CN111796474A - Thermoelectric refrigeration focal plane device for space astronomical camera - Google Patents
Thermoelectric refrigeration focal plane device for space astronomical camera Download PDFInfo
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- CN111796474A CN111796474A CN202010489271.3A CN202010489271A CN111796474A CN 111796474 A CN111796474 A CN 111796474A CN 202010489271 A CN202010489271 A CN 202010489271A CN 111796474 A CN111796474 A CN 111796474A
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- focal plane
- ccd
- thermoelectric
- box body
- detector assembly
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- 238000005057 refrigeration Methods 0.000 title abstract description 14
- 238000001816 cooling Methods 0.000 claims abstract description 18
- 238000001514 detection method Methods 0.000 claims abstract description 18
- 230000005855 radiation Effects 0.000 claims abstract description 10
- 239000011521 glass Substances 0.000 claims abstract description 6
- 239000000463 material Substances 0.000 claims description 10
- 238000007789 sealing Methods 0.000 claims description 9
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 9
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 9
- 229910000838 Al alloy Inorganic materials 0.000 claims description 4
- 229910000881 Cu alloy Inorganic materials 0.000 claims description 4
- 229910001128 Sn alloy Inorganic materials 0.000 claims description 4
- 239000000956 alloy Substances 0.000 claims description 4
- 239000000571 coke Substances 0.000 claims description 4
- WUUZKBJEUBFVMV-UHFFFAOYSA-N copper molybdenum Chemical compound [Cu].[Mo] WUUZKBJEUBFVMV-UHFFFAOYSA-N 0.000 claims description 4
- RHZWSUVWRRXEJF-UHFFFAOYSA-N indium tin Chemical compound [In].[Sn] RHZWSUVWRRXEJF-UHFFFAOYSA-N 0.000 claims description 4
- 229910052751 metal Inorganic materials 0.000 claims description 4
- 239000002184 metal Substances 0.000 claims description 4
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 claims description 4
- 229920002379 silicone rubber Polymers 0.000 claims description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 abstract description 18
- 239000007788 liquid Substances 0.000 abstract description 9
- 229910052757 nitrogen Inorganic materials 0.000 abstract description 9
- 230000035882 stress Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 229920001971 elastomer Polymers 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
Images
Classifications
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- G—PHYSICS
- G03—PHOTOGRAPHY; CINEMATOGRAPHY; ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ELECTROGRAPHY; HOLOGRAPHY
- G03B—APPARATUS OR ARRANGEMENTS FOR TAKING PHOTOGRAPHS OR FOR PROJECTING OR VIEWING THEM; APPARATUS OR ARRANGEMENTS EMPLOYING ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ACCESSORIES THEREFOR
- G03B17/00—Details of cameras or camera bodies; Accessories therefor
- G03B17/55—Details of cameras or camera bodies; Accessories therefor with provision for heating or cooling, e.g. in aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
The invention discloses a thermoelectric refrigeration focal plane device for a space astronomical camera, and aims to solve the technical problems that a liquid nitrogen temperature control structure is complex, the size is large, the mass is large, and the deep refrigeration temperature of a CCD cannot be met. The device comprises a vacuum-sealed focal plane box body, a flexible heat pipe, a satellite radiation-cooling plate, a temperature control instrument and a detector assembly positioned in the focal plane box body; the top of the focal plane box body is provided with a glass window corresponding to the position of the detector assembly; the detector assembly comprises a detector assembly bottom plate, a lower-level thermoelectric refrigerator, a higher-level thermoelectric refrigerator and a CCD bearing sheet which are sequentially bonded from bottom to top; a main thermistor and a bare chip detection CCD comprising a CCD photosensitive area and a CCD storage area are arranged above the CCD bearing sheet; one end of the flexible heat pipe is arranged at the bottom of the outer side of the focal plane box body, and the other end of the flexible heat pipe is embedded in the satellite radiation cooling plate; the temperature controller is used for receiving the temperature signal of the main thermistor and controlling the input current of the lower-level thermoelectric refrigerator and the upper-level thermoelectric refrigerator according to the temperature signal.
Description
Technical Field
The invention relates to a space astronomical camera, in particular to a thermoelectric refrigeration focal plane device for the space astronomical camera.
Background
In order to ensure the signal-to-noise ratio and the light measurement accuracy, the space astronomical camera for detecting the dark and weak targets needs to reduce the dark current of the CCD as much as possible, and the dark current is closely related to the working temperature and the temperature control accuracy of the CCD, so that the working temperature of the CCD needs to be reduced as much as possible, and the temperature control accuracy needs to be improved. In the prior art, a liquid nitrogen temperature control structure is usually adopted, the liquid nitrogen temperature control structure is complex, large in size and large in mass, and liquid nitrogen is easy to evaporate and leak, so that the service life of the liquid nitrogen temperature control structure is short, and the application requirement of long-time astronomical observation cannot be met. And the existing liquid nitrogen temperature control structure is in a passive focal plane refrigeration mode, and the passive focal plane refrigeration mode cannot meet the requirements of CCD deep refrigeration temperature and temperature control precision.
Disclosure of Invention
The invention aims to solve the technical problems that in the prior art, the liquid nitrogen temperature control structure is complex, the size is large, the mass is large, and the liquid nitrogen is easy to evaporate and leak, so that the service life of the liquid nitrogen is short, and the application requirement of long-time astronomical observation cannot be met.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
a thermoelectric refrigeration focal plane device for a space astronomical camera is characterized in that:
the device comprises a vacuum-sealed focal plane box body, a flexible heat pipe, a satellite radiation-cooling plate, a temperature control instrument and a detector assembly positioned in the focal plane box body;
the top of the focal plane box body is provided with a glass window corresponding to the position of the detector assembly;
the detector assembly comprises a detector assembly bottom plate, a lower-level thermoelectric refrigerator, a higher-level thermoelectric refrigerator and a CCD bearing sheet which are sequentially bonded from bottom to top;
the detector assembly bottom plate is fixedly arranged at the bottom in the focal plane box body;
the lower thermoelectric refrigerator and the upper thermoelectric refrigerator are both first-stage thermoelectric refrigerators (i.e. thermoelectric refrigerators with planar structures at the cold end and the hot end), and the cold ends of the first-stage thermoelectric refrigerators and the second-stage thermoelectric refrigerators are both upward;
a main thermistor and a bare chip detection CCD comprising a CCD photosensitive area and a CCD storage area are arranged above the CCD bearing sheet;
the CCD storage area of the detection CCD is positioned right above the upper thermoelectric refrigerator, and the CCD storage area is connected with a vacuum connector embedded in the focal plane box body through a flexible cable;
one end of the flexible heat pipe is arranged at the bottom of the outer side of the focal plane box body, and the other end of the flexible heat pipe is embedded in the satellite radiation cooling plate;
the temperature controller is used for receiving the temperature signal of the main thermistor and controlling the input current of the lower-level thermoelectric refrigerator and the upper-level thermoelectric refrigerator according to the temperature signal.
Further, the flexible cable is a flexible cable with a turning radius of 4-8 mm.
Furthermore, the cold-end panel and the hot-end panel of the lower thermoelectric refrigerator and the upper thermoelectric refrigerator are both made of aluminum oxide materials.
Furthermore, the bottom plate of the detector assembly and the bottom plate of the box body of the focal plane box body are both made of molybdenum-copper alloy.
Furthermore, the CCD bearing sheet is made of silicon carbide.
Further, the device also comprises a thermistor;
the spare thermistor is arranged above the CCD bearing sheet and outputs a temperature signal to the temperature controller.
Further, the flexible cable is pressed on the CCD bearing sheet through a flexible cable pressing plate.
Furthermore, the bottom plate of the detector assembly is in threaded connection with the focal plane box body, and a gap between the bottom plate of the detector assembly and the focal plane box body is filled with silicon rubber.
Further, the flexible heat pipe is made of aluminum alloy.
Furthermore, all sealing positions on the vacuum-sealed coke-side box body are sealed by adopting metal sealing gaskets made of indium-tin alloy materials.
The invention has the beneficial effects that:
1. the thermoelectric refrigeration focal plane device for the space astronomical camera can enable the detection CCD to reach the refrigeration temperature of minus 80 ℃ and the temperature control precision of +/-1 ℃, simultaneously ensures the flatness of the detection CCD and the safety of the focal plane structure under low-temperature work, can adapt to the space launching environment, and has the characteristics of small volume, light weight and low power consumption.
2. The lower thermoelectric refrigerator and the upper thermoelectric refrigerator both adopt the first thermoelectric refrigerator, the cold end and the hot end of the first thermoelectric refrigerator are in a planar structure, and the cold end and the hot end of the first thermoelectric refrigerator are mutually overlapped and connected in series, so that the structure increases the bonding area of the detection CCD and the thermoelectric refrigerator, simultaneously reduces the stress of thermoelectric materials of the thermoelectric refrigerators in the emission mechanical environment, and improves the structural safety of the detection CCD.
3. According to the invention, silicon carbide is used as a CCD bearing sheet, the silicon carbide material has high thermal conductivity and elastic modulus, the working temperature and the temperature uniformity of the detected CCD can be ensured, the flatness under large temperature gradient of the focal plane of the detected CCD can also be ensured, and the cold end panel and the hot end panel of the lower-level thermoelectric refrigerator and the upper-level thermoelectric refrigerator are made of aluminum oxide materials, so that the thermal stress during low-temperature operation on a rail can be reduced, and the safety is improved.
4. According to the invention, the main thermistor and the standby thermistor are arranged on the silicon carbide bearing sheet, and the current of the lower-level thermoelectric refrigerator and the current of the upper-level thermoelectric refrigerator can be adjusted in real time through the temperature feedback of the main thermistor and the standby thermistor, so that the working temperature range of the detection CCD is ensured.
5. The hot end of the lower thermoelectric refrigerator is bonded on the molybdenum-copper alloy bottom plate matched with the thermal expansion coefficient of the lower thermoelectric refrigerator, and the detected heat of the CCD, the upper thermoelectric refrigerator and the lower thermoelectric refrigerator is led out to the satellite radiation plate through the aluminum alloy flexible heat pipe on the back of the bottom plate.
Drawings
FIG. 1 is a schematic diagram of a thermoelectric cooling focal plane device for a space astronomical camera according to the present invention;
FIG. 2 is a schematic structural view of a probe assembly of the present invention;
FIG. 3 is a top view of FIG. 2;
FIG. 4 is a schematic diagram of thermoelectric refrigeration coke face temperature gradients;
FIG. 5 is a schematic thermal deformation of a thermoelectric cooling coke face.
Description of the drawings:
the device comprises a detector assembly base plate 1, a detector assembly base plate 2, a lower-stage thermoelectric refrigerator, a higher-stage thermoelectric refrigerator 3, a CCD bearing plate 4, a CCD photosensitive area 5, a CCD storage area 6, a main thermistor 7, a spare thermistor 8, a flexible cable pressing plate 9, a flexible cable 10, a vacuum connector 11, a focal plane box 12, a box base plate 13, a metal sealing gasket 14, a glass window 15, a flexible heat pipe 16 and a satellite radiation cooling plate 17.
Detailed Description
To make the objects, advantages and features of the present invention more apparent, a thermoelectric cooling focal plane device for a space astronomical camera according to the present invention will be described in detail with reference to the accompanying drawings and specific embodiments. The advantages and features of the present invention will become more apparent from the following detailed description. It should be noted that: the drawings are in simplified form and are not to precise scale, the intention being solely for the convenience and clarity of illustrating embodiments of the invention; second, the structures shown in the drawings are often part of actual structures.
The invention discloses a thermoelectric refrigeration focal plane device for a space astronomical camera, which comprises a vacuum-sealed focal plane box body 12, a flexible heat pipe 16, a satellite radiation-cooling plate 17, a temperature control instrument and a detector assembly positioned in the focal plane box body 12, as shown in figure 1.
The top of the focal plane box body 12 is provided with a glass window 15 corresponding to the position of the detector assembly; all sealing positions on the vacuum-sealed coke oven face box body 12 are sealed by metal sealing gaskets 14 made of indium-tin alloy materials; the sealing gasket is made of an indium-tin alloy material instead of a rubber material, so that brittle volatilization of rubber in a low-temperature space environment is avoided, and inclination of the glass window optical element caused by deformation of the focal plane box body 12 when the sealing gasket is compressed is reduced.
As shown in fig. 2, the detector assembly includes a detector assembly bottom plate 1, a lower stage thermoelectric refrigerator 2, an upper stage thermoelectric refrigerator 3, and a CCD carrier 4, which are sequentially bonded from bottom to top.
The detector assembly bottom plate 1 is in threaded connection with the focal plane box 12, and a gap between the detector assembly bottom plate and the focal plane box is filled with silicon rubber.
The lower thermoelectric refrigerator 2 and the upper thermoelectric refrigerator 3 are both first-stage thermoelectric refrigerators, and both the cold ends of the first-stage thermoelectric refrigerators are upward, and the first-stage thermoelectric refrigerators are connected in series; the cold-end panel and the hot-end panel of the lower thermoelectric refrigerator 2 and the upper thermoelectric refrigerator 3 are both made of aluminum oxide materials. The thermal expansion coefficient of the CCD bearing sheet is similar to that of silicon carbide ceramic, and the thermal deformation of the CCD bearing sheet 4 and the thermal stress of the thermoelectric material per se can be reduced.
As shown in figure 3, a main thermistor 7, a spare thermistor 8 and a bare chip detection CCD comprising a CCD photosensitive area 5 and a CCD storage area 6 are arranged above the CCD bearing sheet 4, the detection CCD is of a non-packaging structure, the bare chips of the CCD photosensitive area 5 and the CCD storage area 6 are adhered to the CCD bearing sheet 4 made of silicon carbide materials, and heat transfer links are reduced, as shown in figures 4 and 5, the flatness and the thermal control precision of the detection CCD are guaranteed by using the silicon carbide materials with high rigidity and high thermal conductivity, the working temperature of-75 ℃ can be reached under the working power of 2W, the temperature gradient of the detection CCD is smaller than 1 ℃ by using the silicon carbide CCD bearing sheet with good force and thermal performance, the flatness of the CCD photosensitive area 5 is smaller than 7 micrometers, and the sensitivity of space astronomical dark target detection is guaranteed.
A CCD storage area 6 of the detection CCD is positioned right above the upper thermoelectric refrigerator 3, and the CCD storage area 6 is connected with a vacuum connector 11 embedded on a focal plane box body 12 through a flexible cable 10; the flexible cable 10 is fixed on the CCD bearing sheet 4 through a flexible cable pressing plate 9.
One end of the flexible heat pipe 16 is connected to the bottom of the outer side of the focal plane box body 12 through a screw on the fin, and the other end is embedded in the satellite radiation cooling plate 17; the flexible heat pipe 16 is used for guiding heat to the satellite radiation plate 17; the flexible heat pipe 16 is made of aluminum alloy, and the flexible link reduces assembly stress generated by the heat pipe due to over-constraint on one hand, and enables vibration deformation generated by the satellite radiation cooling plate 17 with a large-size thin-wall structure during launching not to be transmitted to the focal plane box body 12 on the other hand.
The temperature controller is used for reading temperature signals of the main thermistor 7 and the standby thermistor 8, controlling input currents of the lower thermoelectric refrigerator 2 and the upper thermoelectric refrigerator 3 in real time according to the temperature signals, refrigerating the detection CCD, and adopting a serial connection structure rather than a parallel connection structure, wherein a refrigerating area is the back of the CCD storage area 6, so that the shear stress on the lower thermoelectric refrigerator 2 and the upper thermoelectric refrigerator 3 during thermal deformation can be reduced, and the structural safety is improved.
Turning radius is 4 ~ 8 mm's flexible cable, preferred 5 mm's flexible cable is selected for use to flexible cable 10, and little turning radius has effectively reduced and has surveyed CCD output noise, utilizes clamp control amplitude in the department of bending simultaneously to cable vibration is to surveying CCD's influence when reducing the transmission.
The detector assembly bottom plate 1 and the box bottom plate 13 of the focal plane box 12 are both made of molybdenum-copper alloy, are matched with the thermal expansion coefficient of an alumina panel of the lower-stage thermoelectric refrigerator 2 and have good thermal conductivity.
In normal use, reasonable thermoelectric refrigerator input current and refrigeration power need to be selected, and the temperature of the hot end of the lower thermoelectric refrigerator 2 is-30 ℃, the temperature of the cold end of the upper thermoelectric refrigerator 3 is-75 ℃ and the total temperature drop of the series thermoelectric refrigerators is-45 ℃ in consideration of the heat dissipation capacity of the satellite radiation plate and the power of the detection CCD.
Claims (10)
1. A thermoelectric cooling focal plane device for a space astronomical camera, characterized in that:
the device comprises a vacuum-sealed focal plane box body (12), a flexible heat pipe (16), a satellite radiation cold plate (17), a temperature control instrument and a detector assembly positioned in the focal plane box body (12);
the top of the focal plane box body (12) is provided with a glass window (15) corresponding to the position of the detector assembly;
the detector assembly comprises a detector assembly bottom plate (1), a lower-level thermoelectric refrigerator (2), a higher-level thermoelectric refrigerator (3) and a CCD bearing sheet (4) which are sequentially bonded from bottom to top;
the detector assembly bottom plate (1) is fixedly arranged at the bottom in the focal plane box body (12);
the lower thermoelectric refrigerator (2) and the upper thermoelectric refrigerator (3) are both primary thermoelectric refrigerators, and the cold ends of the primary thermoelectric refrigerators and the secondary thermoelectric refrigerators are both upward;
a main thermistor (7) and a bare chip detection CCD (charge coupled device) comprising a CCD photosensitive area (5) and a CCD storage area (6) are arranged above the CCD bearing sheet (4);
the CCD storage area (6) of the detection CCD is positioned right above the superior thermoelectric refrigerator (3), and the CCD storage area (6) is connected with a vacuum connector (11) embedded on a focal plane box body (12) through a flexible cable (10);
one end of the flexible heat pipe (16) is arranged at the bottom of the outer side of the focal plane box body (12), and the other end of the flexible heat pipe is embedded in the satellite radiation cold plate (17);
the temperature control instrument is used for receiving a temperature signal of the main thermistor (7) and controlling input currents of the lower-level thermoelectric refrigerator (2) and the upper-level thermoelectric refrigerator (3) according to the temperature signal.
2. The thermoelectric cooling focal plane device for the space astronomical camera of claim 1, wherein:
the flexible cable (10) is a flexible cable with a turning radius of 4-8 mm.
3. A thermoelectric cooled focal plane device for a space astronomical camera according to claim 1 or 2, wherein:
the cold end panel and the hot end panel of the lower thermoelectric refrigerator (2) and the upper thermoelectric refrigerator (3) are both made of aluminum oxide materials.
4. A thermoelectric cooled focal plane device for a space astronomical camera according to claim 3, wherein: the detector assembly bottom plate (1) and the box body bottom plate (13) of the focal plane box body (12) are both made of molybdenum-copper alloy.
5. The thermoelectric cooling focal plane device for the space astronomical camera according to claim 4, wherein: the CCD bearing sheet (4) is made of silicon carbide.
6. The thermoelectric cooling focal plane device for the space astronomical camera of claim 1, wherein:
the device also comprises a thermistor (8);
the spare thermistor (8) is arranged above the CCD bearing sheet (4) and outputs a temperature signal to the temperature controller.
7. The thermoelectric cooling focal plane device for the space astronomical camera of claim 1, wherein:
the flexible cable (10) is pressed on the CCD bearing sheet (4) through a flexible cable pressing plate (9).
8. The thermoelectric cooling focal plane device for the space astronomical camera of claim 1, wherein:
the detector assembly bottom plate (1) is in threaded connection with the focal plane box body (12), and a gap between the detector assembly bottom plate and the focal plane box body is filled with silicon rubber.
9. A thermoelectric cooled focal plane device for a space astronomical camera according to claim 1, wherein: the flexible heat pipe (16) is made of aluminum alloy.
10. The thermoelectric cooling focal plane device for the space astronomical camera of claim 1, wherein: all sealing positions on the vacuum-sealed coke surface box body (12) are sealed by metal sealing gaskets (14) made of indium-tin alloy materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010489271.3A CN111796474A (en) | 2020-06-02 | 2020-06-02 | Thermoelectric refrigeration focal plane device for space astronomical camera |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010489271.3A CN111796474A (en) | 2020-06-02 | 2020-06-02 | Thermoelectric refrigeration focal plane device for space astronomical camera |
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| CN111796474A true CN111796474A (en) | 2020-10-20 |
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| CN202010489271.3A Pending CN111796474A (en) | 2020-06-02 | 2020-06-02 | Thermoelectric refrigeration focal plane device for space astronomical camera |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112422855A (en) * | 2020-10-30 | 2021-02-26 | 中国科学院西安光学精密机械研究所 | Stress-free space astronomical camera CCD assembly with small splicing height error and assembling method |
| CN113639715A (en) * | 2021-07-13 | 2021-11-12 | 中国科学院西安光学精密机械研究所 | Spliced focal plane assembly |
| CN113703257A (en) * | 2021-07-14 | 2021-11-26 | 北京空间飞行器总体设计部 | Camera CCD heat abstractor suitable for ultra-thin space |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112422855A (en) * | 2020-10-30 | 2021-02-26 | 中国科学院西安光学精密机械研究所 | Stress-free space astronomical camera CCD assembly with small splicing height error and assembling method |
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| CN113703257A (en) * | 2021-07-14 | 2021-11-26 | 北京空间飞行器总体设计部 | Camera CCD heat abstractor suitable for ultra-thin space |
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Application publication date: 20201020 |