CN114229042A - Two-way coupling system based on loop heat pipe - Google Patents
Two-way coupling system based on loop heat pipe Download PDFInfo
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- CN114229042A CN114229042A CN202111486366.0A CN202111486366A CN114229042A CN 114229042 A CN114229042 A CN 114229042A CN 202111486366 A CN202111486366 A CN 202111486366A CN 114229042 A CN114229042 A CN 114229042A
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- heat
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- heat pipe
- condenser
- heat dissipation
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- 238000010168 coupling process Methods 0.000 title claims abstract description 19
- 230000008878 coupling Effects 0.000 title claims abstract description 18
- 238000005859 coupling reaction Methods 0.000 title claims abstract description 18
- 230000017525 heat dissipation Effects 0.000 claims abstract description 26
- 230000002457 bidirectional effect Effects 0.000 claims abstract description 8
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical group N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 claims description 5
- 230000005540 biological transmission Effects 0.000 claims description 5
- 229910001220 stainless steel Inorganic materials 0.000 claims description 5
- 239000010935 stainless steel Substances 0.000 claims description 5
- 230000008859 change Effects 0.000 claims description 4
- 238000006243 chemical reaction Methods 0.000 claims description 3
- 239000007788 liquid Substances 0.000 claims description 3
- 239000000306 component Substances 0.000 description 5
- 239000000945 filler Substances 0.000 description 4
- 239000008358 core component Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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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
- B64G1/503—Radiator panels
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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
- F28D15/0233—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 the conduits having a particular shape, e.g. non-circular cross-section, annular
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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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- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Biodiversity & Conservation Biology (AREA)
- Health & Medical Sciences (AREA)
- Environmental & Geological Engineering (AREA)
- Environmental Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Toxicology (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
The invention relates to a loop heat pipe-based bidirectional coupling system, which is characterized in that two heat dissipation surfaces which are respectively in a high-temperature state and a low-temperature state at the same time are connected into a whole through two loop heat pipe systems with opposite heat conduction directions to realize the aim of integral heat dissipation, the two loop heat pipe systems have the same structure and comprise a heat collection part, a capillary pump, a condenser, a pipeline and a working medium, wherein the heat collection part is arranged on one heat dissipation surface and used for collecting heat dissipated by the heat dissipation surface, and the capillary pump is arranged at a heat collection end and used for driving the operation of the loop heat pipe system; the condenser is used for dissipating heat and is arranged on the other heat dissipation surface; the pipeline is used for connecting the capillary pump and the condenser into a closed loop, and the inside of the closed loop bears working media; the invention can improve the heat dissipation capability of the system, reduce the temperature of high-power equipment and effectively improve the reliability of products.
Description
Technical Field
The invention relates to the technical field of thermal control design of spacecrafts, in particular to a heat dissipation technology for high-power equipment under complex heat flow change.
Technical Field
When a certain SAR satellite works in orbit, a large-angle real-time yawing mode is adopted based on a load elimination geocentric angle mechanism, so that heat flow outside an orbit space is complex and changeable, and a non-fixed radiating surface can be selected; meanwhile, the peak value of the heat consumption of load operation reaches 6000W, which exceeds the heat dissipation capacity of the traditional satellite platform. Due to the constraint of the configuration layout of the platform, the size of the spacecraft cannot be expanded, so that the heat dissipation capability of the platform cannot be enhanced by the traditional mode of increasing the heat dissipation surface. According to the on-orbit space thermal environment characteristics of the spacecraft, sunlight only irradiates on one direction at the same time, and the temperature is in a high-temperature environment; at the moment, the other direction is not irradiated by sunlight and faces to a cold space and a natural cold space environment, and the temperature is in a low-temperature environment. The coupling system can be adopted to connect the two heat dissipation surfaces in opposite directions into a whole, so that the uneven distribution of space heat flow is weakened, the overall heat dissipation performance of the platform is improved, and the adaptability of complex variable heat flow can be improved.
In the layout design of the coupled system, the conventional coupling method: for example, an externally-attached heat pipe, a fluid loop scheme and the like are numerous, but because a coupling system needs to realize heat connection of two heat dissipation surfaces in opposite directions in a limited space in a spacecraft, a plurality of deck boards need to be spanned, the layout of equipment in the spacecraft is compact, the line is long, a plurality of obstacles needing to be avoided exist, and the layout design in a narrow space is difficult to realize; the loop heat pipe can adapt to long-distance heat transmission in a limited space, but the application of the loop heat pipe in a coupling system is also limited due to the unique fixed-point single-phase transmission characteristic of the loop heat pipe. Therefore, a bidirectional coupling system based on a loop heat pipe needs to be researched.
Disclosure of Invention
In view of this, the invention provides a bidirectional coupling system of a loop heat pipe, which can solve the difficult problem of complex and variable space heat flow and improve the heat dissipation capability of the system. The specific technical scheme is as follows,
the invention connects two heat dissipation surfaces which are respectively in a high temperature state and a low temperature state at the same time into a whole through two loop heat pipe systems with opposite heat conduction directions, realizes the purpose of integral heat dissipation, has the same structure and comprises five parts which are respectively a heat collecting part, a capillary pump, a condenser, a pipeline and a working medium, wherein,
the heat collecting component is arranged on a radiating surface and is used for collecting the heat dispersed by the radiating surface and collecting the heat at a heat collecting end;
the capillary pump is arranged at the heat collecting end and used for driving the operation of the loop heat pipe system through the internal capillary force;
the condenser is a heat dissipation part and is used for dissipating heat and arranged on the other heat dissipation surface;
the pipeline is used as a connecting part and is used for connecting the capillary pump and the condenser to form a closed loop, and the inside of the closed loop bears working media;
the working medium is a heat transmission carrier, and heat transfer is realized through phase change conversion of the working medium between a gas state and a liquid state.
Further, the heat collecting component adopts a heat pipe.
Furthermore, when the temperature is in the range of-10 ℃ to 50 ℃, the working medium selects ammonia gas.
Furthermore, a stainless steel pipe with the diameter phi of 3-5 mm is selected as the pipeline.
Advantageous effects
The invention can improve the heat dissipation capability of the system from 4500W to 6000W, reduce the temperature of high-power equipment by 5 ℃, and effectively improve the reliability of products.
Drawings
FIG. 1 is a schematic diagram of a loop heat pipe-based bidirectional coupling system.
Detailed Description
The invention is described in detail below, by way of example, with reference to the accompanying drawings.
The two-way coupling system based on the loop heat pipe comprises two loop heat pipe systems with opposite heat conduction directions, such as a left closed quadrangle and a right closed quadrangle in the figure 1, wherein the two loop heat pipe systems have the same structure and specifically comprise a heat collecting part, a capillary pump, a condenser, a pipeline and a working medium. The specific functions of the individual components are as follows:
1) a heat collecting member: the scattered heat is collected by a common heat transfer tool such as a heat pipe and collected at a certain position (a heat collecting end);
2) a capillary pump: the core component of the heat transfer system drives the whole heat transfer system to operate through internal capillary force and is generally arranged at a heat collecting end;
3) a condenser: the heat dissipation part of the heat transfer system, the heat of which is dissipated through the condenser, is generally arranged in a low-temperature area;
4) pipeline: as a connecting part, the capillary pump is connected with the condenser to form a closed loop, and the inside of the closed loop bears working media. Selecting a stainless steel pipe with the diameter phi of 3-5 mm according to the charging amount of the working medium;
5) working medium: the heat transmission carrier of the heat transfer system realizes heat transfer through phase change conversion of the working medium between gas state and liquid state, can be selected according to the using temperature range and pressure, and can select ammonia gas generally within the range of-10 to 50 ℃ commonly used by spacecrafts.
The present invention is described in detail below by way of specific examples.
4 large heat-consuming devices are arranged on the spacecraft + Y deck (defined as plate 1), and 4 large heat-consuming devices are arranged on the spacecraft-Y deck (defined as plate 2). The on-orbit spacecraft carries out attitude maneuver adjustment according to task requirements, sunlight vertically irradiates the + Y cabin plate for a long time in certain time periods, 4 devices on the cabin plate are high in temperature and difficult to dissipate heat, and the temperature of the devices exceeds the upper temperature limit; in some periods, sunlight vertically irradiates on a Y cabin plate for a long time, the temperature of 4 equipment on the cabin plate is high, heat dissipation is difficult, and the temperature of the equipment exceeds the upper temperature limit. Due to the limitation of the configuration layout of the platform, the area of the +/-Y cabin plate of the spacecraft cannot be enlarged, so that a coupling system is required to be adopted to realize the heat transfer between the +/-Y cabin plate under the limited space constraint in the spacecraft, and the heat dissipation capacity of the platform is enhanced.
1) On the plate 1, the heat collecting component is an orthogonal heat pipe, 4X-direction heat pipes and 4Z-direction heat pipes are pre-embedded in the honeycomb plate, the temperature difference between devices is leveled on the honeycomb plate, and heat of 4 large heat consumption devices arranged on the plate 1 is collected at a heat collecting end through the orthogonal heat pipes, so that heat collection is realized;
2) the capillary pump is fixed at the heat collecting end of the plate 1, and high-heat-conductivity filler is adopted between interfaces;
3) the condenser is fixed on the plate 2, and high heat conduction fillers are adopted between interfaces;
4) connecting a capillary pump on the plate 1 and a condenser on the plate 2 into a loop by adopting a stainless steel pipe with the diameter phi of 3mm, wherein the outlet of the capillary pump is connected with the inlet of the condenser, and the outlet of the condenser is connected with the inlet of the capillary pump to finally form a closed loop;
5) according to the working temperature range of the heat transfer system, ammonia gas is selected as a working medium, a certain amount of working medium is filled in the loop, the system is ensured to normally operate in a high-temperature range and a low-temperature range, and heat is transferred from the plate 1 to the plate 2;
6) on the plate 2, the heat collecting component is an orthogonal heat pipe, 4X-direction heat pipes and 4Z-direction heat pipes are pre-embedded in the honeycomb plate, the temperature difference between devices is leveled on the honeycomb plate, and heat of 4 large heat consumption devices arranged on the plate 2 is collected at a heat collecting end through the orthogonal heat pipes, so that heat collection is realized;
7) the capillary pump is fixed at the heat collecting end on the plate 2, and high-heat-conductivity filler is adopted between interfaces;
8) the condenser is fixed on the plate 1, and high heat conduction fillers are adopted between interfaces;
9) connecting the capillary pump on the plate 2 and the condenser on the plate 1 into a loop by adopting a stainless steel pipe with the diameter phi of 3mm, wherein the outlet of the capillary pump is connected with the inlet of the condenser, and the outlet of the condenser is connected with the inlet of the capillary pump to finally form a closed loop;
10) according to the working temperature range of the heat transfer system, ammonia gas is selected as a working medium, a certain amount of working medium is filled in the loop, the system is ensured to normally operate in a high-temperature range and a low-temperature range, and heat is transferred from the plate 2 to the plate 1;
11) according to an on-orbit operation environment, when the temperature of the plate 1 is higher than that of the plate 2, the capillary pump on the plate 1 operates spontaneously to realize the transfer of heat from the plate 1 to the plate 2; when the temperature of the plate 2 is higher than that of the plate 1, the capillary pump on the plate 2 operates to realize the heat transfer from the plate 2 to the plate 1. To this end, a system for the bidirectional transfer of heat between the plates 1 and 2 is constituted.
In the using process, the number of the bidirectional coupling systems can be increased according to the actual situation.
Claims (5)
1. A two-way coupling system based on loop heat pipes is characterized in that two heat dissipation surfaces which are respectively in a high-temperature state and a low-temperature state at the same time are connected into a whole through two loop heat pipe systems with opposite heat conduction directions to realize the purpose of integral heat dissipation, the two loop heat pipe systems have the same structure and comprise five parts which are respectively a heat collecting part, a capillary pump, a condenser, a pipeline and a working medium, wherein,
the heat collecting component is arranged on a radiating surface and is used for collecting the heat dispersed by the radiating surface and collecting the heat at a heat collecting end;
the capillary pump is arranged at the heat collecting end and used for driving the operation of the loop heat pipe system through the internal capillary force;
the condenser is a heat dissipation part and is used for dissipating heat and arranged on the other heat dissipation surface;
the pipeline is used as a connecting part and is used for connecting the capillary pump and the condenser to form a closed loop, and the inside of the closed loop bears working media;
the working medium is a heat transmission carrier, and heat transfer is realized through phase change conversion of the working medium between a gas state and a liquid state.
2. A loop heat pipe based bi-directional coupling system as recited in claim 1 wherein the heat collection assembly further comprises a heat pipe.
3. The loop heat pipe-based bidirectional coupling system as claimed in claim 1, wherein the working medium is selected from ammonia gas when the temperature is in the range of-10 ℃ to 50 ℃.
4. The loop heat pipe-based bidirectional coupling system as claimed in claim 1, wherein the pipeline is a stainless steel pipe with a diameter of Φ 3-5 mm.
5. A loop heat pipe-based bi-directional coupling system as claimed in claim 1, wherein the number of bi-directional coupling systems can be increased according to actual conditions during use.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111486366.0A CN114229042A (en) | 2021-12-07 | 2021-12-07 | Two-way coupling system based on loop heat pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111486366.0A CN114229042A (en) | 2021-12-07 | 2021-12-07 | Two-way coupling system based on loop heat pipe |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114229042A true CN114229042A (en) | 2022-03-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111486366.0A Pending CN114229042A (en) | 2021-12-07 | 2021-12-07 | Two-way coupling system based on loop heat pipe |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1995895A (en) * | 2006-01-05 | 2007-07-11 | 捷飞有限公司 | Loop type heat exchanger |
| CN101566442A (en) * | 2009-05-31 | 2009-10-28 | 北京奇宏科技研发中心有限公司 | Serial-parallel type multi-evaporator loop heat pipe |
| CN105277028A (en) * | 2015-11-16 | 2016-01-27 | 中国电子科技集团公司第十研究所 | Thermal control loop heat pipe of integrated structure |
| US20160054074A1 (en) * | 2014-08-19 | 2016-02-25 | Abb Technology Oy | Cooling element |
| CN106542124A (en) * | 2016-11-23 | 2017-03-29 | 上海宇航系统工程研究所 | A kind of spacecraft Fluid for Single-phase Fluid Loop System heat transfer unit (HTU) driven based on axial-flow pump |
| CN111509117A (en) * | 2020-04-22 | 2020-08-07 | 深圳大学 | Thermoelectric conversion device for moon surface |
-
2021
- 2021-12-07 CN CN202111486366.0A patent/CN114229042A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1995895A (en) * | 2006-01-05 | 2007-07-11 | 捷飞有限公司 | Loop type heat exchanger |
| CN101566442A (en) * | 2009-05-31 | 2009-10-28 | 北京奇宏科技研发中心有限公司 | Serial-parallel type multi-evaporator loop heat pipe |
| US20160054074A1 (en) * | 2014-08-19 | 2016-02-25 | Abb Technology Oy | Cooling element |
| CN105277028A (en) * | 2015-11-16 | 2016-01-27 | 中国电子科技集团公司第十研究所 | Thermal control loop heat pipe of integrated structure |
| CN106542124A (en) * | 2016-11-23 | 2017-03-29 | 上海宇航系统工程研究所 | A kind of spacecraft Fluid for Single-phase Fluid Loop System heat transfer unit (HTU) driven based on axial-flow pump |
| CN111509117A (en) * | 2020-04-22 | 2020-08-07 | 深圳大学 | Thermoelectric conversion device for moon surface |
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