CN117080709A - Radiating device for single machine outside microwave radar antenna cabin - Google Patents
Radiating device for single machine outside microwave radar antenna cabin Download PDFInfo
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- CN117080709A CN117080709A CN202310947173.3A CN202310947173A CN117080709A CN 117080709 A CN117080709 A CN 117080709A CN 202310947173 A CN202310947173 A CN 202310947173A CN 117080709 A CN117080709 A CN 117080709A
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- heat
- heat dissipation
- microwave radar
- antenna
- radar antenna
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- 230000017525 heat dissipation Effects 0.000 claims abstract description 82
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 18
- 229910021389 graphene Inorganic materials 0.000 claims abstract description 18
- 238000000576 coating method Methods 0.000 claims abstract description 16
- 239000011248 coating agent Substances 0.000 claims abstract description 15
- 230000005855 radiation Effects 0.000 claims description 15
- 238000009413 insulation Methods 0.000 claims description 14
- 239000011152 fibreglass Substances 0.000 claims description 9
- 238000001816 cooling Methods 0.000 claims description 6
- APFVFJFRJDLVQX-UHFFFAOYSA-N indium atom Chemical compound [In] APFVFJFRJDLVQX-UHFFFAOYSA-N 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 3
- 239000003973 paint Substances 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims 3
- 229910002804 graphite Inorganic materials 0.000 claims 2
- 239000010439 graphite Substances 0.000 claims 2
- -1 graphite alkene Chemical class 0.000 claims 2
- 239000012528 membrane Substances 0.000 claims 2
- 238000005507 spraying Methods 0.000 claims 1
- 238000012360 testing method Methods 0.000 description 6
- 238000013461 design Methods 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000009833 condensation Methods 0.000 description 2
- 230000005494 condensation Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000003562 lightweight material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 229920001296 polysiloxane Polymers 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/288—Satellite antennas
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- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Details Of Aerials (AREA)
Abstract
The application provides a heat dissipation device for a single machine outside a microwave radar antenna cabin, which relates to the technical field of spacecraft heat control and comprises heat dissipation plates arranged between single machine antennas, wherein heat pipes are arranged inside the heat dissipation plates, a graphene film is arranged on an effective heat dissipation surface of the heat dissipation plates, and a heat control coating is sprayed on the outer surface of the graphene film. The heat on the single machine is firstly transferred to the heat dissipation plate, then is transferred to the effective heat dissipation surface of the heat dissipation plate through the heat pipe, and is radiated to the cold space through the graphene film, so that the heat dissipation requirement of the microwave radar antenna of the prior art after the high-power single machine moves from the cabin to the bottom of the antenna is met, and the problems that the single machine is blocked by the antenna and the heat dissipation capacity is insufficient are solved. And the whole set of device products are passive thermal control measures, the problems of starting, stopping and invalidating of the system are avoided, and the reliability is high.
Description
Technical Field
The application relates to the technical field of spacecraft thermal control, in particular to a heat dissipation device for a single machine outside a microwave radar antenna cabin.
Background
In the traditional microwave radar antenna, high-power single machines such as a transmitter and the like are all arranged in a satellite cabin, and heat dissipation of the microwave radar antenna is provided by a heat dissipation surface of the whole satellite, so that the microwave radar antenna is simpler. Due to the improvement of requirements, the precision of the microwave radar antenna is higher and the response speed requirement is higher, the high-power single machine of the microwave radar antenna at present is moved to the outside of the cabin and is directly connected with the antenna through a short waveguide, the heat dissipation condition becomes very bad while the precision and the response speed are improved, and the temperature of the single machine is increased sharply under the condition that the high-power single machine has no effective heat dissipation measure, so that the performance is reduced or even fails. Meanwhile, due to the antistatic requirement, the wave-transmitting requirement and the external heat flow condition, the antenna cannot be used as a direct heat dissipation channel.
The prior Chinese patent application document with publication number of CN114865267A discloses a phased array antenna TR component and an active phased array antenna, and relates to the technical field of active phased array thermal control so as to improve the heat dissipation efficiency of a TR module. The phased array antenna TR assembly comprises a TR module, a mounting structure, a heat pipe and cooling fins, wherein the mounting structure is arranged on one side of the TR module, an evaporation section of the heat pipe is fixed on the mounting structure, a condensation section of the heat pipe is arranged on the outer side of the mounting structure, a plurality of cooling fins are arranged on the condensation section of the heat pipe, the heat pipe transfers heat to the cooling fins, the cooling fins dissipate heat under the action of an external fan, and most of heat is brought into air to realize air cooling and heat dissipation.
The heat dissipation device in the prior art is carried out in the atmosphere environment, is difficult to adapt to the satellite-borne requirements, and at present, a high-power single-machine heat dissipation device outside a microwave radar antenna cabin capable of adapting to the satellite-borne environment is urgently needed.
Disclosure of Invention
Aiming at the defects in the prior art, the application aims to provide a heat dissipation device for a single machine outside a microwave radar antenna cabin.
The heat dissipation device for the single microwave radar antenna outside the cabin comprises heat dissipation plates arranged between the single antennas, wherein heat pipes are arranged inside the heat dissipation plates, graphene films are arranged on effective heat dissipation surfaces of the heat dissipation plates, and thermal control coatings are sprayed on the outer surfaces of the graphene films.
Preferably, the stand-alone unit is connected with the lower surface of the heat dissipation plate, and an indium foil is arranged between the stand-alone unit and the heat dissipation plate.
Preferably, the effective radiating surface of the radiating plate comprises an area on the radiating plate beyond the orthographic projection area of the antenna on the radiating plate.
Preferably, the solar absorptance of the thermal control coating is αs=0.3±0.04; the infrared emissivity of the thermal control coating is epsilon h=0.9+/-0.04; the thermal control coating comprises ACR-1g white paint.
Preferably, a glass fiber reinforced plastic heat insulation pad is arranged between the antenna and the heat dissipation plate, and a gap between the antenna and the heat dissipation plate is filled with a plurality of layers of heat insulation assemblies.
Preferably, a plurality of glass fiber reinforced plastic heat insulation pads are arranged between the antenna and the heat dissipation plate in an array mode, and the plane where the antenna is located is parallel to the upper surface of the heat dissipation plate.
Preferably, the heat pipe connects a region of the heat dissipation plate where the stand-alone unit is installed and an effective heat dissipation surface of the heat dissipation plate; the heat generated by the single machine is firstly transferred to the heat dissipation plate, then transferred to the effective heat dissipation surface of the heat dissipation plate through the heat pipe, and then radiated to the cold space through the graphene film.
Preferably, the heat dissipation plate includes a honeycomb plate.
Preferably, both the heat radiating plate and the heat pipe are made of lightweight materials.
Preferably, the on-track temperature is from-10 ℃ to 37 ℃.
Compared with the prior art, the application has the following beneficial effects:
1. according to the application, heat on the single machine is firstly transferred to the heat dissipation plate, then transferred to the effective heat dissipation surface of the heat dissipation plate through the heat pipe, and then radiated to the cold space through the graphene film, so that the heat dissipation requirement of the existing microwave radar antenna high-power single machine after moving from the cabin to the bottom of the antenna is met, and the problems that the single machine is blocked by the antenna and the heat dissipation capability is insufficient are solved.
2. The application is helpful to reduce the influence of the antenna with severe temperature change on the device and the single machine by the glass fiber reinforced plastic heat insulation pad arranged between the heat radiation plate and the antenna.
3. The application adopts light material and light design, has light overall weight and low cost, and the whole set of device products are all passive thermal control measures, so that the problems of starting, stopping and failure of the system are avoided, and the reliability is high.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a top view of an overall structure of a heat dissipating device embodying the present application;
FIG. 2 is a side view of an overall structure of a heat sink embodying the present application;
FIG. 3 is a graph of actual test temperature for a high power device embodying the present application;
fig. 4 is an actual on-track temperature curve of a high power device embodying the present application.
The figure shows: 1. a heat dissipation plate; 2. a heat pipe; 3. a graphene film; 4. a thermal control coating; 5. glass fiber reinforced plastic heat insulation pad; 6. an antenna; 7. a single machine.
Detailed Description
The present application will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present application, but are not intended to limit the application in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present application.
As shown in fig. 1 and 2, the heat dissipation device for a single machine outside a microwave radar antenna cabin provided by the application comprises a heat dissipation plate 1 arranged between 7 antennas 6 of the single machine, wherein a heat pipe 2 is arranged inside the heat dissipation plate 1, an effective heat dissipation surface of the heat dissipation plate 1 is provided with a graphene film 3, and the outer surface of the graphene film 3 is sprayed with a thermal control coating 4. The heat sink can ensure an on-track temperature of-10 ℃ to 37 ℃.
Specifically, the effective heat dissipation surface of the heat dissipation plate 1 includes an area on the heat dissipation plate 1 beyond the orthographic projection area of the antenna 6 on the heat dissipation plate 1. The heat radiation plate 1 comprises a honeycomb plate, the heat pipes 2 are arranged in the honeycomb plate, and the graphene film 3 is adhered to the effective heat radiation surface of the heat radiation plate 1, so that the heat of the single machine 7 can be transmitted to the whole heat radiation device, the problem that the single machine 7 is shielded by the antenna 6 and the heat radiation capability is insufficient can be effectively solved, and the heat radiation plate has the characteristics of high adaptability and high reliability.
More specifically, the stand-alone 7 is connected to the lower surface of the heat dissipation plate 1, and an indium foil is provided between the stand-alone 7 and the heat dissipation plate 1. The single unit 7 is operated with high heat consumption, and heat of the single unit 7 can be transferred to the heat dissipation plate 1 as soon as possible by the high-purity indium foil. The graphene film 3 is arranged on the effective radiating surface of the radiating plate 1, so that the temperature uniformity of the radiating plate 1 can be improved, and the radiating efficiency can be improved.
And a low-absorptivity high-emissivity thermal control coating 4 is sprayed on the outer surface of the graphene film for heat dissipation. The solar absorptivity of the thermal control coating 4 is αs=0.3±0.04, the infrared emissivity of the thermal control coating 4 is εh=0.9±0.04, and the thermal control coating 4 comprises ACR-1g white paint.
A glass fiber reinforced plastic heat insulation pad 5 is arranged between the antenna 6 and the heat dissipation plate 1, and a gap between the antenna 6 and the heat dissipation plate 1 is filled with a multi-layer heat insulation assembly. The glass fiber reinforced plastic heat insulation pad 5 is arranged between the antenna 6 and the heat dissipation plate 1 in an array mode, and the plane where the antenna 6 is located is parallel to the upper surface of the heat dissipation plate 1. One possible implementation is: nine glass fiber reinforced plastic heat insulation pads 5 are arranged between the heat radiation plate 1 and the antenna 6 in an array manner, and the rest gaps are filled with the multi-layer heat insulation assembly, so that heat exchange between the heat radiation plate 1 and the antenna 6 is reduced, and the influence of temperature change of the antenna 6 on the temperature of the single machine 7 is avoided. It should be further noted that the multi-layer insulation assembly of the present application is any insulation assembly suitable for use in a space-borne environment in the prior art.
Further, the heat pipe 2 connects the area of the heat dissipation plate 1 where the stand-alone 7 is installed and the effective heat dissipation surface of the heat dissipation plate 1. The heat transfer path is: the heat generated by the single machine 7 is firstly transferred to the heat radiation plate 1, then transferred to the effective heat radiation surface of the heat radiation plate 1 through the heat pipe 2, and then radiated to the cold space through the graphene film 3.
Furthermore, both the heat dissipation plate 1 and the heat pipe 2 are made of light materials, so that the overall quality of the heat dissipation device is reduced, preferably, the heat dissipation plate 1 is of a 10mm honeycomb structure, the weight of each square meter is 1.5kg, the weight of the heat pipe 2 is 0.7kg, the weight of the graphene film is 0.5kg, and the whole device is of a light design.
It should be further noted that the heat dissipating device of the present application is a passive thermal control measure, and has no problems of system start, termination and failure, and has the advantages of simple and reliable structure, simple process, easy implementation, low cost and light weight.
Based on the heat dissipation device, a test and on-orbit temperature verification are carried out on the temperature of the high-power single machine 7 of a certain satellite microwave radar antenna 6, the test simulates out-orbit heat flow through a heater, and the microwave radar antenna 6 works according to an actual working mode.
As shown in fig. 3 and fig. 4, the temperature curve of the high-power single machine 7 is shown, and it can be seen from the test results that the test temperature is kept within 35 ℃ under the condition that the high-power single machine 7 is started, and because the heat conduction silicone grease is filled between the high-power single machine 7 and the heat dissipation device, and the heat pipe 2 is pre-embedded in the heat dissipation plate 1, the effective heat dissipation surface of the honeycomb plate is stuck with the graphene film, the heat transfer of the high-power transmitter to the whole heat dissipation device is ensured, and the thermal control coating 4 with low absorptivity and high emissivity is sprayed on the surface of the graphene film, so that the heat dissipation effect of the device is ensured.
The on-orbit temperature is kept at-10 to 37 ℃ which is equivalent to the test result, and provides good guarantee for the microwave radar work.
The embodiment proves that the heat dissipation device of the microwave radar antenna 6 outdoor high-power single machine 7 has the characteristics of stable temperature control, small energy requirement, high adaptability, good reliability and flexible design.
In the description of the present application, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application.
The foregoing describes specific embodiments of the present application. It is to be understood that the application is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the application. The embodiments of the application and the features of the embodiments may be combined with each other arbitrarily without conflict.
Claims (10)
1. A heat abstractor for microwave radar antenna cabin is outer single, its characterized in that, including setting up heating panel (1) between unit (7) antenna (6), heating panel (1) inside has arranged heat pipe (2), the effective cooling surface of heating panel (1) is provided with graphite alkene membrane (3), just the surface spraying of graphite alkene membrane (3) has thermal control coating (4).
2. The heat dissipating device for a stand-alone outside a microwave radar antenna according to claim 1, wherein the stand-alone (7) is connected to the lower surface of the heat dissipating plate (1), and an indium foil is provided between the stand-alone (7) and the heat dissipating plate (1).
3. The heat sink for an off-board unit for a microwave radar antenna according to claim 1, characterized in that the effective heat dissipation surface of the heat dissipation plate (1) comprises an area of the heat dissipation plate (1) beyond the orthographic projection area of the antenna (6) on the heat dissipation plate (1).
4. The heat sink for a microwave radar antenna off-board stand-alone according to claim 1, characterized in that the solar absorptance of the thermal control coating (4) is αs = 0.3±0.04;
the infrared emissivity of the thermal control coating (4) is epsilon h=0.9+/-0.04;
the thermal control coating (4) comprises ACR-1g white paint.
5. The heat dissipation device for a microwave radar antenna single machine outside a cabin according to claim 1, wherein a glass fiber reinforced plastic heat insulation pad (5) is arranged between the antenna (6) and the heat dissipation plate (1), and a gap between the antenna (6) and the heat dissipation plate (1) is filled with a plurality of layers of heat insulation components.
6. The heat dissipating device for a microwave radar antenna single machine outside a cabin according to claim 5, wherein a plurality of glass fiber reinforced plastic heat insulating pads (5) are arranged between the antenna (6) and the heat dissipating plate (1) in an array, and the plane of the antenna (6) is parallel to the upper surface of the heat dissipating plate (1).
7. The heat dissipating device for a single microwave radar antenna module according to claim 1, wherein the heat pipe (2) connects a region of the heat dissipating plate (1) where the single microwave radar antenna module (7) is installed and an effective heat dissipating surface of the heat dissipating plate (1);
the heat generated by the single machine (7) is firstly transferred to the heat radiation plate (1), then transferred to an effective heat radiation surface of the heat radiation plate (1) through the heat pipe (2), and then radiated to a cold space through the graphene film (3).
8. A heat sink for an off-board unit for a microwave radar antenna according to claim 1, characterized in that the heat sink (1) comprises a honeycomb panel.
9. The heat dissipating device for a microwave radar antenna off-board stand-alone according to claim 1, characterized in that both the heat dissipating plate (1) and the heat pipe (2) are made of light materials.
10. The heat sink for an off-board unit for a microwave radar antenna according to claim 1, wherein the in-orbit temperature is-10 ℃ to 37 ℃.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310947173.3A CN117080709A (en) | 2023-07-28 | 2023-07-28 | Radiating device for single machine outside microwave radar antenna cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310947173.3A CN117080709A (en) | 2023-07-28 | 2023-07-28 | Radiating device for single machine outside microwave radar antenna cabin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117080709A true CN117080709A (en) | 2023-11-17 |
Family
ID=88708912
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310947173.3A Pending CN117080709A (en) | 2023-07-28 | 2023-07-28 | Radiating device for single machine outside microwave radar antenna cabin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117080709A (en) |
-
2023
- 2023-07-28 CN CN202310947173.3A patent/CN117080709A/en active Pending
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