CN107613719A - 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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- CN107613719A CN107613719A CN201710717756.1A CN201710717756A CN107613719A CN 107613719 A CN107613719 A CN 107613719A CN 201710717756 A CN201710717756 A CN 201710717756A CN 107613719 A CN107613719 A CN 107613719A
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- focal plane
- air
- cooling mechanism
- space camera
- air cooling
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Abstract
The invention discloses the space camera focal plane air cooling mechanism of a kind of good refrigeration effect, the low vibration for not influenceing camera normal work, and it specifically includes heat sink body, and 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 symmetricly set in the both ends of the heat sink body；The inlet section comprises at least two air inlets, and the outlet section comprises at least two air outlets.A kind of space camera focal plane air cooling mechanism provided by the invention, the efficiency in space camera ground test stage can be effectively improved, realize the testing scheme of side working edge radiating, improve the effective time of test, the conventional testing time is shortened into half；Meanwhile radiating effect is better than prior art.
Description
Technical field
The present invention relates to the space camera focal plane Air cooler of space optics technical field, more particularly to a kind of low vibration
Structure.
Background technology
Space camera is operated in the outer space, its focal plane electronics shooting caused by heat by certain thermally conductive pathways most
It is radiated eventually by spoke cold drawing in the cold darkness environment of the outer space, and during debugging or test on ground, do not possess the outer space
Cold darkness environment, therefore heat can largely be accumulated and can not be exported on electronic component, cause device operating temperature too high and produce
Raw damage.
For heat caused by the work of effective derived space remote sensing camera ground test or experiment process, electronics is reduced
The operating temperature of component, imaging system reliability is improved, improves signal noise ratio (snr) of image, ensure camera imaging quality so as to be lifted,
Some refrigeration plants are usually added into space camera ground testing system.Under normal circumstances, in order to which facility, researcher can adopt
Dried with electric fan alignment cameras focal plane, heat is taken away by way of thermal convection current.The mode of electric fan has two kinds of realization sides
Formula, the first, electric fan can be placed on precision surface plate, the blowing of alignment cameras focal plane；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；
The methods of electric fan blowing are easier, but shortcoming is it will be evident that first, the gas that electric fan is brought when drying
It is inevitable to flow influence, and now, due to the influence of air-flow, camera is unable to image forming job；Secondly, fan is to make
It is cold, take a long time to and focal plane temperature is dropped into room temperature water put down, it is ageing low.
The content of the invention
It is an object of the invention to provide the space camera of a kind of good refrigeration effect, the low vibration for not influenceing camera normal work
Focal plane air cooling mechanism.
To achieve these goals, the present invention provides following technical scheme：
A kind of space camera focal plane air cooling mechanism disclosed by the invention, including：
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 symmetricly set in
The both ends of the heat sink body；
The inlet section comprises at least two air inlets, and the outlet section comprises at least two air outlets.
Further, the inlet section includes a mixing chamber, and the outlet section includes the casing with cavity, the mixing
Interior is fixed with guiding subassembly, and the air intake of the mixing chamber of inlet section is symmetrically arranged with two air inlets, outlet section
The outlet air end of the casing is symmetrically arranged with two air outlets, the inlet section by two air inlets and guiding subassembly to
Blown in the heat sink body, the outlet section is outwards blown by the casing 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 to set at an angle and offer the deflector of through hole for the diversion division.
Further, the radiating piece on the radiating bottom plate is heat dissipation grid, is had on the heat dissipation grid multiple parallel
The fin of distribution.
Further, it is smaller than close between the adjacent fin at thermal source away from adjacent described at thermal source
The distance between fin.
Further, the distance between adjacent described fin is not less than 5mm.
Further, the height of the fin is not more than 50mm, and the fin is integrated with the radiating bottom plate
Formula structure, and formed by processing the radiating bottom plate.
Further, the height of the fin is more than 50mm, and the 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 in space camera ground test stage is effectively improved, the testing scheme of side working edge radiating is realized, improves test
Effective time, the conventional testing time is shortened into half；Meanwhile radiating effect is better than prior art.
Brief description of the drawings
, below will be to institute in embodiment in order to illustrate more clearly of the embodiment of the present application or technical scheme of the prior art
The accompanying drawing needed to use is briefly described, it should be apparent that, drawings in the following description are only one described in the present invention
A little embodiments, for those of ordinary skill in the art, other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is a kind of structural representation of space camera focal plane air cooling mechanism provided in an embodiment of the present invention；
Fig. 2 is a kind of structural representation of the inlet section of space camera focal plane air cooling mechanism shown in Fig. 1；
Fig. 3 is a kind of internal structure schematic diagram of the inlet section of space camera focal plane air cooling mechanism shown in Fig. 1.
Description of reference numerals：
1st, radiating bottom plate；2nd, heat dissipation grid；3rd, air inlet；4th, mixing chamber；5th, air outlet；6th, casing；7th, structural slab；8th, lead
Flowing plate；9th, through hole.
Embodiment
In order that those skilled in the art more fully understands technical scheme, below in conjunction with accompanying drawing to this hair
It is bright to be further detailed.
Referring to shown in Fig. 1-3；
A kind of space camera focal plane air cooling mechanism of low vibration of the present invention, including：
Heat sink body, heat sink body has a radiating bottom plate 1, and the outer surface of radiating bottom plate 1 is provided with radiating piece；
Air-cooled component, air-cooled component include inlet section and outlet section, and inlet section and outlet section are symmetricly set in heat sink body
Both ends；
Inlet section comprises at least two air inlets 3, and outlet section comprises at least two air outlets 4.
Specifically, the invention aims to preferable refrigeration, for the rapid band when space camera is tested
Heat caused by the focal plane work of camera is walked, and does not interfere with camera normal work.Fan in compared with prior art, this
A kind of air cooling mechanism of embodiment major design, it mainly includes heat sink body, 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 connected with heat sink body,
It includes being symmetricly set in the inlet section and outlet section at the heat sink body both ends, is supplied using inlet section into heat sink body cold
Wind.So focal plane electronics work produces big calorimetric, and heat is by the defeated radiating bottom plate 1 to air cooling mechanism of heat pipe, at this moment
Using inlet section conveying come cold wind can carry out heat exchange with the heat of heat sink body, heat is quickly taken away.
Preferably, inlet section includes a mixing chamber 4, and outlet section includes the casing 6 with cavity, is fixed with mixing chamber 4
Guiding subassembly, and the air intake of the mixing chamber 4 of inlet section is symmetrically arranged with two air inlets 3, the outlet air end of the casing 6 of outlet section
Two air outlets 5 are symmetrically arranged with, inlet section is blown by two air inlets 3 and guiding subassembly into heat sink body, outlet section
Outwards blown by casing 6 and air outlet 5.
And conveying your next cold wind from air-cooler has low frequency vibration, the camera strap to work can be given to influence, because
This, the present embodiment devises two air inlets 3 on the mixing chamber 4 of inlet section, and utilizes mixing chamber 4 by the cold of low vibration frequency
Wind further mixes, and eliminates vibration, so as to realize the purpose of camera working edge radiating 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 the both ends of structural slab 7；There are two to set at an angle and offer through hole 9 for diversion division
Deflector 8.Mutually set 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 its final purpose is to vibrate relatively low, more gentle cold wind.
Preferably, the radiating piece on radiating bottom plate 1 is heat dissipation grid 2, has dissipating for multiple parallel distributions on heat dissipation grid 2
Backing.In addition, close between the abutting fins at thermal source be smaller than away between the abutting fins at thermal source away from
From.But it is not less than 5mm either close to thermal source or away from the distance between thermal source, abutting fins.
Wherein, when the height of fin is not more than 50mm, the fin and radiating bottom plate 1 are integral type structure, and are led to
Processing radiating bottom plate 1 is crossed to form.
When the height of fin is more than 50mm, the fin is rigidly connected on radiating bottom plate 1.Rigid connection master
The mode 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 employ the aluminum alloy material of high heat conductance, be for
Quickly by the heat transmission that heat sink body obtains to heat dissipation grid 2, and the fastening of air inlet 3 selection is needed according to cold wind gauge
Draw, wherein, the present embodiment employs φ 75mm air inlets 3, and this is the standard gauge of insulating tube.Described in such scheme
The height of the height of fin, wherein fin, i.e. the highly desirable of heat dissipation grid 2 are calculated according to heat dissipation capacity, draw scattered
After the height of heat grate 2, it connects molding mode and obtained according to described in such scheme.In addition, the radiating bottom plate 1 in the present embodiment
The effect for transmitting thermal source, support fin and external interface is served, meanwhile, the temperature measuring point that control air-cooler opens and closes
On the radiating bottom plate 1, in order to ensure temperature measurement accuracy, temperature measuring point does 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 in space camera ground test stage is effectively improved, the testing scheme of side working edge radiating is realized, improves test
Effective time, the conventional testing time is shortened into half；Meanwhile radiating effect is better than prior art.
Some one exemplary embodiments of the present invention are only described by way of explanation above, 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 modes to institute
The embodiment of description is modified.Therefore, above-mentioned accompanying drawing and description are inherently illustrative, should not be construed as to the present invention
The limitation of claims.
Claims (9)
- A kind of 1. space camera focal plane air cooling mechanism, it is characterised in that including：Heat sink body, the heat sink body has a radiating bottom plate (1), and the radiating bottom plate (1) outer surface is provided with radiating Part；Air-cooled component, the air-cooled component include inlet section and outlet section, and the inlet section and outlet section are symmetricly set in described The both ends of heat sink body；The inlet section comprises at least two air inlets (3), and the outlet section comprises at least two air outlets (5).
- 2. a kind of space camera focal plane air cooling mechanism according to claim 1, it is characterised in that the inlet section includes One mixing chamber (4), the outlet section include the casing (6) with cavity, guiding subassembly are fixed with the mixing chamber (4), and The air intake of the mixing chamber (4) of inlet section is symmetrically arranged with two air inlets (3), and the casing (6) of outlet section go out Wind end is symmetrically arranged with two air outlets (5), and the inlet section is dissipated by two air inlets (3) and guiding subassembly to described Blown in hot main body, the outlet section is outwards blown by the casing (6) and air outlet (5).
- A kind of 3. space camera focal plane air cooling mechanism according to claim 2, it is characterised in that the guiding subassembly bag Include one along the mixing chamber (4) the horizontally disposed structural slab of chamber (7) and be symmetrically fixed on the structural slab (7) both ends The diversion division in portion；There are two to set at an angle and offer the deflector (8) of through hole (9) for the diversion division.
- A kind of 4. space camera focal plane air cooling mechanism according to claim 2, it is characterised in that the radiating bottom plate (1) radiating piece on is heat dissipation grid (2), has the fin of multiple parallel distributions on the heat dissipation grid (2).
- 5. a kind of space camera focal plane air cooling mechanism according to claim 4, it is characterised in that close to the phase at thermal source It is smaller than between the adjacent fin away from the distance between adjacent described fin at thermal source.
- A kind of 6. space camera focal plane air cooling mechanism according to claim 5, it is characterised in that the adjacent fin The distance between be not less than 5mm.
- A kind of 7. space camera focal plane air cooling mechanism according to claim 4, it is characterised in that the height of the fin Degree is not more than 50mm, and the fin and the radiating bottom plate are integral type structure, and by processing the radiating bottom plate (1) Form.
- A kind of 8. space camera focal plane air cooling mechanism according to claim 4, it is characterised in that the height of the fin Degree is more than 50mm, and the fin is rigidly connected on the radiating bottom plate (1).
- A kind of 9. space camera focal plane air cooling mechanism according to claim 4, it is characterised 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 true CN107613719A (en) | 2018-01-19 |
| CN107613719B CN107613719B (en) | 2019-08-02 |
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| Application Number | Title | Priority Date | Filing Date |
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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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| CN101714015A (en) * | 2008-10-08 | 2010-05-26 | 英业达股份有限公司 | Shell structure of portable electronic device |
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| JP4635670B2 (en) * | 2005-03-23 | 2011-02-23 | 株式会社明電舎 | Cooling structure of electronic equipment unit |
| 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 |
| 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 |
| CN204179076U (en) * | 2014-10-21 | 2015-02-25 | 山东鲁能智能技术有限公司 | A kind of reinforcing radiating module structure |
| 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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2017
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Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| JP4635670B2 (en) * | 2005-03-23 | 2011-02-23 | 株式会社明電舎 | Cooling structure of electronic equipment unit |
| US20070193720A1 (en) * | 2006-02-20 | 2007-08-23 | Sunonwealth Electric Machine Industry Co., Ltd. | Composite heat-dissipating module |
| 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 |
| 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 |
| 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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| 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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| CN107613719B (en) | 2019-08-02 |
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