CN115241624A - High-heat-dissipation miniaturized satellite communication antenna main bearing structure piece - Google Patents
High-heat-dissipation miniaturized satellite communication antenna main bearing structure piece Download PDFInfo
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- CN115241624A CN115241624A CN202210909133.5A CN202210909133A CN115241624A CN 115241624 A CN115241624 A CN 115241624A CN 202210909133 A CN202210909133 A CN 202210909133A CN 115241624 A CN115241624 A CN 115241624A
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- temperature
- main bearing
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- 238000004891 communication Methods 0.000 title claims abstract description 30
- 230000017525 heat dissipation Effects 0.000 claims abstract description 20
- 239000007787 solid Substances 0.000 claims abstract description 16
- 238000001816 cooling Methods 0.000 claims abstract description 15
- 239000002184 metal Substances 0.000 claims abstract description 14
- 239000002131 composite material Substances 0.000 claims abstract description 7
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 238000005516 engineering process Methods 0.000 abstract description 10
- 230000002349 favourable effect Effects 0.000 abstract 1
- 238000009434 installation Methods 0.000 description 5
- 230000010354 integration Effects 0.000 description 5
- 238000013461 design Methods 0.000 description 3
- 230000004907 flux Effects 0.000 description 3
- 238000009825 accumulation Methods 0.000 description 1
- 238000003491 array Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/02—Arrangements for de-icing; Arrangements for drying-out ; Arrangements for cooling; Arrangements for preventing corrosion
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/22—Supports; Mounting means by structural association with other equipment or articles
- H01Q1/24—Supports; Mounting means by structural association with other equipment or articles with receiving set
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
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- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
The invention discloses a high-heat-dissipation miniaturized satellite communication antenna main bearing structural member, which adopts a temperature-equalizing plate and an isolated open air-cooled composite heat dissipation structure and comprises an A-frequency transmitting antenna mounting area, an A-frequency receiving antenna mounting area and a B-frequency antenna mounting area, wherein the parts of the main bearing structural member, which correspond to the three areas, adopt temperature-equalizing plate structures, the A-frequency transmitting antenna mounting area and the A-frequency receiving antenna mounting area correspond to a first circulation chamber of the temperature-equalizing plate, and the B-frequency antenna mounting area corresponds to a second circulation chamber of the temperature-equalizing plate; the main bearing structural parts outside the first circulation chamber, the second circulation chamber and the third circulation chamber are made of solid metal plates; and an isolated open air cooling channel is arranged outside the temperature equalizing plate between the A frequency transmitting antenna mounting area and the A frequency receiving antenna mounting area and on the solid metal plate. The invention adopts the composite heat dissipation technology of the temperature equalizing plate and the isolated open air cooling, solves the problem of thermal control of the satellite communication antenna, and has the advantages of light weight, bearing capacity, quick heat dissipation, high strength and favorable severe environment resistance.
Description
Technical Field
The invention relates to a satellite communication antenna technology, in particular to a high-heat-dissipation miniaturized satellite communication antenna main bearing structural part.
Background
With the continuous development of electronic technology and antenna technology, the requirements of airborne active phased-array antennas are also higher and higher, and particularly, the stable, fast and accurate information transmission is realized on the basis of miniaturization. The active phased array satellite communication antenna is an integrated device of an electronic system, and consists of a large number of active components and equipment, the miniaturization and integration of the active components are continuously improved, the power component assembly density, the power consumption and the heat load of the active components are rapidly increased, so that the power consumption and the heat flux density of a generated array surface are rapidly increased, and a severe test is provided for a heat control technology.
For a dual-band active phased array communication antenna, the layout of the dual-band antenna needs to be completed in a limited size space, and meanwhile, in order to ensure the normal and stable operation of the antenna, high heat generated by a radio frequency part needs to be quickly led out and dissipated, so that the influence on indexes due to overhigh temperature of a device caused by heat accumulation is avoided. In the face of high heat flux density of high integrated rf components, air exchange cannot be achieved by external means alone. Therefore, a satellite communication antenna main bearing structure member which can bear load, is light, has fast heat dissipation and high strength is required to be developed so as to meet the requirements of high integration degree miniaturization and high heat dissipation.
However, no main bearing structure of the satellite communication antenna which can meet the requirements is reported at present.
Disclosure of Invention
Aiming at the defects that the electrical performance indexes of heating key components are affected by limited space when an active phased array satellite communication antenna adopts dual-band communication in the prior art, the invention aims to solve the technical problem of providing a satellite communication antenna main bearing structural member which is small in size, light in weight, high in heat dissipation and small in size.
In order to solve the technical problems, the invention adopts the technical scheme that:
the invention provides a high-heat-dissipation miniaturized satellite communication antenna main bearing structure member, which adopts a temperature-equalizing plate and an isolated open air-cooled composite heat dissipation structure and comprises an A-frequency transmitting antenna mounting area, an A-frequency receiving antenna mounting area and a B-frequency antenna mounting area, wherein the parts of the main bearing structure member corresponding to the three areas adopt temperature-equalizing plate structures, the A-frequency transmitting antenna mounting area and the A-frequency receiving antenna mounting area correspond to a first circulation chamber of the temperature-equalizing plate, the B-frequency antenna mounting area corresponds to a second circulation chamber of the temperature-equalizing plate, and the first circulation chamber and the second circulation chamber operate independently; the main bearing structural part outside the first circulating chamber and the second circulating chamber is made of a solid metal plate; and an isolated open air cooling channel is arranged outside the temperature equalizing plate between the A frequency transmitting antenna mounting area and the A frequency receiving antenna mounting area and on the solid metal plate.
The A frequency transmitting antenna mounting area, the A frequency receiving antenna mounting area and the B frequency antenna mounting area are distributed in a shape of Chinese character 'ji'.
The temperature-equalizing plates of the frequency A transmitting antenna mounting area, the frequency A receiving antenna mounting area and the frequency B antenna mounting area are provided with through holes penetrating through the temperature-equalizing plates, and the first circulating cavity and the second circulating cavity of the temperature-equalizing plates at the through holes are still sealed structures.
The isolated open air-cooled channel comprises a first fin, a second fin and a fan, wherein the first fin is arranged on a temperature-equalizing plate between an A-frequency transmitting antenna mounting area and an A-frequency receiving antenna mounting area, the second fin is arranged on a solid metal plate between the A-frequency receiving antenna mounting area and a B-frequency antenna mounting area, the first fin and the second fin are distributed in an L shape, and the fan mounting area is arranged at the position of an L-shaped inflection point; and structural plates are fixedly arranged on the upper parts of the first fins and the second fins, so that the first fins, the second fins and the fan form an L-shaped air cooling channel.
And a functional module mounting area is arranged on the structural plate above the first fin and the second fin.
And heat conducting gaskets are filled between the A frequency transmitting antenna, the A frequency receiving antenna and the B frequency antenna and the mounting surface of the temperature-equalizing plate.
The invention has the following beneficial effects and advantages:
1. the main bearing structural part provided by the invention can highly integrate the whole satellite communication antenna system, and the composite heat dissipation technology of the temperature equalizing plate and the isolated open air cooling is adopted, so that the problem of thermal control of the satellite communication antenna with high power heat consumption, high heat flow density and high integration is well solved, the weight is reduced, and the main bearing structural part has the characteristics of bearing, light weight, quick heat dissipation, high strength and the like;
2. the invention has the advantages of small volume, light weight and high heat dissipation, provides a good working temperature environment for the normal operation of satellite communication antenna equipment, and ensures that the satellite communication antenna equipment operates stably and continuously; the heat transferred to the main bearing structural part by each functional module is quickly taken away by the fan, so that the aim of quickly dissipating heat is fulfilled;
3. the isolated open air-cooled air flows through the fin air duct, the airflow does not flow through the functional module, and the cooling air duct is isolated from the equipment installation cabin, so that the electronic equipment in the antenna equipment installation cabin is isolated from the air duct, the airflow in the air duct cannot contact and damage the functional module, and the isolated open air-cooled air-conditioner has good severe environment resistance.
Drawings
FIG. 1 is a schematic view of a main bearing structure of a satellite communications antenna according to the present invention;
FIG. 2 is a schematic diagram of the layout of two chambers of the vapor chamber of the present invention;
FIG. 3 is a schematic view of the fan and fin duct layout of the present invention;
the system comprises a power module, a fan, a first circulation chamber, a second circulation chamber, a first fin, a second fin, a solid metal plate, a first frequency transmitting antenna mounting area 1, a frequency receiving antenna mounting area 2, a frequency antenna mounting area B3, a power module mounting area 4, a comprehensive control module mounting area 5, a fan mounting area 6, a first circulation chamber 7, a second circulation chamber 8, a first fin 9a, a first fin 9B and a solid metal plate 10.
Detailed Description
The structure of the invention is further explained in the following with the attached drawings.
As shown in fig. 1 to 2, the invention provides a high-heat-dissipation miniaturized satellite communication antenna main bearing structure, which adopts a temperature-equalizing plate and an isolated open air-cooled composite heat dissipation structure, and comprises an a-frequency transmitting antenna mounting area 1, an a-frequency receiving antenna mounting area 2 and a B-frequency antenna mounting area 3, wherein the parts of the main bearing structure corresponding to the three areas adopt temperature-equalizing plate structures, wherein the a-frequency transmitting antenna mounting area 1 and the a-frequency receiving antenna mounting area 2 correspond to a first circulation chamber 7 of the temperature-equalizing plate, the B-frequency antenna mounting area 3 corresponds to a second circulation chamber 8 of the temperature-equalizing plate, and the first circulation chamber 7 and the second circulation chamber 8 operate independently; the main bearing structural part outside the first circulating chamber 7 and the second circulating chamber 8 adopts a solid metal plate 10; and an isolated open air cooling channel is arranged outside the temperature equalizing plate between the A frequency transmitting antenna mounting area 1 and the A frequency receiving antenna mounting area 2 and on the solid metal plate 10.
In this embodiment, the main bearing structure member may be embedded with three functional modules, such as an antenna, a power module, and a comprehensive control module. In order to achieve the purposes that the three antenna arrays do not interfere with each other, the maximum radiation field angle can be obtained, and the layout area can be minimized, the invention designs a finished product font layout mode for the A frequency transmitting antenna mounting area 1, the A frequency receiving antenna mounting area 2 and the B frequency antenna mounting area 3. In order to make the space occupied by the airborne satellite communication antenna small and highly integrated, each module adopts a mosaic and superposition installation form, as shown in fig. 1.
The isolated open air cooling channel comprises a first fin 9a, a second fin 9B and a fan, wherein the first fin 9a is arranged on a temperature equalizing plate between the A frequency transmitting antenna mounting area 1 and the A frequency receiving antenna mounting area 2, the second fin 9B is arranged on a solid metal plate 10 between the A frequency receiving antenna mounting area 2 and the B frequency antenna mounting area 3, the first fin 9a and the second fin 9B are distributed in an L shape, and a fan mounting area 6 is arranged at the position of an inflection point of the L shape; a structural plate is fixedly mounted on the upper portions of the first fin 9a and the second fin 9b, so that the first fin 9a, the second fin 9b and the fan form an L-shaped air cooling channel, as shown in fig. 3; the component board is provided with a functional module mounting area.
The satellite communication antenna is an active phased array antenna, and the heat proportion of an antenna radio frequency component (comprising an A frequency transmitting antenna 1, an A frequency receiving antenna 2 and a B frequency antenna 3) is the largest and reaches more than 70 percent, so the satellite communication antenna is mainly considered in thermal control. According to the invention, the area for mounting the antenna radio frequency assembly is provided with the circulating chamber, the other area is of a solid structure (namely the solid metal plate 10 in the figure 2), and the fin assembly and the fan are mounted on the solid structure part, so that the design can save the cost and simplify the manufacturing process.
The thermal control design scheme of the application utilizes a temperature equalizing plate and an isolated open air cooling composite heat dissipation technology, well solves the thermal control problem of the satellite communication antenna with high power heat consumption, high heat flow density and high integration, and ensures the normal and stable work of the antenna.
Meanwhile, the frequency A transmitting antenna mounting area 1, the frequency A receiving antenna mounting area 2 and the frequency B antenna mounting area 3 are three concave areas seen on the surface of the main bearing structure, and through holes which penetrate through the temperature equalizing plate and are used for electric connection are arranged at the corresponding positions of the temperature equalizing plate; the first circulation chamber and the second circulation chamber of the temperature-equalizing plate at the through hole are still in a sealing structure.
In this embodiment, the temperature equalization plate at the through hole and the areas of the first circulation chamber 7 and the second circulation chamber 8 are well sealed by welding, and the working medium of the first circulation chamber 7 and the working medium of the second circulation chamber 8 do not leak, so that the operation safety is ensured.
And a functional module mounting area is arranged on the structural plate above the first fin and the second fin, namely the functional module mounting area comprises a power module mounting area 4 and a comprehensive control module mounting area 5.
And the other side of the main bearing structural part is also provided with a corresponding functional module, and the functional modules (including a power supply module and a comprehensive control module) at the two sides can be in direct-insert type electric connection through the through holes, so that the complexity of cable wiring is avoided.
The main bearing structural member is designed into a temperature equalizing plate form at the mounting position of a high-power antenna radio frequency assembly, the temperature equalizing plate is used for carrying out thermal control on a high heat consumption unit of the antenna assembly, and a heat conduction gasket is filled between the antenna assembly and the mounting surface of the main bearing member, so that the contact surface is increased, the heat conduction performance is improved, and the heat generated by the antenna assembly can be led out to the main bearing structural member as soon as possible.
Because the whole antenna has compact structure and small volume, partial functional modules such as a power supply module, a comprehensive control module and the like are nested and laminated, and radiating fins are designed and installed on the periphery of the module which can not radiate through a temperature equalizing plate, and the heat radiated by each module (including an antenna assembly) is transferred to the surface of a main bearing structure part and taken away by an isolated open air-cooled channel by utilizing the negative pressure action of a fan and diffused to the outside air, thereby ensuring that the antenna equipment stably and continuously normally works in a good temperature environment.
The temperature equalizing plate technology is the prior art, adopts a phase-change high-heat-conduction principle, and rapidly guides out high heat generated by the work of an antenna radio frequency assembly through a liquid-gas-liquid cold-heat conversion principle. According to the operating state of the antenna system and the distribution density of the heat source, the temperature equalization plate of the main bearing structure is designed to be 2-chamber structure, as shown in fig. 2. An independent chamber, namely a first circulation chamber 7, is arranged inside a temperature-equalizing plate corresponding to the A-frequency transmitting antenna mounting area 1 and the A-frequency receiving antenna mounting area 2 with high heat flux density, an independent chamber, namely a second circulation chamber 8, is arranged inside a temperature-equalizing plate corresponding to the B-frequency antenna mounting area, each circulation chamber operates independently, working medium circulation flow is formed rapidly, and heat is led out rapidly.
The isolated open air cooling adopts a forced convection technology, and realizes the thermal control of the antenna by utilizing an air cooling and fin integration technology. A large number of dense fin air channels are designed at the positions of the main bearing structural member where the power supply module and the comprehensive control module are installed, the two fin air channels are distributed in an L shape, and the air quantity is distributed in the fin air channels in an equivalent manner. The two fin air channels and the fan form a heat dissipation channel, so that heat transferred to the main bearing structural part by each module is quickly taken away by the fan (the fin air channels are communicated with the atmosphere and are open channels), the purpose of quickly dissipating heat is achieved, and meanwhile, the weight is also reduced.
The isolated air-cooled airflow flows through the fin air duct but does not flow through the power supply module, the comprehensive control module and other functional modules, and the cooling air duct is isolated from the equipment installation cabin (the space for installing all the functional modules except the fan on the main bearing structural member), so that the electronic equipment in the installation cabin is isolated from the air duct, and the airflow does not contact and damage the functional modules, so that the air-cooled fan has good severe environment resistance.
Claims (6)
1. The utility model provides a miniaturized satellite communication antenna owner of high heat dissipation holds structure which characterized in that: the composite heat dissipation structure comprises an A frequency transmitting antenna mounting area, an A frequency receiving antenna mounting area and a B frequency antenna mounting area, wherein the parts of a main bearing structural member corresponding to the three areas are of a temperature equalization plate structure, the A frequency transmitting antenna mounting area and the A frequency receiving antenna mounting area correspond to a first circulation chamber of the temperature equalization plate, the B frequency antenna mounting area corresponds to a second circulation chamber of the temperature equalization plate, and the first circulation chamber and the second circulation chamber operate independently; the main bearing structural part outside the first circulating chamber and the second circulating chamber is made of a solid metal plate; and an isolated open air cooling channel is arranged outside the temperature equalizing plate between the A frequency transmitting antenna mounting area and the A frequency receiving antenna mounting area and on the solid metal plate.
2. The high heat dissipation miniaturized satellite communications antenna main bearing structure of claim 1, wherein: the A frequency transmitting antenna mounting area, the A frequency receiving antenna mounting area and the B frequency antenna mounting area are distributed in a shape of Chinese character 'ji'.
3. The high heat dissipation miniaturized satellite communication antenna main bearing structure according to claim 1 or 2, characterized in that: the temperature-equalizing plates of the A frequency transmitting antenna mounting area, the A frequency receiving antenna mounting area and the B frequency antenna mounting area are provided with through holes penetrating through the temperature-equalizing plates, and the first circulating cavity and the second circulating cavity of the temperature-equalizing plates at the through holes are still sealed structures.
4. The high heat dissipation miniaturized satellite communication antenna main bearing structure of claim 1, wherein: the isolated open air-cooled channel comprises a first fin, a second fin and a fan, wherein the first fin is arranged on a temperature-equalizing plate between an A-frequency transmitting antenna mounting area and an A-frequency receiving antenna mounting area, the second fin is arranged on a solid metal plate between the A-frequency receiving antenna mounting area and a B-frequency antenna mounting area, the first fin and the second fin are distributed in an L shape, and the fan mounting area is arranged at the position of an L-shaped inflection point; and structural plates are fixedly arranged on the upper parts of the first fins and the second fins, so that the first fins, the second fins and the fan form an L-shaped air cooling channel.
5. The high heat dissipation miniaturized satellite communication antenna main bearing structure of claim 4, wherein: the functional module mounting area is arranged on the structural plate above the first fin and the second fin.
6. The high heat dissipation miniaturized satellite communications antenna main bearing structure of claim 1, wherein: and heat conducting gaskets are filled between the A frequency transmitting antenna, the A frequency receiving antenna and the B frequency antenna and the mounting surface of the temperature equalizing plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210909133.5A CN115241624B (en) | 2022-07-29 | 2022-07-29 | High-heat-dissipation miniaturized satellite communication antenna main bearing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210909133.5A CN115241624B (en) | 2022-07-29 | 2022-07-29 | High-heat-dissipation miniaturized satellite communication antenna main bearing structure |
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| CN115241624A true CN115241624A (en) | 2022-10-25 |
| CN115241624B CN115241624B (en) | 2023-07-04 |
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009072732A1 (en) * | 2007-12-07 | 2009-06-11 | Electronics And Telecommunications Research Institute | Antenna system for mobile vehicles |
| US20150048978A1 (en) * | 2013-08-14 | 2015-02-19 | The Directv Group, Inc. | Antenna systems for wireless devices |
| CN109076720A (en) * | 2016-11-25 | 2018-12-21 | 华为技术有限公司 | Heat sink, radiator and electronic equipment |
| JP2019198009A (en) * | 2018-05-10 | 2019-11-14 | 三菱電機株式会社 | Antenna device |
| CN110632561A (en) * | 2019-09-28 | 2019-12-31 | 西安电子工程研究所 | Thermal control structure of airborne radar radio frequency unit |
| CN112638131A (en) * | 2020-12-25 | 2021-04-09 | 西安电子工程研究所 | Unmanned aerial vehicle carries radar heat radiation structure |
| US20210359389A1 (en) * | 2020-05-15 | 2021-11-18 | University Of South Carolina | Heat Dissipating Antenna Structures |
| CN113782940A (en) * | 2021-08-31 | 2021-12-10 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | High-speed airflow through type air-cooling heat dissipation airborne antenna |
| CN113917403A (en) * | 2021-09-30 | 2022-01-11 | 中国船舶重工集团公司第七二四研究所 | Blade type receiving and dispatching assembly with efficient heat dissipation device |
-
2022
- 2022-07-29 CN CN202210909133.5A patent/CN115241624B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009072732A1 (en) * | 2007-12-07 | 2009-06-11 | Electronics And Telecommunications Research Institute | Antenna system for mobile vehicles |
| US20150048978A1 (en) * | 2013-08-14 | 2015-02-19 | The Directv Group, Inc. | Antenna systems for wireless devices |
| CN109076720A (en) * | 2016-11-25 | 2018-12-21 | 华为技术有限公司 | Heat sink, radiator and electronic equipment |
| JP2019198009A (en) * | 2018-05-10 | 2019-11-14 | 三菱電機株式会社 | Antenna device |
| CN110632561A (en) * | 2019-09-28 | 2019-12-31 | 西安电子工程研究所 | Thermal control structure of airborne radar radio frequency unit |
| US20210359389A1 (en) * | 2020-05-15 | 2021-11-18 | University Of South Carolina | Heat Dissipating Antenna Structures |
| CN112638131A (en) * | 2020-12-25 | 2021-04-09 | 西安电子工程研究所 | Unmanned aerial vehicle carries radar heat radiation structure |
| CN113782940A (en) * | 2021-08-31 | 2021-12-10 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | High-speed airflow through type air-cooling heat dissipation airborne antenna |
| CN113917403A (en) * | 2021-09-30 | 2022-01-11 | 中国船舶重工集团公司第七二四研究所 | Blade type receiving and dispatching assembly with efficient heat dissipation device |
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|---|---|
| CN115241624B (en) | 2023-07-04 |
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Effective date of registration: 20231009 Address after: Building D, 201 Wenchang East Road, Ecological Science and Technology New City, Yangzhou City, Jiangsu Province, 225000 Patentee after: Yangzhou Sairui Avionics Technology Co.,Ltd. Address before: Thavorn street in Huanggu District of Shenyang city of Liaoning Province, No. 40 110035 Patentee before: SHENYANG HANGSHENG TECHNOLOGY Co.,Ltd. |