CN112407347A - Wide-temperature-range temperature control system of aerospace ring mold equipment - Google Patents
Wide-temperature-range temperature control system of aerospace ring mold equipment Download PDFInfo
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- CN112407347A CN112407347A CN202011352925.4A CN202011352925A CN112407347A CN 112407347 A CN112407347 A CN 112407347A CN 202011352925 A CN202011352925 A CN 202011352925A CN 112407347 A CN112407347 A CN 112407347A
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- 238000010438 heat treatment Methods 0.000 claims abstract description 26
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims abstract description 24
- 238000000576 coating method Methods 0.000 claims abstract description 15
- 229910052757 nitrogen Inorganic materials 0.000 claims abstract description 12
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 8
- 239000011248 coating agent Substances 0.000 claims abstract description 8
- 229910052802 copper Inorganic materials 0.000 claims abstract description 8
- 239000010949 copper Substances 0.000 claims abstract description 8
- 239000007788 liquid Substances 0.000 claims abstract description 8
- 238000005219 brazing Methods 0.000 claims abstract description 4
- 239000010963 304 stainless steel Substances 0.000 claims description 6
- 229910000589 SAE 304 stainless steel Inorganic materials 0.000 claims description 6
- 239000004642 Polyimide Substances 0.000 claims description 4
- 229920001721 polyimide Polymers 0.000 claims description 4
- -1 polytetrafluoroethylene Polymers 0.000 claims description 4
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 4
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 4
- 230000005855 radiation Effects 0.000 description 11
- 238000001816 cooling Methods 0.000 description 10
- 238000012546 transfer Methods 0.000 description 7
- 239000000463 material Substances 0.000 description 6
- 239000000047 product Substances 0.000 description 6
- 230000000694 effects Effects 0.000 description 5
- 239000013307 optical fiber Substances 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 239000011888 foil Substances 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000012782 phase change material Substances 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 229910018487 Ni—Cr Inorganic materials 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- VNNRSPGTAMTISX-UHFFFAOYSA-N chromium nickel Chemical compound [Cr].[Ni] VNNRSPGTAMTISX-UHFFFAOYSA-N 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005485 electric heating Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005057 refrigeration Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
Abstract
The invention provides a wide temperature zone temperature control system of an aerospace ring mold device, which comprises: the heat sink comprises an inner heat sink, an outer heat sink, heating wires, a temperature control coil, a temperature control support, an inner heat sink coil and a thermal control coating; the outer heat sink, the heating wires, the temperature control coil pipe, the temperature control support and the inner heat sink coil pipe are sequentially arranged from outside to inside; the heating wire is fixed between the external heat sink and the temperature control coil through supporting structures at two ends; the temperature control coil is fixed on the temperature control supporting surface through a fastening block; the temperature control support is connected with the internal heat sink through a screw; the inner heat sink coil is welded on the outer side surface of the inner heat sink in a copper brazing mode; the internal and external heat sinks and the heating wires are fixed into a whole through an external space; and thermal control coatings are sprayed on the surfaces of the temperature control coil, the temperature control support, the inner heat sink coil and the inner and outer heat sinks. The invention can effectively solve the problem of continuous temperature control from the liquid nitrogen temperature region to the high temperature region of the aerospace ring mold equipment, and has better economical efficiency and more accurate temperature control.
Description
Technical Field
The invention relates to the technical field of temperature control, in particular to a wide-temperature-zone temperature control system of an aerospace ring mold device.
Background
The aerospace product ring model test mainly aims to verify the reliability of the product by simulating the space black and cold environment, and the aerospace ring model equipment is a main body for bearing the aerospace product ring model test. The aerospace ring mould equipment generally comprises a vacuum system, a vacuum container and a heat sink in the vacuum container, wherein the heat sink is a main part for realizing low-temperature environment and high-low temperature circulation. In order to simulate the high-low temperature alternation phenomenon of an aerospace product along with the change of a track and verify the reliability of the aerospace product, more and more aerospace environmental model equipment needs to have a wide temperature area adjusting range. For the adjustment of the temperature range from the liquid nitrogen temperature range to the high temperature (100 ℃ -200 ℃), because the temperature is wide, the heat transfer media such as conventional heat transfer oil can not meet the requirements of high temperature and low temperature at the same time, and the continuous adjustment in the temperature range is almost realized by using nitrogen as the media and using external circulation equipment such as a high pressure fan and the like in the industry at present. The temperature control system which adopts nitrogen as a heat transfer medium and uses a high-pressure fan has the reliability problems of high one-time investment, high operation and maintenance cost, large occupied area, easy leakage, easy damage of system components and the like. In order to overcome the defects existing in the conventional mode in the industry at present, a novel wide-temperature-zone temperature control system of an aerospace ring die device is provided, and the system has the characteristics of economy, compactness, reliability and accurate temperature control.
Patent document CN103557857A (application number: 201310505498.2) discloses an optical fiber gyro ring module based on a phase-change material temperature control mechanism, which includes a housing composed of an upper cover and an outer cover, an inner cover and an inner container arranged in the housing, a cavity composed of the above parts, an optical fiber loop coil and an optical fiber loop skeleton, wherein the optical fiber loop coil and the optical fiber loop skeleton are arranged in the inner container, and a phase-change material is stored in the cavity.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a wide-temperature-zone temperature control system for an aerospace ring mold device.
The wide temperature zone temperature control system of the aerospace ring mould equipment provided by the invention comprises: the heat sink comprises an inner heat sink, an outer heat sink, heating wires, a temperature control coil, a temperature control support, an inner heat sink coil and a thermal control coating;
the outer heat sink, the heating wires, the temperature control coil pipe, the temperature control support and the inner heat sink coil pipe are sequentially arranged from outside to inside;
the heating wire is fixed between the external heat sink and the temperature control coil through supporting structures at two ends;
the temperature control coil is fixed on the temperature control supporting surface through a fastening block;
the temperature control support is connected with the internal heat sink through a screw;
the inner heat sink coil is welded on the outer side surface of the inner heat sink in a copper brazing mode;
the internal and external heat sinks and the heating wires are fixed into a whole through an external space;
and thermal control coatings are sprayed on the surfaces of the temperature control coil, the temperature control support, the inner heat sink coil and the inner and outer heat sinks.
Preferably, the temperature of the internal heat sink surface is controlled between-150 ℃ and +150 ℃, and is continuously adjustable and controllable.
Preferably, the external heat sink is an expansion plate type heat sink, a coil pipe type heat sink or a rib type heat sink;
the outer heat sink is cooled by liquid nitrogen, and the surface temperature of the outer heat sink is maintained between-190 ℃ and-180 ℃ during temperature control.
Preferably, when the temperature is controlled between-150 ℃ and-100 ℃, liquid nitrogen is continuously introduced into the temperature control coil, the surface of the temperature control coil is maintained between-190 ℃ and-180 ℃, and the heat sink is cooled by arranging the supporting structure.
Preferably, the temperature control support is made of 304 stainless steel, polytetrafluoroethylene or polyimide materials according to the internal heat sink internal heat flow, temperature control precision and temperature control range.
Preferably, the surface of the external heat sink is polished, and black thermal control coatings are sprayed on the inner part of the external heat sink, the two sides of the internal heat sink and the surface of the internal heat sink coil.
Preferably, the contact surface of the temperature control support and the internal heat sink is processed into a curved surface structure conforming to the internal heat sink radian.
Preferably, the top of the temperature control support is machined into a groove conforming to the outer diameter of the temperature control coil.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention can replace the prior wide temperature zone temperature control system which takes nitrogen as a heat transfer medium and depends on an external circulating device, and can reduce the cost by more than 50 percent;
2. the external heat sink is at the liquid nitrogen temperature for a long time and has larger heat capacity, and external interference factors have smaller influence on the external heat sink temperature, so that the influence on the internal heat sink is smaller, and the external heat sink has higher stability on the whole;
3. the invention occupies a space which is obviously smaller than that of the conventional wide-temperature-zone temperature control system which takes nitrogen as a heat transfer medium and depends on an external circulating device, and can realize compact design.
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 diagram of an overall structure of a temperature controlled heat sink;
FIG. 2 is a partial cross-sectional view of a temperature controlled heat sink;
FIG. 3 is a cross-sectional view of a temperature controlled heat sink;
in the figure: 1-external heat sink; 2-internal heat sink; 3-heating wires; 4-internal heat sink coil; 5-temperature control coil pipe; 6-temperature control support.
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.
Example 1:
referring to fig. 1 to 3, the wide temperature zone temperature control system for aerospace ring mold equipment according to the present invention includes an inner heat sink 2, an outer heat sink 1, a heating wire 3, a temperature control coil 5, a temperature control support 6, an inner heat sink coil 4 and a related thermal control coating.
The theoretical basis of the invention is that the outer heat sink 1 provides a low-temperature cold background, the inner heat sink 2 is provided with a strong enough radiation cooling effect within the range of-100 ℃ to +150 ℃, the heating wire 3 heats the inner heat sink 2 through radiation heating, and the temperature of the inner heat sink 2 can be maintained at any temperature point within the temperature design range through the combined action of the radiation cooling of the outer heat sink 1 and the radiation heating of the heating wire 3. The radiation cooling and heating heat transfer mechanism is clear, and the heat transfer quantity can be accurately calculated through a mature formula, so that the refrigeration and heating effects are clear for a control system, and higher temperature control precision can be realized theoretically. Theoretical simulation finds that the temperature control accuracy of the temperature control system can reach +/-0.1 ℃.
In the range of-150 ℃ to-100 ℃, the radiation cooling effect between the inner heat sink 1 and the outer heat sink 1 is weaker because the temperature difference between the inner heat sink and the outer heat sink is smaller and the inner heat sink and the outer heat sink are both in an extremely low temperature area. In order to make up the deficiency of radiation cooling effect of the temperature zone, a temperature control coil pipe 5 is arranged on the surface of the inner heat sink 2, and liquid nitrogen is introduced into the temperature control coil pipe 5 when the temperature of the temperature zone is controlled. The temperature control coil 5 cools the inner heat sink 2 through the temperature control support 6 structure, the cooling effect is obviously better than radiation cooling, and supplement to insufficient radiation cooling is formed.
The temperature control support 6 can be made of 304 stainless steel, polytetrafluoroethylene and polyimide materials according to the difference of heat flow inside the heat sink, temperature control precision and temperature control range, and the support thickness is 50-200 mm. The contact surface of the temperature control support 6 and the inner heat sink 2 is processed into a curved surface structure which conforms to the radian of the inner heat sink 2, and the temperature control support 6 is connected with the inner heat sink 2 through a screw. The top of the temperature control support 6 is provided with a groove with the same outer diameter as the temperature control coil pipe 5, the temperature control coil pipe 5 and the temperature control support 6 are tightly connected through a pressing block, an elastic sheet and other structures, and a red copper net or an aluminum foil is filled between the two when necessary, so that an obvious gap is avoided between the two.
The external heat sink 1 can be a plate type heat sink made of stainless steel materials, and can also be a conventional copper heat sink, and the internal heat sink 2, the temperature control coil 5 and the internal heat sink 2 are made of red copper materials generally. In order to improve the temperature control performance of the temperature control system and reduce the operation cost, the radiation heat exchange between the outer heat sink 1 and the wall surface of the outer container needs to be reduced as much as possible, and the radiation heat exchange between the outer heat sink 1 and the inner heat sink 2 and between the inner heat sink 2 and a reference test piece needs to be improved. Therefore, the surface of the outer heat sink 1 needs to be polished, and the infrared emissivity of a hemisphere of the polished surface is generally lower than 0.1; black thermal control coatings are sprayed on the inner part of the outer heat sink 1, the two sides of the inner heat sink 2 and the surface of the coil pipe, and the infrared hemispherical emissivity of the coatings is generally greater than 0.88.
Example 2:
the system designed by the invention comprises an inner heat sink 2, an outer heat sink 1, a heating wire 3, a temperature control coil 5, a temperature control support 6, an inner heat sink 2 coil and a related thermal control coating.
The manufacturing method of the wide-temperature-zone temperature control system of the novel aerospace ring mold equipment comprises the following steps:
step 1: external heat sink 1 processing
The outer heat sink 1 is processed according to the design size, the outer heat sink 1 can generally adopt an expansion plate type heat sink, a coil pipe type heat sink or a rib type heat sink, and the effective radius of the outer heat sink 1 is about 150mm larger than that of the inner heat sink 2. The outer side of the external heat sink 1 can be polished chemically or manually and mechanically, the polished surface is tested by a handheld emissivity tester, and the emissivity of the infrared hemisphere is less than 0.1. The inner side of the outer heat sink 1 is sprayed with a black coating, the performance of the coating is in accordance with the relevant national military standard, TML is less than 1 percent, CVCM is less than 1 percent, and the hemispherical emissivity of the surface of the coating is greater than 0.88.
And a step 2: heating cage processing
An armored nickel-chromium heating wire 3 is adopted as an electric heating body, the diameter of the heating wire 3 is generally 1.0 mm-2.0 mm, and the material of the armored body is generally 304 stainless steel.
Step 3: internal heat sink 2 processing
The inner heat sink 2 and the related coil pipe are generally made of red copper, and the diameter of the inner heat sink 2 is processed according to the design size. The coil of the inner heat sink 2 is welded on the outer surface of the inner heat sink 2 in a brazing mode. The material of the temperature control support 6 can be 304 stainless steel, polytetrafluoroethylene or polyimide according to different heat flows and cooling rates, the temperature control support 6 made of 304 stainless steel is generally applied to heat sinks in a low-temperature control stage which need to bear larger heat flows (generally from products or built-in heating equipment) or have a rapid cooling requirement, and the support thickness is 50-200 mm. The contact surface of the temperature control support 6 and the inner heat sink 2 is processed into a curved surface structure which conforms to the radian of the inner heat sink 2, and the temperature control support 6 is connected with the inner heat sink 2 through a screw. The top of the temperature control support 6 is provided with a groove with the same outer diameter as the temperature control coil pipe 5, the temperature control coil pipe 5 and the temperature control support 6 are tightly connected through a pressing block, an elastic sheet and other structures, and a red copper net or an aluminum foil is filled between the two when necessary, so that an obvious gap is avoided between the two.
And step 4: assembly
The outer heat sink 1, the heating cage and the inner heat sink 2 are connected into a whole through flange rings at two ends.
Step 5: assembled into a ring die equipment container
The integrated heat sink is pushed inside the aerospace ring mould device, and is generally supported inside the container through an insulating support.
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.
Those skilled in the art will appreciate that, in addition to implementing the systems, apparatus, and various modules thereof provided by the present invention in purely computer readable program code, the same procedures can be implemented entirely by logically programming method steps such that the systems, apparatus, and various modules thereof are provided in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system, the device and the modules thereof provided by the present invention can be considered as a hardware component, and the modules included in the system, the device and the modules thereof for implementing various programs can also be considered as structures in the hardware component; modules for performing various functions may also be considered to be both software programs for performing the methods and structures within hardware components.
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 (8)
1. A wide temperature zone temperature control system of an aerospace ring mold device is characterized by comprising: the heat sink comprises an inner heat sink, an outer heat sink, heating wires, a temperature control coil, a temperature control support, an inner heat sink coil and a thermal control coating;
the outer heat sink, the heating wires, the temperature control coil pipe, the temperature control support and the inner heat sink coil pipe are sequentially arranged from outside to inside;
the heating wire is fixed between the external heat sink and the temperature control coil through supporting structures at two ends;
the temperature control coil is fixed on the temperature control supporting surface through a fastening block;
the temperature control support is connected with the internal heat sink through a screw;
the inner heat sink coil is welded on the outer side surface of the inner heat sink in a copper brazing mode;
the internal and external heat sinks and the heating wires are fixed into a whole through an external space;
and thermal control coatings are sprayed on the surfaces of the temperature control coil, the temperature control support, the inner heat sink coil and the inner and outer heat sinks.
2. The wide-temperature-zone temperature control system of the aerospace ring mold equipment as claimed in claim 1, wherein the temperature of the internal heat sink surface is controlled to be-150 ℃ to +150 ℃, and is continuously adjustable and controllable.
3. The wide-temperature-zone temperature control system of the aerospace ring mold device according to claim 1, wherein the external heat sink is an expansion plate type heat sink, a coil type heat sink or a rib type heat sink;
the outer heat sink is cooled by liquid nitrogen, and the surface temperature of the outer heat sink is maintained between-190 ℃ and-180 ℃ during temperature control.
4. The wide-temperature-zone temperature control system of the aerospace ring mold equipment as claimed in claim 1, wherein liquid nitrogen is continuously introduced into the temperature control coil pipe when the temperature is controlled at-150 ℃ to-100 ℃, the surface of the temperature control coil pipe is maintained at-190 ℃ to-180 ℃, and the heatsink is cooled by arranging a support structure.
5. The wide-temperature-zone temperature control system of the aerospace ring mold device according to claim 1, wherein the temperature control support is made of 304 stainless steel, polytetrafluoroethylene or polyimide according to the internal heat sink internal heat flow, temperature control precision and temperature control range.
6. The wide-temperature-zone temperature control system of the aerospace ring mold device according to claim 1, wherein the surface of the external heat sink is polished, and black thermal control coatings are sprayed on the inner part of the external heat sink, the two sides of the internal heat sink and the surface of the internal heat sink coil.
7. The wide temperature zone temperature control system of aerospace ring mold equipment as claimed in claim 1, wherein the temperature control support and the inner heat sink contact surface are processed into a curved surface structure conforming to the inner heat sink radian.
8. The wide temperature zone temperature control system of aerospace ring mold equipment as claimed in claim 1, wherein the top of the temperature control support is machined into a groove conforming to the outer diameter of the temperature control coil.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011352925.4A CN112407347A (en) | 2020-11-26 | 2020-11-26 | Wide-temperature-range temperature control system of aerospace ring mold equipment |
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| CN202011352925.4A CN112407347A (en) | 2020-11-26 | 2020-11-26 | Wide-temperature-range temperature control system of aerospace ring mold equipment |
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| CN202011352925.4A Pending CN112407347A (en) | 2020-11-26 | 2020-11-26 | Wide-temperature-range temperature control system of aerospace ring mold equipment |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114212283A (en) * | 2021-12-17 | 2022-03-22 | 重庆哈丁环境试验技术股份有限公司 | Space environment simulation test box |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201348569Y (en) * | 2008-12-29 | 2009-11-18 | 北京卫星环境工程研究所 | Space ship environment simulation test device utilizing mixed work substance refrigerating technology |
| CN101936817A (en) * | 2009-06-30 | 2011-01-05 | 富准精密工业(深圳)有限公司 | Fastening device for use in radiator performance test and method for fastening radiator with heat source |
| CN107543618A (en) * | 2016-09-05 | 2018-01-05 | 北京卫星环境工程研究所 | Circle foil radiant heat flux measurement apparatus based on fexible film thermoelectric pile |
| EP3486583A1 (en) * | 2017-11-16 | 2019-05-22 | Vaillant GmbH | Cooling circuit with leak prevention |
| CN109969434A (en) * | 2019-04-03 | 2019-07-05 | 北京卫星环境工程研究所 | The heat sink component of lift for space environment simulation |
| CN110118597A (en) * | 2019-04-26 | 2019-08-13 | 中国科学院长春光学精密机械与物理研究所 | A kind of actinometer Split hot sink structure |
-
2020
- 2020-11-26 CN CN202011352925.4A patent/CN112407347A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201348569Y (en) * | 2008-12-29 | 2009-11-18 | 北京卫星环境工程研究所 | Space ship environment simulation test device utilizing mixed work substance refrigerating technology |
| CN101936817A (en) * | 2009-06-30 | 2011-01-05 | 富准精密工业(深圳)有限公司 | Fastening device for use in radiator performance test and method for fastening radiator with heat source |
| CN107543618A (en) * | 2016-09-05 | 2018-01-05 | 北京卫星环境工程研究所 | Circle foil radiant heat flux measurement apparatus based on fexible film thermoelectric pile |
| EP3486583A1 (en) * | 2017-11-16 | 2019-05-22 | Vaillant GmbH | Cooling circuit with leak prevention |
| CN109969434A (en) * | 2019-04-03 | 2019-07-05 | 北京卫星环境工程研究所 | The heat sink component of lift for space environment simulation |
| CN110118597A (en) * | 2019-04-26 | 2019-08-13 | 中国科学院长春光学精密机械与物理研究所 | A kind of actinometer Split hot sink structure |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114212283A (en) * | 2021-12-17 | 2022-03-22 | 重庆哈丁环境试验技术股份有限公司 | Space environment simulation test box |
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