CN107613719B - A kind of space camera focal plane air cooling mechanism - Google Patents
A kind of space camera focal plane air cooling mechanism Download PDFInfo
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- CN107613719B CN107613719B CN201710717756.1A CN201710717756A CN107613719B CN 107613719 B CN107613719 B CN 107613719B CN 201710717756 A CN201710717756 A CN 201710717756A CN 107613719 B CN107613719 B CN 107613719B
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Abstract
The invention discloses the space camera focal plane air cooling mechanisms of a kind of good refrigeration effect, the low vibration for not influencing camera normal work, specifically include heat sink body, the heat sink body has a radiating bottom plate, and the radiating bottom plate outer surface is provided with radiating piece；Air-cooled component, the air-cooled component include inlet section and outlet section, and the inlet section and outlet section are symmetrically disposed on the both ends of the heat sink body；The inlet section includes at least two air inlets, and the outlet section includes at least two air outlets.A kind of space camera focal plane air cooling mechanism provided by the invention, can effectively improve the efficiency in space camera ground test stage, realizes the testing scheme of side working edge heat dissipation, improves the effective time of test, and the previous testing time is shortened half；Meanwhile heat dissipation effect is better than the prior art.
Description
Technical field
The present invention relates to the space camera focal plane Air coolers of space optics technical field more particularly to a kind of low vibration
Structure.
Background technique
Space camera work passes through certain thermally conductive pathways most in the outer space, the heat that focal plane electronics generates when imaging
It is radiated in the cold darkness environment of the outer space by spoke cold plate eventually, and during ground is debugged or is tested, do not have the outer space
Cold darkness environment, therefore heat can largely be accumulated and can not be exported on electronic component, caused device operating temperature excessively high and produced
Raw damage.
The heat generated for the work of effective derived space remote sensing camera ground test or when testing process, reduces electronics
The operating temperature of component improves imaging system reliability, improves signal noise ratio (snr) of image, guarantees camera imaging quality to be promoted,
Some refrigeration equipments are usually added into space camera ground testing system.Under normal conditions, for convenience, researcher can be adopted
It is dried with electric fan alignment cameras focal plane, heat is taken away by way of thermal convection.There are two types of realization sides for the mode of electric fan
Formula, the first, electric fan can be placed on precision surface plate, the blowing of alignment cameras focal plane；It second, will be small using small fan
Fan is placed on camera beside focal plane or on focal plane, the blowing of alignment cameras focal plane；
Electric fan blowing methods it is easier, but the disadvantage is that it will be evident that firstly, electric fan dry when bring gas
Stream influences to be inevitable, at this point, due to the influence of air-flow, camera is unable to image forming job；Secondly, fan is cannot to make
It is cold, take a long time to and focal plane temperature is dropped into room temperature water put down, timeliness is low.
Summary of the invention
The object of the present invention is to provide the space cameras of a kind of good refrigeration effect, the low vibration for not influencing camera normal work
Focal plane air cooling mechanism.
To achieve the goals above, the invention provides the following technical scheme:
A kind of space camera focal plane air cooling mechanism disclosed by the invention, comprising:
Heat sink body, the heat sink body has a radiating bottom plate, and the radiating bottom plate outer surface is provided with radiating piece；
Air-cooled component, the air-cooled component include inlet section and outlet section, and the inlet section and outlet section are symmetrically disposed on
The both ends of the heat sink body；
The inlet section includes at least two air inlets, and the outlet section includes at least two air outlets.
Further, the inlet section includes a mixing chamber, and the outlet section includes the cabinet with cavity, the mixing
Interior is fixed with guiding subassembly, and the air intake of the mixing chamber of inlet section is symmetrical arranged there are two air inlet, outlet section
The outlet air end of the cabinet is symmetrical arranged there are two air outlet, the inlet section by two air inlets and guiding subassembly to
Air-supply in the heat sink body, the outlet section are blown outward by the cabinet and air outlet.
Further, the guiding subassembly includes one along the horizontally disposed structural slab of chamber of the mixing chamber and right
Claim the diversion division for being fixed on the structural slab both ends；
There are two the deflectors for being arranged and offering through-hole at an angle for the diversion division tool.
Further, the radiating piece on the radiating bottom plate is heat dissipation grid, is had on the heat dissipation grid multiple parallel
The cooling fin of distribution.
Further, it is less than close to the spacing between the adjacent cooling fin at heat source far from adjacent described at heat source
The distance between cooling fin.
Further, the distance between adjacent described cooling fin is not less than 5mm.
Further, the height of the cooling fin is not more than 50mm, and the cooling fin is integrated with the radiating bottom plate
Formula structure, and formed by processing the radiating bottom plate.
Further, the height of the cooling fin is greater than 50mm, and the cooling fin is rigidly connected in the radiating bottom plate
On.
Further, the heat dissipation grid, mixing chamber, air inlet are aluminum alloy material.
In the above-mentioned technical solutions, the space camera focal plane air cooling mechanism of a kind of low vibration provided by the invention, can be with
The efficiency for effectively improving the space camera ground test stage realizes the testing scheme of side working edge heat dissipation, improves test
The previous testing time is shortened half by effective time；Meanwhile heat dissipation effect is better than the prior art.
Detailed description of the invention
In order to illustrate the technical solutions in the embodiments of the present application or in the prior art more clearly, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only one recorded in the present invention
A little embodiments are also possible to obtain other drawings based on these drawings for those of ordinary skill in the art.
Fig. 1 is a kind of structural schematic diagram of space camera focal plane air cooling mechanism provided in an embodiment of the present invention；
Fig. 2 is a kind of structural schematic diagram of the inlet section of space camera focal plane air cooling mechanism shown in FIG. 1；
Fig. 3 is a kind of schematic diagram of internal structure of the inlet section of space camera focal plane air cooling mechanism shown in FIG. 1.
Description of symbols:
1, radiating bottom plate；2, heat dissipation grid；3, air inlet；4, mixing chamber；5, air outlet；6, cabinet；7, structural slab；8, it leads
Flowing plate；9, through-hole.
Specific embodiment
In order to make those skilled in the art more fully understand technical solution of the present invention, below in conjunction with attached drawing to this hair
It is bright to be further detailed.
Ginseng is as shown in figure 1 to 3；
A kind of space camera focal plane air cooling mechanism of low vibration of the invention, comprising:
Heat sink body, heat sink body has a radiating bottom plate 1, and 1 outer surface of radiating bottom plate is provided with radiating piece；
Air-cooled component, air-cooled component include inlet section and outlet section, and inlet section and outlet section are symmetrically disposed on heat sink body
Both ends；
Inlet section includes at least two air inlets 3, and outlet section includes at least two air outlets 5.
Specifically, the invention aims to preferable refrigeration effect, for band rapid when space camera is tested
The heat generated when the focal plane work of camera is walked, and will not influence camera normal work.Fan compared to the prior art, this
A kind of air cooling mechanism of embodiment major design mainly includes heat sink body, and heat sink body is main thermal component, is had thereon
There is a radiating bottom plate 1, the radiating piece on radiating bottom plate 1 is above-mentioned thermal component, and the air-cooled component being connected to heat sink body,
It includes the inlet section and outlet section for being symmetrically disposed on the heat sink body both ends, is supplied using inlet section into heat sink body cold
Wind.Electronics work in focal plane generates big calorimetric in this way, and heat passes through on the defeated radiating bottom plate 1 to air cooling mechanism of heat pipe, at this moment
Using inlet section conveying come cold wind can with the heat of heat sink body carry out heat exchange, heat is quickly taken away.
Preferably, inlet section includes a mixing chamber 4, and outlet section includes the cabinet 6 with cavity, is fixed in mixing chamber 4
Guiding subassembly, and the air intake of the mixing chamber 4 of inlet section is symmetrical arranged there are two air inlet 3, the outlet air end of the cabinet 6 of outlet section
It is symmetrical arranged there are two air outlet 5, inlet section is blown by two air inlets 3 and guiding subassembly into heat sink body, outlet section
It is blown outward by cabinet 6 and air outlet 5.
And the cold wind come from air-cooler conveying has low frequency vibration, can affect to the camera to work, therefore,
The present embodiment devises two air inlets 3 on the mixing chamber 4 of inlet section, and utilizes mixing chamber 4 by the cold wind of low vibration frequency
Further mixing, eliminates vibration, to realize the purpose of camera working edge heat dissipation in test.
It is furthermore preferred that in the present embodiment guiding subassembly include one along mixing chamber 4 the horizontally disposed structural slab 7 of chamber, with
And it is symmetrically fixed on the diversion division at 7 both ends of structural slab；There are two be arranged at an angle and offer through-hole 9 for diversion division tool
Deflector 8.Mutually it is arranged at an angle between deflector 8, angle is needed according to the defeated of the size of mixing chamber 4 and air-cooler
Air quantity determines that final purpose is to vibrate lower, more gentle cold wind.
Preferably, the radiating piece on radiating bottom plate 1 is heat dissipation grid 2, dissipating with multiple parallelly distribute ons on heat dissipation grid 2
Backing.In addition, close to the spacing between the abutting fins at heat source be less than far between the abutting fins at heat source away from
From.But either close to heat source or far from heat source, the distance between abutting fins are not less than 5mm.
Wherein, when the height of cooling fin is not more than 50mm, which is an integral structure with radiating bottom plate 1, and leads to
Processing radiating bottom plate 1 is crossed to form.
When the height of cooling fin is greater than 50mm, which is rigidly connected on radiating bottom plate 1.Rigid connection master
The modes such as there is welding, inlays, clamps.
Preferably, heat dissipation grid 2, mixing chamber 4, air inlet 3 are aluminum alloy material in the present embodiment.
The heat dissipation grid 2, mixing chamber 4, air inlet 3 of the present embodiment have been all made of the aluminum alloy material of high heat conductance, be for
The heat transmission that quickly heat sink body is obtained is to heat dissipation grid 2, and the fastening of air inlet 3 selection is needed according to cold wind meter
It obtains, wherein the present embodiment uses φ 75mm air inlet 3, this is the standard gauge of insulating tube.It is described in above scheme
The height of cooling fin, wherein the height of cooling fin, i.e. the height needs of heat dissipation grid 2 are calculated according to heat dissipation capacity, obtain scattered
After 2 height of heat grate, connection molding mode is obtained according to description in above scheme.In addition, the radiating bottom plate 1 in the present embodiment
Play the role of transmitting heat source, support cooling fin and external interface, meanwhile, the temperature measuring point that control air-cooler opens and closes
It is mounted on the radiating bottom plate 1, in order to guarantee that temperature measurement accuracy, temperature measuring point do not use adhesive type, should use embedded.
In the above-mentioned technical solutions, the space camera focal plane air cooling mechanism of a kind of low vibration provided by the invention, can be with
The efficiency for effectively improving the space camera ground test stage realizes the testing scheme of side working edge heat dissipation, improves test
The previous testing time is shortened half by effective time；Meanwhile heat dissipation effect is better than the prior art.
It is above that certain exemplary embodiments of the invention are only described by way of explanation, undoubtedly, for ability
The those of ordinary skill in domain without departing from the spirit and scope of the present invention can be with a variety of different modes to institute
The embodiment of description is modified.Therefore, above-mentioned attached drawing and description are regarded as illustrative in nature, and should not be construed as to the present invention
The limitation of claims.
Claims (7)
1. a kind of space camera focal plane air cooling mechanism characterized by comprising
Heat sink body, the heat sink body has a radiating bottom plate (1), and the radiating bottom plate (1) outer surface is provided with heat dissipation
Part；
Air-cooled component, the air-cooled component include inlet section and outlet section, and the inlet section and outlet section are symmetrically disposed on described
The both ends of heat sink body；
The inlet section includes at least two air inlets (3), and the outlet section includes at least two air outlets (5)；
The inlet section includes a mixing chamber (4), and the outlet section includes the cabinet (6) with cavity, and the mixing chamber (4) is interior
It is fixed with guiding subassembly, and the air intake of the mixing chamber (4) of inlet section is symmetrical arranged that there are two air inlet (3), outlet sections
The outlet air end of the cabinet (6) be symmetrical arranged there are two air outlet (5), the inlet section passes through two air inlets (3)
It blows with guiding subassembly into the heat sink body, the outlet section is blown outward by the cabinet (6) and air outlet (5)；
The guiding subassembly include one along the mixing chamber (4) the horizontally disposed structural slab of chamber (7) and be symmetrically fixed on
The diversion division at structural slab (7) both ends；
There are two the deflectors (8) for being arranged and offering through-hole (9) at an angle for the diversion division tool.
2. a kind of space camera focal plane air cooling mechanism according to claim 1, which is characterized in that the radiating bottom plate
(1) radiating piece on is heat dissipation grid (2), the cooling fin with multiple parallelly distribute ons on the heat dissipation grid (2).
3. a kind of space camera focal plane air cooling mechanism according to claim 2, which is characterized in that close to the phase at heat source
Spacing between the adjacent cooling fin is less than far from the distance between the adjacent cooling fin at heat source.
4. a kind of space camera focal plane air cooling mechanism according to claim 3, which is characterized in that the adjacent cooling fin
The distance between be not less than 5mm.
5. a kind of space camera focal plane air cooling mechanism according to claim 2, which is characterized in that the height of the cooling fin
Degree is not more than 50mm, and the cooling fin is an integral structure with the radiating bottom plate, and by processing the radiating bottom plate (1)
It forms.
6. a kind of space camera focal plane air cooling mechanism according to claim 2, which is characterized in that the height of the cooling fin
Degree is greater than 50mm, and the cooling fin is rigidly connected on the radiating bottom plate (1).
7. a kind of space camera focal plane air cooling mechanism according to claim 2, which is characterized in that the heat dissipation grid
(2), mixing chamber (4), air inlet (3) are aluminum alloy material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710717756.1A CN107613719B (en) | 2017-08-21 | 2017-08-21 | A kind of space camera focal plane air cooling mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710717756.1A CN107613719B (en) | 2017-08-21 | 2017-08-21 | A kind of space camera focal plane air cooling mechanism |
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| Publication Number | Publication Date |
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| CN107613719A CN107613719A (en) | 2018-01-19 |
| CN107613719B true CN107613719B (en) | 2019-08-02 |
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| CN201710717756.1A Active CN107613719B (en) | 2017-08-21 | 2017-08-21 | A kind of space camera focal plane air cooling mechanism |
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| CN205071580U (en) * | 2015-10-10 | 2016-03-02 | 重庆港宇高科技开发有限公司 | Heat dissipation frame |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| TW200733856A (en) * | 2006-02-20 | 2007-09-01 | Sunonwealth Electr Mach Ind Co | Composite heat-dissipating module |
| CN203495978U (en) * | 2013-09-24 | 2014-03-26 | 昆山泰丰自动化技术有限公司 | Manipulator control box heat dissipation system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4635670B2 (en) * | 2005-03-23 | 2011-02-23 | 株式会社明電舎 | Cooling structure of electronic equipment unit |
| DE202006008792U1 (en) * | 2006-06-01 | 2007-10-04 | Diehl Ako Stiftung & Co. Kg | Solar inverters |
| CN101714015A (en) * | 2008-10-08 | 2010-05-26 | 英业达股份有限公司 | Shell structure of portable electronic device |
| CN101813951A (en) * | 2009-12-07 | 2010-08-25 | 中国科学院西安光学精密机械研究所 | Temperature-controllable focal plane detector mechanism |
| CN103869844A (en) * | 2014-03-10 | 2014-06-18 | 北京空间机电研究所 | Constant-temperature control device for CCDs (charge coupled devices) of spaceflight optical remote sensor |
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| CN107613719A (en) | 2018-01-19 |
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