CN110401001B - Air-cooled heat dissipation airborne antenna - Google Patents
Air-cooled heat dissipation airborne antenna Download PDFInfo
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- CN110401001B CN110401001B CN201910580687.3A CN201910580687A CN110401001B CN 110401001 B CN110401001 B CN 110401001B CN 201910580687 A CN201910580687 A CN 201910580687A CN 110401001 B CN110401001 B CN 110401001B
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/42—Housings not intimately mechanically associated with radiating elements, e.g. radome
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- 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
-
- 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
- H01Q1/285—Aircraft wire antennas
Abstract
The invention discloses an airborne air-cooled heat dissipation antenna, and aims to provide an air-cooled heat dissipation cold plate which can give consideration to two working modes of ground and flight and has high thermal conductivity. The invention is realized by the following technical scheme: the antenna body (1) is arranged on the upper surface of a rectangular strip-shaped upper partition plate (302) of the air-cooled heat dissipation cold plate (3), the upper partition plate forms a strip-shaped interlayer along the course through a lower partition plate (303) with a corresponding shape, and the strip-shaped interlayer encapsulates a bifurcated air inlet straight-out type heat dissipation functional area of the cold plate (3) in the strip-shaped interlayer. When the airplane stops on the ground, a fan (5) is started to radiate the air-cooled radiating cold plate, air flow enters from an air inlet (304) and an air outlet (305), flows through an air channel gradually, is exhausted from the air outlet of a fan cabin through a front radiating area and a rear radiating area, and is conducted away; when the airplane flies in the air, the fan is closed, high-speed flying airflow enters from the air inlet at the inclined front end of the course and is exhausted from the air outlet, and heat is conducted away by the high-speed flying airflow.
Description
Technical Field
The invention belongs to the field of heat dissipation of avionic devices, and particularly relates to an air-cooled heat dissipation cold plate of an airborne antenna.
Background
The active phased array antenna is more and more widely applied to military and civil use, because a plurality of T/R components are arranged inside the antenna, the arrangement is compact, the heat dissipation space is small, the heat flow density of the antenna is large, if the heat cannot be taken away from the antenna array surface in time, the temperature of the antenna is increased, the performance of the T/R components is reduced or even fails, and the electrical performance of the antenna is affected, so that the performance of the antenna is deteriorated. The thermal design of an active phased array antenna is therefore directly related to the electrical performance specifications of the antenna. Due to the ever-increasing heat flux density of the antenna front and the high reliability requirements, the cooling technology also faces great challenges. The existing heat design of the active phased-array antenna can adopt forced air cooling, forced liquid cooling or high-efficiency heat pipe technology and the like according to the heat flux density of an antenna array surface and the using environment of the antenna, so that the normal work of heating components such as components and the like is ensured.
According to the functional requirements of an airplane, an active phased array antenna needs to be installed on the surface of the airplane. The antenna is installed in a space enclosed by the antenna cover, the fairing and the aircraft skin. Because the working power of the antenna is high, and because the airplane cannot provide an environmental control system or a heat sink on the surface of the airplane, the antenna can only be designed by utilizing natural air cooling. In order to ensure that the antenna can work reliably for a long time, a corresponding air-cooling heat dissipation cold plate needs to be designed, and meanwhile, the antenna can work normally on the ground and in the flying process. The conventional air-cooled heat dissipation scheme of the aircraft antenna generally comprises two types of fan heat dissipation and external high-speed airflow heat dissipation directly introduced into the aircraft. The fan heat dissipation scheme adopts the fan directly to blow the antenna, in the air with heat transfer to the antenna house in, opens the draught hole at radome fairing or antenna house lateral wall simultaneously to hot-air and the outside cold air in the cover exchange, with the heat dissipation to the atmosphere in. The fan is required to work in both ground environment and high-altitude flight severe environment, and the requirement on the reliability of the fan is high. The heat dissipation scheme of directly introducing external flying high-speed airflow is that an air inlet is formed at the front end of a fairing or an antenna cover, and an air outlet is formed at the tail end of the fairing. The air inlet introduces external high-speed cold air, and the cold air takes heat away when flowing through the surface of the antenna and is exhausted from the tail end air outlet. When the airplane is stopped on the ground, the antenna cannot dissipate heat due to no high-speed airflow entering the antenna housing, the antenna is not suitable for the antenna which needs to work on the ground, and the requirement on the protection of the antenna is high due to the fact that the airflow directly blows over the antenna.
Disclosure of Invention
The invention provides an air-cooled heat dissipation airborne antenna which can give consideration to two working modes of ground and flight and has high thermal conductivity, aiming at the problems that the existing conventional airborne antenna heat dissipation scheme can not give consideration to aerial ground work, long-term reliability, protection and the like.
The above object of the present invention can be achieved by the following means: an air-cooled heat dissipating airborne antenna comprising: radome 2, radome fairing 4 and aircraft skin enclose together cover antenna body 1's enclosure to and the fan 5 of symmetric distribution in 3 both sides of cold plate, its characterized in that: the fairing 4 is connected with the radome 2 through the smooth transition of the outer wall ring of the cold plate 3; the antenna body 1 is arranged on the upper surface of a rectangular strip-shaped upper partition plate 302 of the cold plate 3, the upper partition plate 302 forms a strip-shaped interlayer along the heading direction through a lower partition plate 303 with a corresponding shape, and the strip-shaped interlayer encapsulates a branched air inlet direct outlet type heat dissipation functional area of the cold plate 3 in the strip-shaped interlayer; when the airplane stops on the ground, the fan 5 is started to radiate the air-cooled radiating cold plate 3, air flow enters from the air inlet 304 and the air outlet 305, gradually flows through an air duct 307 formed by the front radiating area 308 and the rear radiating area 309, passes through the front radiating area 308, the rear radiating area 309 and the air duct air distribution area 310, and is finally discharged from the air outlet 306 of the fan cabin, and heat is conducted away; when the airplane flies in the air, the fan 5 is closed, high-speed flying airflow enters from the air inlet 304 at the inclined front end of the heading direction, gradually flows through the air duct 307, the front heat dissipation area (308), the air duct air distribution area 310 and the rear heat dissipation area 309, and is finally exhausted from the air outlet 305, and heat is conducted away by the high-speed flying airflow.
Compared with the prior art, the invention has the following beneficial effects:
the ground and flight modes are considered. The air-cooled heat dissipation cold plate 3 is provided with the independent heat dissipation functional area, and the ground and flight working modes are considered. When the airplane is stopped on the ground, the fan 5 can be started to radiate the air-cooled radiating cold plate 3, the air flow enters from the air inlet 304 and the air outlet 305 at the same time, gradually flows through the air duct 307 formed by the front radiating area 308 and the rear radiating area 309, the air duct air dividing area 310, the air inlet 312 of the fan cabin and the fan cabin 311, and finally is exhausted from the air outlet 306 of the fan cabin to conduct away the heat. When the airplane flies in the air, the fan is turned off, high-speed flying airflow enters from the front air inlet 304, flows through the air duct 307, the front heat dissipation area 308, the air duct wind distribution area 310 and the rear heat dissipation area 309 gradually, and is finally discharged from the air outlet 305, and heat is conducted away by the high-speed flying airflow.
The reliability of the antenna is improved. The invention encapsulates the heat dissipation functional area in the strip interlayer of the air-cooled heat dissipation cold plate 3; the heat generated by the antenna is conducted to the microchannel air-cooled heat dissipation cold plate, the heat is taken away by blowing the heat dissipation functional area, the antenna is not exposed in the outside air and is not directly contacted with the severe natural environment outside, and the reliability of the antenna is improved.
The reliability of the fan is improved. The fan 5 does not work in a high-altitude severe environment, and the air inlet 312 and the air outlet 306 of the wind cabin are directional grid windows, so that high-speed flying airflow is prevented from entering the wind cabin 311 to damage the fan 5.
The thermal conductivity is high. According to the invention, the heating antenna body 1 is arranged on the upper surface of the upper partition plate 302 along the heading direction, the heat source is directly attached to the air-cooled heat dissipation cold plate, the thermal conductivity is high, the heat of the antenna body 1 can be efficiently dispersed and transferred to the air-cooled heat dissipation cold plate, and a good heat dissipation effect is obtained.
Drawings
Fig. 1 is a side cross-sectional view of an embodiment of an air-cooled heat-dissipating airborne antenna of the present invention.
FIG. 2 is a schematic view of the FIG. 1 construction with the skin removed.
Fig. 3 is a vertical sectional view of fig. 2.
In the figure: 1-antenna body, 2-antenna housing, 3-air cooling heat dissipation cold plate, 4-fairing, 5-fan, 301-outer wall ring, 302-upper partition plate, 303-lower partition plate, 304-air inlet, 305-air outlet, 306-fan cabin air outlet, 307-air channel, 308-front heat dissipation area, 309-rear heat dissipation area, 310-air channel air distribution area, 311-fan cabin and 312-fan cabin air inlet.
Detailed Description
See fig. 1-3. In embodiments described below, an air-cooled heat dissipating airborne antenna includes: antenna house 2, radome fairing 4 and aircraft skin enclose together cover 1 enclosure space of antenna body, and the fan 5 of symmetric distribution in cold drawing 3 both sides, wherein: the fairing 4 is connected with the radome 2 through the smooth transition of the outer wall ring of the cold plate 3; the antenna body 1 is arranged on the upper surface of a rectangular strip-shaped upper partition plate 302 of the cold plate 3, the upper partition plate 302 forms a strip-shaped interlayer along the heading direction through a lower partition plate 303 with a corresponding shape, and the strip-shaped interlayer encapsulates a branched air inlet direct outlet type heat dissipation functional area of the cold plate 3 in the strip-shaped interlayer; when the airplane stops on the ground, the fan 5 is started to radiate the air-cooled radiating cold plate 3, air flow enters from the air inlet 304 and the air outlet 305, gradually flows through an air duct 307 formed by the front radiating area 308 and the rear radiating area 309, passes through the front radiating area 308, the rear radiating area 309 and the air duct sub-air area 310, and is finally discharged from the air outlet 306 of the fan cabin, so that heat is conducted away; when the airplane flies in the air, the fan 5 is closed, high-speed flying airflow enters from the air inlet 304 at the inclined front end of the heading direction, gradually flows through the air duct 307, the front heat dissipation area 308, the air duct air distribution area 310 and the rear heat dissipation area 309, and is finally exhausted from the air outlet 305, and heat is conducted away by the high-speed flying airflow.
The air inlet 304 is located at the leading end of the air-cooled heat-dissipating cold plate 3. The exhaust port 305 is located at the aft end of the air-cooled cold plate 3. The front and rear heat dissipation areas 308 and 309 have heat dissipation fins parallel to the heading. The air inlet 304, the air duct 307, the air outlet 305, the front heat dissipation area 308, the air duct wind division area 310 and the rear heat dissipation area 309 form a ventilation path parallel to the heading direction.
The fan compartment air outlet 306, the air duct air distribution area 310, the fan compartment 311 and the fan compartment air inlet 312 are located at the middle end of the air-cooled heat sink cold plate. The air duct air distribution area 310, and the fan cabin 311, the fan cabin exhaust port 306 and the fan cabin air inlet 312 which are symmetrically distributed on two sides of the air duct air distribution area 310 form a ventilation path vertical to the course direction; the fan 5 is arranged in the fan cabin 311; the wind cabin air inlet 312 is used for connecting the air duct air distribution area 310 and the wind cabin 311; the nacelle air inlet 312 and the nacelle air outlet 306 are directional grid windows.
The heat dissipation functional area is divided into a front heat dissipation area 308 and a rear heat dissipation area 309 which are provided with heat dissipation fins parallel to the course direction by taking the air duct wind division area 310 as the center, so as to form a ventilation path parallel to the course direction, and the two fans 5 are distributed at two ends of the air duct wind division area 310 in a cross way. The air outlet 306 of the wind cabin, the air duct air dividing area 310 and the air inlet 312 of the wind cabin are positioned at the middle end of the air-cooled heat dissipation cold plate 3. The front heat dissipation region 308 and the rear heat dissipation region 309 arranged at positions forward and backward in the direction of the heading have heat dissipation fins parallel to the heading. Preferably, the front heat dissipation area 308 and the rear heat dissipation area 309 are an array of heat dissipation fins. The heat dissipation functional area is symmetrical about the axial plane in the air-cooled heat dissipation cold plate 3. The heat dissipation functional area includes: an air inlet 304 at the leading end of the air-cooled heat-dissipating cold plate 3, an air outlet 305 at the trailing end of the heading, and the air outlet 305 at the trailing end of the air-cooled heat-dissipating cold plate 3.
The air duct air dividing area 310, and the fan cabin 311, the fan cabin air outlet 306 and the fan cabin air inlet 312 which are symmetrically distributed on two sides of the air duct air dividing area 310 form a ventilation path vertical to the course. The fan 5 is mounted within a nacelle 311, and a nacelle inlet 312 connects the duct splitter 310 and the nacelle 311. The air inlet and air outlet of the nacelle 311 are directional grid windows. Preferably, the blower compartment air inlet 312 and the blower compartment air outlet 306 are rectangular holes in an angled back array.
See fig. 1-3. The air inlet 304 is positioned at the front end of the air-cooled heat dissipation cold plate in the direction of flight, so that foreign matters are prevented from directly entering the heat dissipation functional area in the direction right ahead of the course during flight. Preferably, the air inlet 304 is an array of circular holes, and the air outlet 305 is located at the rear end of the air-cooled heat dissipation cold plate 3. Preferably, the air inlet 304 is in the form of a V-shaped structure, and directs the obliquely entering flying high-speed airflow into a direction parallel to the heading direction.
The foregoing is directed to the preferred embodiment of the present invention and it is noted that the above-mentioned embodiments illustrate rather than limit the invention, and that those skilled in the art will be able to design alternative embodiments without departing from the scope of the appended claims. It will be apparent to those skilled in the art that various modifications and improvements can be made without departing from the spirit and substance of the invention, and these modifications and improvements are also considered to be within the scope of the invention.
Claims (10)
1. An air-cooled heat dissipating airborne antenna comprising: antenna house (2), radome fairing (4) and aircraft skin enclose together cover the enclosure space of antenna body (1) to and fan (5) of symmetric distribution in cold plate (3) both sides, its characterized in that: the radome (4) is connected with the radome (2) through smooth transition of an outer wall ring (301) of the cold plate (3), the antenna body (1) is installed on the upper surface of a rectangular strip-shaped upper partition plate (302) of the cold plate (3), the upper partition plate (302) forms a strip-shaped interlayer along the heading direction through a lower partition plate (303) in a corresponding shape, and the strip-shaped interlayer encapsulates a branched air inlet straight-out type heat dissipation functional area of the cold plate (3) in the strip-shaped interlayer; when the airplane stops on the ground, a fan (5) is started to radiate the air-cooled radiating cold plate (3), air flow enters from an air inlet (304) and an air outlet (305), flows through an air channel (307) formed by a front radiating area (308) and a rear radiating area (309) and an air channel air distribution area (310) gradually, and is finally discharged from an air outlet (306) of a fan cabin to conduct heat away; when the airplane flies in the air, the fan (5) is closed, high-speed flying airflow enters from the air inlet (304) at the inclined front end of the heading direction, flows through the air duct (307), the front heat dissipation area (308), the air duct wind distribution area (310) and the rear heat dissipation area (309) gradually, is discharged from the air outlet (305), and is conducted away by the high-speed flying airflow.
2. The air-cooled heat dissipating airborne antenna of claim 1, wherein: the heat dissipation function area comprises an air inlet (304), an air outlet (305), a fan cabin air outlet (306), an air duct (307), a front heat dissipation area (308), a rear heat dissipation area (309), an air duct air distribution area (310), a fan cabin (311) and a fan cabin air inlet (312), and the heat dissipation function area is symmetrical about the axial plane of the air cooling heat dissipation cold plate (3).
3. The air-cooled heat dissipating airborne antenna of claim 1, wherein: the heat dissipation function area is divided into a front heat dissipation area (308) and a rear heat dissipation area (309) which are provided with heat dissipation fins parallel to the course direction by taking the air duct wind division area (310) as the center, a ventilation path parallel to the course direction is formed, and the two fans (5) are distributed at two ends of the air duct wind division area (310) in a cross mode.
4. The air-cooled heat dissipating airborne antenna of claim 1, wherein: the front heat dissipation area (308) and the rear heat dissipation area (309) arranged at positions forward and backward in the direction of the heading have heat dissipation fins parallel to the heading.
5. The air-cooled heat dissipating airborne antenna of claim 1, wherein: the front heat dissipation area (308) and the rear heat dissipation area (309) are an array of heat dissipation fins.
6. The air-cooled heat dissipating airborne antenna of claim 1, wherein: the heat dissipation functional area includes: an air inlet (304) positioned at the leading end of the air-cooled heat dissipation cold plate (3) in the direction of the ship, and an air outlet (305) positioned at the tail end of the ship.
7. The air-cooled heat dissipating airborne antenna of claim 1, wherein: the air duct air distribution area (310), and the air cabin (311), the air outlet (306) of the fan cabin and the air inlet (312) of the fan cabin which are symmetrically distributed on two sides of the air duct air distribution area (310) form a ventilation path vertical to the course.
8. The air-cooled heat dissipating airborne antenna of claim 1, wherein: the fan (5) is arranged in the fan cabin (311), and an air inlet (312) of the fan cabin is connected with the air channel air distribution area (310) and the fan cabin (311).
9. The air-cooled heat dissipating airborne antenna of claim 1, wherein: the fan compartment air inlet (312) and the fan compartment air outlet (306) are directional grid windows.
10. The air-cooled heat dissipating airborne antenna of claim 1, wherein: the air duct of the air inlet (304) is in a V-shaped structure form, and guides the obliquely entering flying high-speed airflow into a direction parallel to the heading direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910580687.3A CN110401001B (en) | 2019-06-29 | 2019-06-29 | Air-cooled heat dissipation airborne antenna |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910580687.3A CN110401001B (en) | 2019-06-29 | 2019-06-29 | Air-cooled heat dissipation airborne antenna |
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| CN110401001A CN110401001A (en) | 2019-11-01 |
| CN110401001B true CN110401001B (en) | 2021-02-09 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4199247A1 (en) * | 2021-12-16 | 2023-06-21 | The Boeing Company | Thermoelectric cooling assembly and method for thermally insulating an aircraft fuselage exterior from an aircraft antennae array |
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| WO2022013322A1 (en) * | 2020-07-14 | 2022-01-20 | Satixfy Uk Limited | Air-breathing platform-mounted satcom radome |
| CN112103612B (en) * | 2020-11-02 | 2021-02-26 | 成都天锐星通科技有限公司 | Antenna for communication in motion |
| CN112310593B (en) * | 2020-12-24 | 2021-03-23 | 成都天锐星通科技有限公司 | Vehicle-mounted communication antenna |
| CN113782940B (en) * | 2021-08-31 | 2023-05-26 | 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 air-flow through type air-cooled radiating airborne antenna |
| US20230174232A1 (en) * | 2021-12-03 | 2023-06-08 | Wing Aviation Llc | Air scoop solar shield for uav |
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| KR100995082B1 (en) * | 2008-08-13 | 2010-11-18 | 한국전자통신연구원 | System for controlling the temperature of antenna module |
| JP5836604B2 (en) * | 2011-02-18 | 2015-12-24 | 三菱電機株式会社 | Module cooling structure |
| CN103188921B (en) * | 2011-12-31 | 2015-12-02 | 中国科学院电子学研究所 | A kind of heat abstractor of airborne phased array radar antenna |
| CN103717036B (en) * | 2013-03-06 | 2015-06-03 | 华为技术有限公司 | Radio remote unit (RRU) and communication device |
| DE102014002169A1 (en) * | 2014-02-19 | 2015-08-20 | Kathrein-Werke Kg | Antenna, in particular mobile radio antenna |
| CN105208830B (en) * | 2015-09-23 | 2017-08-29 | 西安电子工程研究所 | A kind of radar TR components multitube pinpoints jet air-cooled radiating device |
| CN105699946B (en) * | 2016-03-23 | 2017-10-20 | 西安电子工程研究所 | A kind of multi-layer sealed cabinet with multiple hollow taper heat dissipation wind channels |
| DE102018120053A1 (en) * | 2017-08-17 | 2019-03-28 | Hirschmann Car Communication Gmbh | Electronic device with active ventilation |
| CN108767472A (en) * | 2018-03-30 | 2018-11-06 | 彩虹无人机科技有限公司 | A kind of air-cooled radome of airborne suspension type |
| CN108598657B (en) * | 2018-04-18 | 2020-12-29 | 陕西黄河集团有限公司 | Design method and framework structure of environment control system of active phased array radar antenna |
| CN208453250U (en) * | 2018-06-22 | 2019-02-01 | 浙江华东测绘地理信息有限公司 | A kind of fixed-wing unmanned plane self-driving device with radiator structure |
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| EP4199247A1 (en) * | 2021-12-16 | 2023-06-21 | The Boeing Company | Thermoelectric cooling assembly and method for thermally insulating an aircraft fuselage exterior from an aircraft antennae array |
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