided by the invention comprises a heat exchanger shell 2, a heat exchanger core, a packaging end 1, an adapter joint 4 and an end cover 3. As shown in fig. 1, a heat exchanger shell 2 is coupled with a loop heat pipe condensation pipeline in a coil pipe welding mode; as shown in fig. 3, the heat exchanger shell 2 and the heat exchanger core are coupled by inserting short fins 8 and long fins 9 into fins 11; as shown in fig. 2, the heat exchanger core is connected with the truss heat pipe shell 5 into a whole through the adapter joint 4; as shown in fig. 3, the end of the heat exchanger core not connected with the adapter connector 4 is sealed by a packaging end head 1; as shown in fig. 3, the heat exchanger shell 2 and the heat exchanger core are combined and then both ends are encapsulated by the end covers 3.
As shown in fig. 4 and 5, the heat exchanger shell 2 is a hollow structure, the outer surface of the heat exchanger shell is provided with a spiral groove 6 for a loop heat pipe condensation pipeline coil, the inner surface of the heat exchanger shell is provided with circumferential fins, and two ends of the heat exchanger shell are provided with sinking grooves 7 for placing the end covers 3. The outer surface spiral groove of the loop heat pipe condensation pipeline is processed on a numerical control lathe, the loop heat pipe condensation pipeline is coiled along the spiral trend of the spiral groove of the heat exchanger shell 2, the loop heat pipe condensation pipeline is tightly attached to the outer surface spiral groove of the heat exchanger, a tensioning tool is needed when the coil is coiled, and after the coil is finished, the loop heat pipe condensation pipeline and the heat exchanger shell 2 are welded into a whole, and then the tensioning tool is removed. The circumferential fins on the inner surface of the heat exchanger shell 2 are processed in a linear cutting mode, and in order to ensure that the circumferential fins on the inner surface of the heat exchanger shell 2 can be smoothly inserted with the circumferential fins 11 on the outer surface of the heat exchanger core, the physical size of the circumferential fins on the inner surface of the heat exchanger shell 2 is subjected to certain negative tolerance during processing. The fin that heat exchanger shell 2 internal surface and heat exchanger core coupling divide into two parts, and the first part is short fin 8, and the second part is long fin 9, and short fin 8 and long fin 9 all set up a short fin 8 along circumference interval evenly between two adjacent long fins 9.
As shown in fig. 6 and 7, the heat exchanger core is a hollow structure, the capillary core 10 is processed on the inner wall surface, and the sectional size, the circumferential number and the circumferential position distribution of the capillary core 10 are completely consistent with those of the capillary core in the truss heat pipe shell 5. The external structure of the heat exchanger core is divided into 3 parts along the axial direction, and the part 1 is a hollow cylindrical structure 14 matched with the adapter joint 4; the 2 nd part is the fin 11 with the fin coupling of heat exchanger shell 2 inboard, and the 3 rd part is used for with encapsulation end 1 matching cylindrical structure 15, and cylindrical structure 15 tip processing has heavy groove 16 for place encapsulation end 1. The external circumferential fins 11 are machined by linear cutting, and certain negative tolerance is taken for the physical size of the circumferential fins 11 on the outer surface of the heat exchanger core during machining in order to ensure that the circumferential fins on the inner surface of the heat exchanger shell 2 can be smoothly inserted with the circumferential fins 11 on the outer surface of the heat exchanger core. Meanwhile, as shown in fig. 6, in order to increase the contact area between the circumferential fins of the heat exchanger shell 2 and the circumferential fins 11 of the heat exchanger core as much as possible and reduce the contact thermal resistance, on the premise of ensuring the strength of the fins 11, the fins 11 on the heat exchanger core are distributed along the circumferential direction of the heat exchanger core, a gap 13 for coupling with the long fin 9 is formed between two adjacent fins 11 when viewed from the cross section, a groove 12 for coupling with the short fin 8 is formed in the end of each fin 11, and correspondingly, as shown in fig. 5, the circumferential fins on the inner side of the heat exchanger shell 2 are provided with the short fins 8 and the long fins 9 corresponding to the short.
As shown in fig. 8 and 9, the adapter 4 is a hollow structure, and the structure thereof is divided into 3 parts along the axial direction, both ends of the adapter are hollow cylindrical structures, and the inner wall surface of the adapter has no wick, wherein the hollow structure 17 at one end is connected with the truss heat pipe shell 5, and a cylinder matched with the truss heat pipe shell 5 is inserted into the hollow structure; the other end of the hollow structure 20 is connected with one end of the heat exchanger core, and a cylinder matched with the heat exchanger core is inserted into the hollow structure; the middle part is a hollow round table-shaped structure 18, and the inner wall surface is provided with a capillary core 19. At the end inserted into the truss heat pipe shell 5, the cross section size, the number and the circumferential distribution of the circular truncated cone inner wall surface capillary cores 19 are consistent with those of the truss heat pipe shell 5, the circular truncated cone inner wall surface capillary cores 19 extend to the side inserted into the cylindrical part of the heat exchanger core along the circular truncated cone inner wall surface, and the cross section size, the number and the circumferential distribution of the circular truncated cone inner wall surface capillary cores 19 are consistent with those of the heat exchanger core capillary cores 10 at the side. After the truss heat pipe shell 5 is inserted into the adapter 4, measures are taken to ensure that the capillary cores of the truss heat pipe shell 5 are in one-to-one correspondence with the capillary cores 19 on the inner wall surface of the circular table on the side of the adapter 4 and are communicated with each other; after the heat exchanger core is inserted into the adapter connector 4, measures are taken to ensure that the capillary cores 10 on the wall surface of the heat exchanger core are in one-to-one correspondence with the capillary cores 19 on the inner wall surface of the circular table on the side of the adapter connector 4 and are communicated with each other; therefore, the heat exchanger core capillary core 10 is ensured to be communicated with the capillary core of the truss heat pipe shell 5 through the circular truncated cone inner wall surface capillary core 19 of the adapter joint 4.
After the truss heat pipe shell 5 is inserted into the adapter 4 and the capillary cores of the truss heat pipe shell 5 are ensured to be correspondingly communicated with the capillary cores 19 of the inner wall surface of the circular truncated cone on the side of the adapter 4 one by one, the truss heat pipe shell 5 and the adapter 4 are welded into a whole; and after the cylindrical end of the heat exchanger core matched with the adapter joint 4 is inserted into the adapter joint 4 and the heat exchanger capillary core 10 is ensured to be communicated with the capillary core 19 on the inner wall surface of the circular table on the side of the adapter joint 4 in a one-to-one correspondence manner, the heat exchanger core and the adapter joint 4 are welded into a whole. After the packaging end head 1 at the other end of the heat exchanger core is placed into the packaging end head 1 in a sinking way, the packaging end head 1 and the heat exchanger core are welded into a whole. Therefore, the heat exchanger core and the truss heat pipe form a closed system with mutually communicated capillary cores through the adapter joint 4, and the heat exchanger core becomes an evaporation end of the truss heat pipe. The working heat consumption of the focal plane refrigerator is transmitted to the heat exchanger shell 2 through a loop heat pipe condensation pipeline, the heat exchanger shell 2 is transmitted to the heat exchanger core through a coupling fin of the heat exchanger core, the working medium in the heat exchanger core is heated and evaporated to be steam, the steam flows to other pipe shells directly installed by the truss heat pipe and the front lens cone in a heat conduction mode and is condensed to release heat, the heat is transmitted to the front lens cone, the condensed supercooling liquid flows back to the heat exchanger core under the suction effect of the heat exchanger core capillary core 10, and the supercooling liquid is continuously heated and evaporated and repeatedly circulated.
The specific assembling method of the truss heat pipe and the path-changing heat pipe coupling heat exchange assembly is as follows:
step one, finishing the processing of a heat exchanger shell 2, a heat exchanger core, a packaging end head 1, a switching joint 4 and an end cover 3, wherein 2 end covers 3 are processed, and one end cover is divided into 2 parts from the middle;
secondly, coiling the loop heat pipe condensation pipeline along the spiral direction of the spiral groove of the heat exchanger shell 2, and tightening a tool by virtue of the coil in the process of coiling so as to ensure that the heat exchange heat pipe condensation pipeline is tightly attached to the spiral groove of the heat exchanger shell 2;
thirdly, after the loop heat pipe condensation pipeline and the disc tube of the spiral groove of the heat exchanger shell 2 are finished, the loop heat pipe condensation pipeline and the spiral groove of the heat exchanger are welded into a whole, then the tensioning tool is taken out, and the combination of the loop heat pipe condensation pipeline and the heat exchanger shell 2 is used for standby;
step four, assembling the heat exchanger core, the adapter joint 4 and the truss heat pipe shell 5, wherein a cylinder matched with the adapter joint 4 of the heat exchanger core is inserted into a hole matched with the adapter joint 4 during assembling, so as to ensure that the capillary cores 10 of the heat exchanger core are communicated with the capillary cores 19 on the inner wall surface of the circular table on the side of the adapter joint 4 in a one-to-one correspondence manner; the cylinders matched with the truss heat pipe shell 5 and the adapter joint 4 are inserted into the holes matched with the adapter joint 4, so that the capillary cores of the truss heat pipe shell 5 and the capillary cores 19 on the inner wall surface of the circular table on the side of the adapter joint 4 are ensured to be communicated with each other in a one-to-one correspondence mode, the capillary cores 10 of the heat exchanger cores are ensured to be communicated with the capillary cores of the truss heat pipe shell 5 in a one-to-one correspondence mode through the capillary cores 19 of the adapter joint 4, then the heat exchanger cores and the adapter joint 4 are welded into a whole, and the adapter joint 4 and the truss heat;
placing the packaging end head 1 into a packaging end head 1 sink groove of a heat exchanger core, and then welding the packaging end head 1 and the heat exchanger core into a whole;
step six, oppositely inserting the loop heat pipe condensation pipeline and heat exchanger shell 2 assembly in the step 3 and a heat exchanger core which is welded with the truss heat pipe into a whole, starting from the end of a heat exchanger core packaging end 1, and uniformly coating heat-conducting silicone grease on the heat exchanger core external circumferential fins 11 and the heat exchanger shell 2 internal circumferential fins before oppositely inserting;
and seventhly, coating silicon rubber on the surfaces of the heat exchanger shell 2, the heat exchanger core inserting fins and the surfaces of the heat exchanger shell 2, which are in contact with the end covers 3, after inserting, and then adhering the end covers 3 to two ends of the heat exchanger and heat exchanger core assembly. The split end cover 3 is adhered to one side connected with the truss heat pipe, and the split end cover 3 can only be used on the side because the heat exchanger core is welded with the truss heat pipe into a whole in advance.
The present invention has not been described in detail, partly as is known to the person skilled in the art.
Claims (6)
1. A truss heat pipe and loop heat pipe coupling heat transfer assembly for a spacecraft is characterized by comprising a heat exchanger shell (2), a heat exchanger core, a packaging end (1), a switching joint (4) and an end cover (3);
the heat exchanger shell (2) is coupled with the loop heat pipe condensation pipeline in a coil pipe welding mode, the heat exchanger core is coupled with the heat exchanger shell (2) in a circumferential fin (11) inserting mode, one end of the heat exchanger core is connected with the truss heat pipe shell (5) through the adapter joint (4), and the other end of the heat exchanger core is sealed by the packaging end (1); the heat exchanger core is arranged in a heat exchanger shell (2), fins on the inner side of the heat exchanger shell (2) are in plug-in coupling with fins (11) on the outer side of the heat exchanger core, heat-conducting silicone grease is coated on the coupling part, and two ends of the heat exchanger shell (2) are packaged by end covers (3); the heat exchanger core, the adapter joint (4), the truss heat pipe shell (5) and the packaging end (1) are connected in a sealing manner to form a sealing system.
2. The coupling heat transfer assembly of the truss heat pipe and the loop heat pipe for the spacecraft according to claim 1, wherein the heat exchanger shell (2) is of a hollow structure, two sides of the heat exchanger shell are provided with sunken grooves (7) for placing the end covers (3), the outer surface of the heat exchanger shell is provided with spiral grooves (6) for a loop heat pipe condensation pipeline coil, the inner surface of the heat exchanger shell is provided with fins coupled with a heat exchanger core, the fins on the inner side of the heat exchanger shell are divided into two parts, the first part is short fins (8), the second part is long fins (9), the short fins (8) and the long fins (9) are uniformly arranged at intervals along the circumferential direction, and one short fin (8) is arranged between every two adjacent long fins (9).
3. The truss heat pipe and loop heat pipe coupling heat transfer assembly for the spacecraft of claim 1 or 2, wherein the heat exchanger core is of a hollow structure, the capillary cores (10) are processed on the inner wall surface of the heat exchanger core, and the cross-sectional size, the circumferential number and the circumferential position distribution of the capillary cores (10) are completely consistent with those of the capillary cores (10) in the truss heat pipe shell (5); the external structure of the heat exchanger core is divided into three parts along the axial direction, wherein the first part is a hollow cylindrical structure (14) used for being connected with the adapter joint (4); the second part is a fin (11) coupled with the fin on the inner side of the heat exchanger shell (2), and the third part is a hollow cylindrical structure (15) matched with the packaging end head (1).
4. The truss heat pipe and loop heat pipe coupling heat transfer assembly for the spacecraft of claim 3, wherein the fins (11) on the heat exchanger core are distributed along the circumference of the heat exchanger core, when viewed in cross section, a gap (13) for coupling with the long fin (9) is formed between two adjacent fins (11), and the end part of each fin (11) is provided with a groove (12) for coupling with the short fin (8).
5. The coupled heat transfer component of truss heat pipe and loop heat pipe for spacecraft of claim 4, wherein the adapter (4) is a hollow structure, and is divided into three parts along the axial direction, both ends are hollow cylindrical structures, and the inner wall surface has no wick, wherein the hollow cylindrical structure at one end is connected with the truss heat pipe shell (5), and the matched cylinder on the truss heat pipe shell (5) is inserted into the hollow cylindrical structure; the other end of the hollow cylindrical structure is connected with one end of the heat exchanger core, and a cylinder matched with the heat exchanger core is inserted into the hollow cylindrical structure; the middle part of the adapter joint (4) is of a hollow round table-shaped structure, and the inner wall surface of the adapter joint is provided with a round table inner wall surface capillary core (19).
6. The coupled heat transfer component of the truss heat pipe and the loop heat pipe for the spacecraft as claimed in claim 5, wherein the cross-sectional size, the number and the circumferential distribution of the circular truncated cone inner wall surface capillary wick (19) at one end (17) of the adapter joint (4) connected with the truss heat pipe shell (5) are consistent with the cross-sectional size, the number and the circumferential distribution of the circular truncated cone inner wall surface capillary wick at the inner wall surface of the truss heat pipe shell (5); the circular truncated cone inner wall surface capillary cores (19) extend to one end (20) of the cylindrical part inserted into the heat exchanger core along the circular truncated cone inner wall surface, and the cross section size, the number and the circumferential distribution of the circular truncated cone inner wall surface capillary cores (19) on the side of the rotary joint (4) are consistent with those of the capillary cores (10) in the heat exchanger core; after the truss heat pipe shell (5) is inserted into the adapter joint (4), the capillary cores of the truss heat pipe shell (5) correspond to the capillary cores (19) on the inner wall surface of the circular truncated cone on the side of the adapter joint (4) one by one and are communicated with each other; after the heat exchanger core is inserted into the adapter connector (4), the capillary cores (10) on the wall surface of the heat exchanger core correspond to the capillary cores (19) on the inner wall surface of the circular table on the side of the adapter connector (4) one by one and are communicated with each other.
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Cited By (1)
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| CN116469852B (en) * | 2023-04-12 | 2024-05-17 | 广东工业大学 | Integrated chip substrate with loop heat pipe heat dissipation system |
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| JP2001201282A (en) * | 2000-01-18 | 2001-07-27 | Hitachi Ltd | Radiator |
| US20030000681A1 (en) * | 2001-06-27 | 2003-01-02 | Gideon Reisfeld | Efficient heat pumping from mobile platforms using on platform assembled heat pipe |
| US20030000683A1 (en) * | 2001-06-29 | 2003-01-02 | Mast Brian E. | Heat pipe system for cooling flywheel energy storage systems |
| CN100583419C (en) * | 2005-03-28 | 2010-01-20 | 英特尔公司 | Systems for improved passive liquid cooling |
| US7784269B1 (en) * | 2006-08-25 | 2010-08-31 | Xcor Aerospace | System and method for cooling rocket engines |
| CN109297329A (en) * | 2018-09-03 | 2019-02-01 | 北京空间机电研究所 | A kind of axial-grooved heat pipe and attaching method thereof with circumferential channel |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116469852B (en) * | 2023-04-12 | 2024-05-17 | 广东工业大学 | Integrated chip substrate with loop heat pipe heat dissipation system |
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