CN113074570A - Composite phase-change flat heat pipe for satellite - Google Patents
Composite phase-change flat heat pipe for satellite Download PDFInfo
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- CN113074570A CN113074570A CN202110269364.XA CN202110269364A CN113074570A CN 113074570 A CN113074570 A CN 113074570A CN 202110269364 A CN202110269364 A CN 202110269364A CN 113074570 A CN113074570 A CN 113074570A
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- Prior art keywords
- plate
- phase change
- phase
- satellite
- capillary core
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Classifications
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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
- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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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
- F28D15/0283—Means for filling or sealing heat pipes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F21/00—Constructions of heat-exchange apparatus characterised by the selection of particular materials
- F28F21/08—Constructions of heat-exchange apparatus characterised by the selection of particular materials of metal
- F28F21/081—Heat exchange elements made from metals or metal alloys
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F9/00—Casings; Header boxes; Auxiliary supports for elements; Auxiliary members within casings
- F28F9/007—Auxiliary supports for elements
- F28F9/0075—Supports for plates or plate assemblies
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F9/00—Casings; Header boxes; Auxiliary supports for elements; Auxiliary members within casings
- F28F9/26—Arrangements for connecting different sections of heat-exchange elements, e.g. of radiators
Abstract
The invention provides a composite phase change flat heat pipe for a satellite, which comprises: the device comprises a cover plate, a temperature equalizing plate, a phase change plate, a first capillary core, a second capillary core, a liquid working medium and a phase change material; the cover plate is fixedly connected with the temperature equalizing plate, a first sealing chamber cavity is formed between the cover plate and the temperature equalizing plate, the temperature equalizing plate is fixedly connected with the phase change plate, a second sealing chamber cavity is formed between the temperature equalizing plate and the phase change plate, the first capillary core is installed on the upper side of the first sealing chamber cavity, the second capillary core is installed on the lower side of the first sealing chamber cavity, liquid working media are added into the first sealing chamber cavity, and phase change materials are added into the second sealing chamber cavity. The temperature equalizing layer and the phase change layer are welded into a whole, the thickness of the device is reduced, meanwhile, the light metal fins with high thermal conductivity are used as a reinforcing structure, the mechanical strength and the bearing capacity of the shell are enhanced, the thermal conductivity coefficient of the paraffin phase change material is increased, and the weight of the thermal control device is effectively reduced.
Description
Technical Field
The invention relates to the technical field of thermal management, in particular to a composite phase change flat heat pipe for a satellite.
Background
With the development of aerospace technology, many high-power electronic and optical single machines carried on a spacecraft are in a modular design. A plurality of electronic/optical components are distributed in the single machine, and the components usually have the characteristics of short-time periodic work and narrow working temperature zone. If the self heat cannot be effectively dissipated in time, the temperature of the device will be increased sharply. Excessive temperatures can degrade device performance and, more seriously, can increase the failure rate of the device, which can degrade its stability and reliability, thereby affecting the performance and lifetime of the entire single device. The temperature difference between the devices is easy to form larger thermal stress, which reduces the working performance and reliability of the devices and even causes the reduction of the overall performance of the single machine. Therefore, the requirements of heat dissipation and temperature uniformity of the array type multi-heat source are met, heat generated by a plurality of devices is effectively discharged in time, the devices and a single machine are prevented from being overhigh in temperature, and the temperature consistency of each device is ensured. In order to solve the requirement, the aerospace thermal control subsystem needs to adopt corresponding measures to carry out heat dissipation and temperature control on a multi-heat-source single machine working in a short-time narrow temperature region so as to ensure the reliability and the performance of the device.
In order to solve the problem of temperature uniformity of multiple heat sources, a temperature equalization design is adopted, a flat heat pipe structure is adopted, and the vapor-liquid phase change and the capillary force of a foam structure are utilized to realize rapid heat transfer so as to effectively transfer the heat of the multiple heat sources to a phase change layer in time. In order to improve the temperature uniformity of a heat source and meet the application requirements in a space microgravity environment, the design of a capillary core needs to be considered in the design of a temperature equalizing layer, and the capillary core of a foam structure needs to improve enough capillary acting force so as to meet the requirement of liquid rapid transfer in the microgravity environment and avoid local overheating.
In addition, in order to solve the problem of heat storage of short-time working load, a phase-change material is required to store energy, so that a peak clipping effect is achieved. However, the paraffin phase-change material used at normal temperature has extremely low heat conductivity coefficient, influences the energy storage rate and has large temperature difference. In order to improve the heat conductivity of the phase-change material, a reinforced heat conduction structure design is needed, the equivalent heat conductivity of the phase-change material is improved by using a metal micro-rib array with high heat conductivity, and the requirement of rapid heat storage is met.
The temperature equalization technology and the phase change energy storage technology are combined, and the composite phase change energy storage flat heat pipe is designed, so that the heat of multiple heat sources can be timely and quickly stored while the temperature uniformity is ensured, and the temperature stability of devices and a single machine is ensured.
TABLE 1 search of related patent documents
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a composite phase-change flat heat pipe for a satellite.
The invention provides a composite phase change flat heat pipe for a satellite, which comprises: the device comprises a cover plate, a temperature equalizing plate, a phase change plate, a first capillary core, a second capillary core, a liquid working medium and a phase change material;
the cover plate is fixedly connected with the temperature equalizing plate, a first sealing chamber cavity is formed between the cover plate and the temperature equalizing plate, the temperature equalizing plate is fixedly connected with the phase change plate, a second sealing chamber cavity is formed between the temperature equalizing plate and the phase change plate, the first capillary core is installed on the upper side of the first sealing chamber cavity, the second capillary core is installed on the lower side of the first sealing chamber cavity, liquid working media are added into the first sealing chamber cavity, and phase change materials are added into the second sealing chamber cavity.
Preferably, a first square groove is formed in the middle of the upper side of the temperature equalizing plate, supporting fins are installed in the first square groove, and the supporting fins are arranged in an array mode.
Preferably, the first capillary core and the second capillary core are provided with avoiding holes, and the avoiding holes correspond to the supporting ribs in position.
Preferably, a second square groove is formed in the middle of the upper side of the phase change plate, reinforcing ribs are installed in the second square groove, and the reinforcing ribs are arranged in an array mode.
Preferably, the temperature equalizing plate is provided with a heat source device, and the periphery of the cover plate is provided with mounting holes.
Preferably, the cover plate and the temperature equalizing plate are welded by molecular diffusion welding, the temperature equalizing plate and the phase change plate are welded by molecular diffusion welding, the first capillary core is welded to the lower side of the cover plate by molecular diffusion welding, and the second capillary core is welded to the square groove by molecular diffusion welding.
Preferably, a first filling port is arranged at the front end of the left side of the temperature equalizing plate, and the first filling port is communicated with the first sealing chamber cavity.
Preferably, a second filling port is arranged at the front end of the left side of the phase change plate, and the second filling port is communicated with the second sealing chamber cavity.
Preferably, the first capillary wick and the second capillary wick are made of a nickel foam material, and the cover plate, the temperature equalizing plate, the phase change plate, the supporting ribs and the reinforcing ribs are made of light metal with high thermal conductivity.
Preferably, the liquid working medium comprises liquid nitrogen, and the phase change material comprises paraffin.
Compared with the prior art, the invention has the following beneficial effects:
1. the temperature equalizing layer and the phase change layer are welded into a whole, the thickness of the device is reduced, meanwhile, the light metal fins with high thermal conductivity are used as a reinforcing structure, the mechanical strength and the bearing capacity of the shell are enhanced, the thermal conductivity coefficient of the paraffin phase change material is increased, and the weight of the thermal control device is effectively reduced.
2. For a plurality of devices which have temperature uniformity requirements in short-time work, when the devices work, heat is transferred to the phase change layer through the temperature equalization layer, the temperature equalization layer can ensure the temperature uniformity, and the phase change material absorbs large short-time heat to maintain the temperature stability. The composite phase-change flat heat pipe can maintain the temperature of a single machine to be stable and uniform, greatly reduce the scale of an active thermal control system and realize passive thermal control.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic view of a composite phase-change flat heat pipe for a satellite;
FIG. 2 is a top view of a composite phase-change flat heat pipe for a satellite;
FIG. 3 is a front view of a composite phase-change flat heat pipe for a satellite;
FIG. 4 is a structural diagram of the inside of a composite phase-change flat heat pipe temperature plate for a satellite;
FIG. 5 is a view of the internal structure of a composite phase-change flat heat pipe phase-change plate for a satellite;
fig. 6 is a structure diagram of the inside of a composite phase-change flat heat pipe wick for a satellite.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1 to 3, a composite phase-change flat heat pipe for a satellite includes: the device comprises a cover plate 1, a temperature equalizing plate 2, a phase change plate 3, a first capillary core 4, a second capillary core 9, a liquid working medium and a phase change material; the lower side of the cover plate 1 is fixedly connected with the temperature-equalizing plate 2, a first sealing chamber cavity is formed between the cover plate 1 and the temperature-equalizing plate 2, the lower side of the temperature-equalizing plate 2 is fixedly connected with the phase-change plate 3, a second sealing chamber cavity is formed between the temperature-equalizing plate 2 and the phase-change plate 3, a first capillary core 4 is installed on the upper side of the first sealing chamber cavity, a second capillary core 9 is installed on the lower side of the first sealing chamber cavity, a liquid working medium is added into the first sealing chamber cavity, and a phase-change material is added into the second sealing chamber cavity.
As shown in fig. 4 to 6, a first square groove is formed in the middle of the upper side of the temperature equalization plate 2, supporting fins 6 are installed in the first square groove, and the supporting fins 6 are arranged in an array. The first capillary core 4 and the second capillary core 9 are provided with avoiding holes, and the avoiding holes correspond to the supporting ribs in position. The middle of the upper side of the phase change plate 3 is provided with a second square groove, reinforcing ribs 7 are arranged in the second square groove, and the reinforcing ribs 7 are arranged in an array.
Specifically, the temperature-uniforming plate 2 is composed of a light metal base plate with high heat conductivity and an array of supporting ribs 6, the array of supporting ribs 6 is used for strengthening mechanical properties, and a cover plate 1 is welded on the upper wall surface inside the temperature-uniforming plate 2 to form a liquid working medium filling cavity. The phase change plate 3 is composed of a light metal base plate with high heat conductivity and a reinforcing fin 7 array, the reinforcing fin 7 array is used for reinforcing heat conduction, and the phase change plate 3 and the temperature-uniforming plate 2 are welded into a whole to form a phase change material filling cavity. The first capillary core 4 and the second capillary core 9 are made of foam nickel materials, the hole positions correspond to the support fins 6 one by one and are respectively welded on the inner wall surfaces of the cover plate 1 and the temperature equalizing plate 2, and a gap of the foam materials can be used for flowing of a liquid working medium. The temperature equalizing layer part consists of a cover plate 1, a temperature equalizing plate 2, supporting ribs 6, a first capillary core 4, a second capillary core 9 and a liquid working medium; the phase change layer part is composed of the bottom surface of the temperature equalizing plate 2, the phase change plate 3, the reinforcing fins 7 and a phase change working medium, and the temperature equalizing layer and the phase change layer are respectively packaged after being filled.
The heat source device is arranged on the temperature-uniforming plate 2, and heat is transferred to the phase change plate 3 through the temperature-uniforming plate 2. The rapid heat transfer is realized through the vapor-liquid phase change of the saturated liquid working medium and the capillary acting force of the first capillary core 4 and the second capillary core 9. The phase change material in the phase change plate 3 absorbs heat and then melts, and the heat is stored.
The strengthening fins 7 are designed into square columnar structures with the same size, are distributed on the metal base plate in an equidistant array mode, and are welded with the top surface of the phase change plate 3 into a whole through molecular diffusion welding. On one hand, the rib array can strengthen the mechanical property and improve the pressure resistance to 5 MPa; on one hand, the heat conduction performance of the phase-change material is enhanced, and the melting rate of the phase-change material is improved. The cover plate 1 and the first capillary core 4, the temperature-equalizing plate 2 and the second capillary core 9, the cover plate 1 and the temperature-equalizing plate 2, the temperature-equalizing plate 2 and the phase-change plate 3 are welded into a whole by adopting molecular diffusion welding, the strength reaches 90% of the strength of the base metal, the pressure resistance of the shell of the integrated device is improved, except the first capillary core 4, the second capillary core 9, the liquid material and the phase-change material, the used material is light metal with high heat conductivity coefficient, the phase-change material is paraffin, and the main molecular formula is CnH2n+2The transformation point is between 5 and 40 ℃.
Example 1: the present embodiment is a flat cube, with specific dimensions of 280mm × 280mm × 20mm, and the inside is divided into a uniform temperature layer and a phase change layer.
The temperature-equalizing layer is flat and square, the specific size is 280mm multiplied by 10mm, the wall thickness of the cover plate 1 and the bottom part is 3mm, and the depth of the inner cavity is 4 mm. The mechanical property of the temperature equalizing layer is strengthened by a matrix of supporting fins 6, the supporting fins 6 are square, and the size of each supporting fin 6 is 6mm multiplied by 6mm, the height is 4mm, and the distance is 14 mm. The material used was aluminum.
The phase change layer is flat and square, the specific size is 280mm multiplied by 10mm, the wall thickness is 3mm, the upper wall is the bottom surface of the temperature-uniforming layer, and the phase change layer and the temperature-uniforming layer are welded into a whole through diffusion welding. The phase change layer is subjected to matrix enhanced heat exchange by using enhanced fins 7, the enhanced fins 7 are square, and the size of each fin is 2mm multiplied by 2mm, the height is 7mm, and the distance is 8 mm. The material used was aluminum.
Two layers of capillary cores are arranged in the temperature equalizing layer and are respectively welded on the inner wall surfaces of the temperature equalizing plate 2 and the cover plate 1, the specific size is 280mm multiplied by 1mm, 144 through holes are uniformly distributed in the temperature equalizing layer, the diameter is 9mm, and the distance is 20 mm. The material used was nickel foam.
The liquid material of the temperature-equalizing layer in this embodiment is liquid ammonia, the molecular formula of the main component of the liquid material is NH3, and the purity of the liquid material is 99.999%.
The phase change material of the phase change layer of the embodiment is paraffin, and the molecular formula of the main component of the phase change material is CnH2n+2Such as tetradecane (melting point: 5.5 ℃ C., latent heat of fusion: 226kJ/kg), hexadecane (melting point: 16.7 ℃ C., latent heat of fusion: 237kJ/kg), octadecane (melting point: 28.0 ℃ C., latent heat of fusion: 247 kJ/kg).
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A composite phase change flat heat pipe for a satellite is characterized by comprising: the device comprises a cover plate (1), a temperature equalizing plate (2), a phase change plate (3), a first capillary core (4), a second capillary core (9), a liquid working medium and a phase change material;
apron (1) downside fixed connection temperature-uniforming plate (2), apron (1) with form first seal chamber between temperature-uniforming plate (2), temperature-uniforming plate (2) downside fixed connection phase transition board (3), temperature-uniforming plate (2) with form the seal chamber of second between phase transition board (3), the installation of first seal chamber upside first capillary core (4), the installation of first seal chamber downside second capillary core (9), the interior liquid working medium that adds of first seal chamber, the interior phase change material that adds of second seal chamber intracavity.
2. The composite phase-change flat heat pipe for the satellite as claimed in claim 1, wherein: the middle of the upper side of the temperature equalizing plate (2) is provided with a first square groove, supporting fins (6) are installed in the first square groove, and the supporting fins (6) are arranged in an array mode.
3. The composite phase-change flat heat pipe for the satellite as claimed in claim 2, wherein: the first capillary core (4) and the second capillary core (9) are provided with avoiding holes, and the avoiding holes correspond to the supporting ribs (6).
4. The composite phase-change flat heat pipe for the satellite as claimed in claim 2, wherein: the phase change plate is characterized in that a second square groove is formed in the middle of the upper side of the phase change plate (3), reinforcing ribs (7) are installed in the second square groove, and the reinforcing ribs (7) are arranged in an array mode.
5. The composite phase-change flat heat pipe for the satellite as claimed in claim 1, wherein: and a heat source device is arranged on the temperature equalizing plate (2), and mounting holes (8) are formed in the periphery of the cover plate (1).
6. The composite phase-change flat heat pipe for the satellite as claimed in claim 2, wherein: the cover plate (1) and the temperature equalizing plate (2) are welded by molecular diffusion welding, the temperature equalizing plate (2) and the phase change plate (3) are welded by molecular diffusion welding, the first capillary core (4) and the lower side of the cover plate (1) are welded by molecular diffusion welding, and the second capillary core (9) and the square groove are welded by molecular diffusion welding.
7. The composite phase-change flat heat pipe for the satellite as claimed in claim 1, wherein: the front end of the left side of the temperature equalizing plate (2) is provided with a first filling port (5), and the first filling port (5) is communicated with the first sealing chamber cavity.
8. The composite phase-change flat heat pipe for the satellite as claimed in claim 1, wherein: and a second filling port (10) is arranged at the front end of the left side of the phase change plate (3), and the second filling port (10) is communicated with the second sealing chamber cavity.
9. The composite phase-change flat heat pipe for the satellite as claimed in claim 4, wherein: the first capillary core (4) and the second capillary core (9) are made of foam nickel materials, and the cover plate (1), the temperature equalizing plate (2), the phase change plate (3), the supporting fins (6) and the reinforcing fins (7) are made of light metal with high heat conductivity coefficient.
10. The composite phase-change flat heat pipe for the satellite as claimed in claim 1, wherein: the liquid working medium comprises liquid nitrogen, and the phase-change material comprises paraffin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110269364.XA CN113074570A (en) | 2021-03-12 | 2021-03-12 | Composite phase-change flat heat pipe for satellite |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110269364.XA CN113074570A (en) | 2021-03-12 | 2021-03-12 | Composite phase-change flat heat pipe for satellite |
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| CN113074570A true CN113074570A (en) | 2021-07-06 |
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| CN202110269364.XA Pending CN113074570A (en) | 2021-03-12 | 2021-03-12 | Composite phase-change flat heat pipe for satellite |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113581493A (en) * | 2021-07-30 | 2021-11-02 | 北京微焓科技有限公司 | Plate-shaped satellite main frame and plate-shaped satellite |
| CN114537716A (en) * | 2022-01-25 | 2022-05-27 | 上海卫星工程研究所 | Dot-matrix heat source temperature consistency control method and system |
| US11976885B2 (en) | 2021-12-29 | 2024-05-07 | Industrial Technology Research Institute | Phase change thermal management device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102595861A (en) * | 2012-03-12 | 2012-07-18 | 华南理工大学 | Vapor chamber having support posts with inner-sintering structure |
| US20150285564A1 (en) * | 2014-04-03 | 2015-10-08 | Raytheon Company | Encapsulated phase change material heat sink and method |
| CN106697335A (en) * | 2016-11-29 | 2017-05-24 | 上海卫星装备研究所 | Energy storage and temperature control cooler structure for spacecraft and manufacturing method thereof |
| CN109654929A (en) * | 2019-02-27 | 2019-04-19 | 新乡市特美特热控技术股份有限公司 | A kind of high-efficiency thermal storage device and its manufacturing method |
| CN110290686A (en) * | 2019-07-24 | 2019-09-27 | 中国科学院理化技术研究所 | A kind of composite radiating system |
| WO2020123683A1 (en) * | 2018-12-12 | 2020-06-18 | Magna International Inc. | Additive manufactured heat sink |
-
2021
- 2021-03-12 CN CN202110269364.XA patent/CN113074570A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102595861A (en) * | 2012-03-12 | 2012-07-18 | 华南理工大学 | Vapor chamber having support posts with inner-sintering structure |
| US20150285564A1 (en) * | 2014-04-03 | 2015-10-08 | Raytheon Company | Encapsulated phase change material heat sink and method |
| CN106697335A (en) * | 2016-11-29 | 2017-05-24 | 上海卫星装备研究所 | Energy storage and temperature control cooler structure for spacecraft and manufacturing method thereof |
| WO2020123683A1 (en) * | 2018-12-12 | 2020-06-18 | Magna International Inc. | Additive manufactured heat sink |
| CN109654929A (en) * | 2019-02-27 | 2019-04-19 | 新乡市特美特热控技术股份有限公司 | A kind of high-efficiency thermal storage device and its manufacturing method |
| CN110290686A (en) * | 2019-07-24 | 2019-09-27 | 中国科学院理化技术研究所 | A kind of composite radiating system |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113581493A (en) * | 2021-07-30 | 2021-11-02 | 北京微焓科技有限公司 | Plate-shaped satellite main frame and plate-shaped satellite |
| US11976885B2 (en) | 2021-12-29 | 2024-05-07 | Industrial Technology Research Institute | Phase change thermal management device |
| CN114537716A (en) * | 2022-01-25 | 2022-05-27 | 上海卫星工程研究所 | Dot-matrix heat source temperature consistency control method and system |
| CN114537716B (en) * | 2022-01-25 | 2023-10-27 | 上海卫星工程研究所 | Lattice type heat source temperature consistency control method and system |
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Application publication date: 20210706 |