CN114735252A - Deep low-temperature heat dissipation system based on earth screen shielding - Google Patents
Deep low-temperature heat dissipation system based on earth screen shielding Download PDFInfo
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- CN114735252A CN114735252A CN202210400111.6A CN202210400111A CN114735252A CN 114735252 A CN114735252 A CN 114735252A CN 202210400111 A CN202210400111 A CN 202210400111A CN 114735252 A CN114735252 A CN 114735252A
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- 230000017525 heat dissipation Effects 0.000 title claims abstract description 26
- 230000003287 optical effect Effects 0.000 claims abstract description 74
- 230000005855 radiation Effects 0.000 claims abstract description 55
- 230000006641 stabilisation Effects 0.000 claims abstract 2
- 238000011105 stabilization Methods 0.000 claims abstract 2
- 238000003825 pressing Methods 0.000 claims description 17
- 229910002804 graphite Inorganic materials 0.000 claims description 13
- 239000010439 graphite Substances 0.000 claims description 13
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 12
- 238000001816 cooling Methods 0.000 claims description 8
- 229910052738 indium Inorganic materials 0.000 claims description 8
- 239000004642 Polyimide Substances 0.000 claims description 7
- APFVFJFRJDLVQX-UHFFFAOYSA-N indium atom Chemical compound [In] APFVFJFRJDLVQX-UHFFFAOYSA-N 0.000 claims description 7
- 229920001721 polyimide Polymers 0.000 claims description 7
- 238000009413 insulation Methods 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 5
- 239000004593 Epoxy Substances 0.000 claims description 3
- 230000000903 blocking effect Effects 0.000 claims description 2
- 239000011152 fibreglass Substances 0.000 claims description 2
- 230000005540 biological transmission Effects 0.000 claims 1
- 230000007613 environmental effect Effects 0.000 abstract description 2
- 238000005057 refrigeration Methods 0.000 description 5
- 238000001514 detection method Methods 0.000 description 3
- 239000002360 explosive Substances 0.000 description 3
- 230000000977 initiatory effect Effects 0.000 description 3
- 239000000956 alloy Substances 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000035945 sensitivity Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005422 blasting Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
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- 238000010292 electrical insulation Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 238000003384 imaging method Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/1021—Earth observation satellites
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/1021—Earth observation satellites
- B64G1/1028—Earth observation satellites using optical means for mapping, surveying or detection, e.g. of intelligence
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
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- General Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
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- Biodiversity & Conservation Biology (AREA)
- Environmental & Geological Engineering (AREA)
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Abstract
The invention provides a deep low-temperature heat dissipation system based on an earth screen. Including the satellite platform who bears the camera, the optical system radiation board of control temperature and shelter from the earth screen of heat current, the earth screen with satellite platform and camera frame are articulated, the earth screen constructs to fold in on the optical system radiation board when launching, and the on-orbit expansion keeps camera job stabilization with sheltering from the heat current. The deep low-temperature heat dissipation system based on earth screen shielding further reduces the environmental temperature of the optical system.
Description
Technical Field
The present invention relates generally to the field of aerospace, and more particularly to the field of cryogenic heat dissipation systems for satellite platform cameras.
Background
The long-wave infrared camera is mainly used for high-precision detection of the surface temperature of an object and has a large number of applications in military and civil fields. Considering the instrument background radiation of the long-wave infrared camera, the optical system generally needs to adopt a deep low temperature design to restrain the instrument background of the system and improve the detection sensitivity. The conventional thermal control design of the long-wave infrared camera generally adopts an optical system radiation plate for passive refrigeration to achieve the aim of reducing the temperature of the optical system, and the requirement of the detection sensitivity index is continuously improved, so that the requirement of the optical system on the deep low temperature cannot be met by simply depending on the optical system radiation plate for refrigeration.
In reducing external heat radiation, the prior art generally adopts a radiation radiator arranged outside the radiation plate to reduce the "sunny side" so as to reduce the influence of heat radiation. Because space is limited when the satellite is launched, the traditional radiation radiator has large expansion area, and the cost of the satellite launching can be increased.
In the aspect of heat conduction and dissipation of a radiation plate of an optical system, in the prior art, a direct-bonding design is generally adopted between the optical heat dissipation system and the optical system. When a camera on a satellite is in orbit or is in a vacuum test, the thermal deformation of the cold box made of the aluminum alloy material and the lens cone made of the titanium alloy material is inconsistent in a large temperature difference environment, the pressure borne by the lens cone can be increased, and the influence on the image quality is generated.
In terms of the overall design of the satellite camera system, the prior art generally adopts direct screw connection between the optical system radiation plate and the satellite platform frame. However, this leads to heat leakage by conduction of the radiation plate of the optical system, which increases the refrigeration loss of the optical system.
Disclosure of Invention
The method aims at solving the problems of reducing heat flow radiation, heat dissipation and cold loss of a satellite camera system. The invention aims to provide a deep low-temperature heat dissipation system based on earth screen shielding, and further reduce the environmental temperature of an optical system.
The invention aims to provide a deep low-temperature heat dissipation system based on earth screen shielding, which comprises a satellite platform for bearing a camera, an optical system radiation plate for controlling temperature and an earth screen for shielding heat flow, wherein the earth screen is hinged with the satellite platform and a camera frame, and the earth screen can be folded on the optical system radiation plate during emission and unfolded in orbit to shield the heat flow to keep the camera stable in work.
Further, dark low temperature cooling system based on earth screen shelters from, wherein, the satellite platform includes the frame, the optical system radiation plate with the frame is connected through thermal-insulated support, thermal-insulated support is epoxy glass steel material, is used for reducing the optical system radiation plate with frame conduction heat leak.
Further, dark low temperature cooling system based on earth screen shelters from, wherein, the earth screen includes first side front of a garment and second side front of a garment, the edge relative position of earth screen forms earth screen first edge portion and earth screen second edge portion, first side front of a garment sets up the first edge portion of earth screen at the earth screen, second side front of a garment sets up the earth screen second edge portion at the earth screen, first side front of a garment with second side front of a garment sets up relatively, forms the shade with the earth screen jointly for block outer heat flow radiation.
Further, the deep low temperature heat dissipation system based on earth screen shielding is characterized in that the first side flap comprises a first side flap first edge portion, a first side flap second edge portion and a first side flap third edge portion, the second side flap comprises a second side flap first edge portion, a second side flap second edge portion and a second side flap third edge portion, the edge relative positions of the optical system radiation plates form an optical system radiation plate first edge portion and an optical system radiation plate second edge portion, the first side flap first edge portion is arranged on the earth screen first edge portion, the first side flap second edge portion is arranged on the optical system radiation plate first edge portion, the first side flap third edge portion, the first side flap first edge portion and the first side flap second edge portion jointly enclose a triangular plane, and the second side flap first edge portion is arranged on the earth screen second edge portion, the second edge portion of the second side flap is arranged on the second edge portion of the optical system radiation plate, and a triangular plane is defined by the third edge portion of the second side flap, the first edge portion of the second side flap and the second edge portion of the second side flap.
Further, the deep low-temperature heat dissipation system based on earth screen shielding is characterized in that a compressing and releasing device is arranged on the earth screen, a digging hole corresponding to the compressing and releasing device is formed in the earth screen, and the digging hole is used for accommodating the compressing and releasing device.
Further, the deep low temperature heat dissipation system based on earth screen shielding is characterized in that an initiating explosive cutter is arranged on the compressing and releasing device, and the initiating explosive cutter performs initiating explosive blasting to cut the compressing and releasing device so as to release the earth screen.
Further, dark low temperature cooling system based on earth screen shelters from, wherein, satellite platform's camera is including being used for the radiating cold box of optical system and lens cone, the lens cone sets up in the cold box, the lens cone is provided with the indium piece with the junction of cold box.
Further, dark low temperature cooling system based on earth screen shelters from, wherein, be provided with the dewar shell in the cold box, be provided with at least one optical system low temperature heat pipe on the cold box, the dewar shell with connect through the graphite cold chain between the optical system low temperature heat pipe.
Further, dark low temperature cooling system based on earth screen shelters from, wherein, graphite cold chain is U type structure for reduce and drag the deformation.
Further, the deep low-temperature heat dissipation system based on earth screen shielding is characterized in that a lens cone support is arranged below the lens cone, a frame support is arranged on the frame, and at least one layer of polyimide is arranged between the lens cone support and the frame support and used for reducing the cold loss of the optical system.
The invention has the following beneficial effects:
(1) the earth screen is in a folded state when being launched, thereby reducing the launching cost and increasing the satellite loading space; the earth screen shields external heat flow after being unfolded in orbit, and reduces the temperature of the radiation plate of the optical system, thereby realizing the requirement of the optical system on the deep low temperature.
(2) The conduction and heat dissipation of the optical system are increased, and the imaging stability of the optical system of the satellite camera is improved.
(3) The loss of the cooling capacity of the optical system is reduced, the power consumption of the system is reduced, and the overall stability of the system is improved.
Drawings
FIG. 1 is a perspective view of an earth screen in a collapsed state according to a preferred embodiment of the present invention;
FIG. 2 is a perspective view of the earth's screen in an extended state according to the preferred embodiment of the present invention;
FIG. 3 is a schematic view of the insulation of two ends of the heat-insulating support according to the preferred embodiment of the invention;
FIG. 4 is a schematic view of the mechanical interface between the lens barrel and the cold box according to the preferred embodiment of the present invention;
fig. 5 is an enlarged view of a portion a of the mechanical interface between the lens barrel and the cold box of fig. 4;
FIG. 6 is a perspective view of a graphite cold chain connection according to a preferred embodiment of the present invention; and
FIG. 7 is a schematic view of the thermal isolation of the lens barrel support and frame support polyimide according to the preferred embodiment of the invention.
Detailed Description
As shown in fig. 1, 2 and 3, the cryogenic heat dissipation system mainly includes a satellite platform 1 for carrying a camera, an optical system radiation plate 2 for controlling temperature, and an earth screen 3 for shielding heat flow. The satellite platform 1 comprises a frame 11. Wherein, thermal-insulated support 12 adopts epoxy glass fiber reinforced plastic material that excels in, thermal-insulated support first end 121 and the frame 11 of thermal-insulated support 12 are through 6M 2.5 screw connections, thermal-insulated support second end 122 of thermal-insulated support 12 is connected with optical system radiant panel 2 through 4M 2 screws, through the first support tip 121 and the second of thermal-insulated support 12 support the connection of tip 122, avoided taking place heat conduction through screw lug connection between optical system radiant panel 2 and the frame 11, can effectively reduce the conduction heat leak of optical system radiant panel 2.
The earth screen 3 is hinged to the satellite platform and camera frame by hinges 31. Preferably, this embodiment provides two hinges 31, one hinged to the frame of the camera and one hinged to the satellite platform 1. The pressing lever 37 is provided at the center of the earth screen 3 and protrudes from the earth screen 3. The optical system radiation plate 2 is provided with a cutout 23 corresponding to the pressing rod 37. The digging hole 23 is provided with a pressing and releasing device 32. When the earth screen 3 is launched, the earth screen 3 is in the folded state, and one end of the pressing and releasing device 32 is arranged on the frame 11, and the other end of the pressing and releasing device passes through the digging hole 23 and is connected with the pressing rod 37. The pressing and releasing device 32 is used for being matched with the hinge 31 on the earth screen 3 and fixed on the optical radiation plate 2 in a folding mode when the satellite is launched so as to reduce the satellite envelope when the satellite is launched. The pressing and releasing device 32 is provided with a firer cutter 321 for spreading the earth screen 3 in space, the firer cutter 321 is a part of the pressing and releasing device 32, and the firer cutter 321 cuts the pressing rod 37 to spread the earth screen 3 during satellite orbit.
As shown in fig. 2, the optical system radiation plate 2 and the earth screen 3 are rectangular structures. The relative positions of the edges of the optical system radiation plate 2 form an optical system radiation plate first edge portion 21 and an optical system radiation plate second edge portion 22. The relative positions of the edges of the earth screen 3 form an earth screen first edge portion 38 and an earth screen second edge portion 39 of the earth screen 3.
The first side sheet first edge portion 331 of the first side sheet 33 is provided on the earth screen first edge portion 38 of the earth screen 3; the first side flap second edge portion 332 is provided on the optical system radiation plate first edge portion 21 of the optical system radiation plate 2; the first side sheet third edge portion 333, together with the first side sheet first edge portion 331 and the first side sheet second edge portion 332, enclose a triangular plane. The second side sheet first edge portion 341 of the second side sheet 34 is provided on the earth screen second edge portion 39 of the earth screen 3; the second flap second edge portion 342 is provided on the optical system radiation plate second edge portion 22 of the optical system radiation plate 2; the second side flap third edge portion 343, the second side flap first edge portion 341 and the second side flap second edge portion 342 together enclose a triangular plane. The first side flap 33 and the second side flap 34 form a shield together with the earth screen 3 for blocking external heat flow radiation.
And an auxiliary support member 35 provided near the inner periphery of the earth screen 3, wherein the auxiliary support member 35 stabilizes the earth screen 3 when it is folded in the optical system radiation plate. The side flap pressing mechanism 36 is arranged near the upper and lower edges of the earth screen 3, and the side flap pressing mechanism 36 is used for pressing the first side flap 33 and the second side flap 34 between the earth screen 3 and the optical system radiation plate 2 when the earth screen 3 is folded.
When the satellite is launched, the earth screen 3 is in a folded state, and after the satellite enters the orbit and receives an unfolding instruction, the earth screen 3 is cut by the firer cutter 321 to compress and release the compression rod 37 of the device 32. The earth screen 3 is unlocked to be unfolded and provides an unfolded-in-place signal. After the earth screen 3 is unfolded, the earth screen is matched with a side front fly arranged on the earth screen 3 to shield the infrared radiation external heat flow, so that the temperature of a radiation plate of the optical system is reduced, and the requirement of the optical system on the deep low temperature is met.
As shown in fig. 4 and 5, the lens barrel 4 is provided in the cold box 5. An indium sheet 6 is arranged between the connection part of the lens cone 4 and the cold box 5. The thickness of the indium sheet 6 is 0.1mm, the indium sheet 6 is soft, when a camera is in orbit or in a vacuum test, deformation is inconsistent under a large temperature difference environment due to different materials of the lens cone 4 and the cold box 5, and the indium sheet 6 arranged between the connection part of the lens cone 4 and the cold box 5 can effectively reduce the pressure stress borne by the lens cone 4 when the lens cone 4 is deformed under pressure, so that the influence of the large temperature difference on the image quality of the lens is reduced. Meanwhile, when the assembly precision is not high enough, the contact area between the lens barrel 4 and the cold box 5 can be increased by the soft indium sheet with good heat conduction effect, so that the heat conduction between the lens barrel 4 and the cold box 5 is increased.
As shown in fig. 6, the dewar housing 7 is set in the cold box 5, and the surface of the dewar housing 7 is plated with gold. Four optical system low temperature heat pipes 8 are arranged on the upper part of the cold box 5, and the Dewar shell 7 is connected with two of the optical system low temperature heat pipes 8 through a U-shaped graphite cold chain 9. The graphite cold chain 9 belongs to a flexible heat conduction connecting piece and is formed by sewing 40 layers of graphite sheet layers. Because the graphite cold chain 9 adopts the U-shaped structure in the structural design, the expansion with heat and contraction with cold of the graphite cold chain 9 can not cause the obvious pulling deformation of the Dewar. The Dewar shell 7 and the optical system low-temperature heat pipe 8 are connected through the flexible graphite cold chain 9, and the low-temperature index and temperature control requirements of the Dewar shell 7 can be met. The graphite cold chain is adopted as a heat conduction design scheme, so that heat conduction can be enhanced, and the influence of the thermal control component on the image quality of the optical system in a large temperature difference environment can be reduced.
As shown in fig. 7, a lens barrel support 41 is disposed below the lens barrel 4, a frame support 111 is disposed on the frame 11, and at least one layer of polyimide 11 is disposed between the lens barrel support 41 and the frame support 111, and the present embodiment is preferably configured as three layers. The polyimide 10 is a high molecular material having outstanding heat insulation, high temperature resistance, radiation resistance, chemical corrosion resistance and electrical insulation properties. 3 layers of polyimide 10 are arranged between the lens barrel 41 support and the frame support 111 for heat insulation, so that the refrigeration loss of an optical system can be reduced.
Through the multi-stage heat insulation design, the refrigeration capacity loss of the optical system can be effectively reduced, and the design index requirements of the optical system at the deep low temperature are met. The earth screen 3 is used to shield the external heat flow entering the optical system radiation plate 2, and the design scheme of the heat dissipation system with high efficiency conduction shown in fig. 4 to 7 is adopted to further reduce the ambient temperature of the optical system.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and those skilled in the art can equally or differently substitute the technical solution of the present invention and the inventive concept thereof within the technical scope of the present invention. It should be understood that various changes may be made in the connection manner, such as screw connection and hinge connection, and these possible modifications are intended to be included within the scope of the present invention.
Reference numerals:
1-a satellite platform;
11-a frame;
111-a frame support;
12-a thermally insulating support;
121-a thermally insulating standoff first end;
122-a thermally insulating standoff second end;
2-an optical system radiation plate;
21-optical system radiation plate first edge portion;
22-the second edge portion of the optical system radiation plate;
23-digging a hole;
3-earth screen;
31-a hinge;
32-a compression and release device;
321-a fire cutter;
33-a first side flap;
331-a first side flap first edge portion;
332-a second side flap second edge portion;
333-a third edge portion of the third side flap;
34-second side flap
341-second side flap first edge portion;
342-a second side panel second edge portion;
343-third edge of second side flap
35-auxiliary support members;
36-side placket pressing mechanism;
37-a hold down bar;
38-earth screen first edge portion;
39-second edge portion of earth screen;
4-a lens barrel;
41-lens barrel support;
5-a cold box;
6-indium plate;
7-Dewar shell;
8-optical system low-temperature heat pipe;
9-graphite cold chain;
10-polyimide.
Claims (10)
1. The utility model provides a dark low temperature cooling system based on earth screen shelters from, its characterized in that, including satellite platform (1) that bears the camera, optical system radiation plate (2) of control temperature and earth screen (3) of sheltering from the heat current, earth screen (3) with satellite platform (1) and camera frame are articulated, on drawing in optical system radiation plate (2) when earth screen (3) construct the transmission, expand when the orbit and keep camera job stabilization with sheltering from the heat current.
2. The earth screen shielding based deep low temperature heat dissipation system according to claim 1, wherein the satellite platform (1) comprises a frame (11), the optical system radiation plate (2) is connected with the frame (11) through a heat insulation support (12), and the heat insulation support (12) is made of epoxy glass fiber reinforced plastic material, so as to reduce the heat conduction leakage of the optical system radiation plate (2) and the frame (11).
3. Deep low temperature heat dissipation system based on earth screen shading according to claim 2, characterized in that the earth screen (3) comprises a first side sheet (33) and a second side sheet (34);
the edge of the earth screen (3) is opposite to form a first edge part (38) and a second edge part (39) of the earth screen;
the first side flap (33) is arranged at a first edge part (38) of the earth screen (3), the second side flap (34) is arranged at a second edge part (39) of the earth screen (3), the first side flap (33) and the second side flap (34) are arranged oppositely to form a shield together with the earth screen (3) for blocking external heat flow radiation.
4. The earth screen shielding based deep low temperature heat dissipation system according to claim 3, wherein the first side sheet (33) comprises a first side sheet first edge portion (331), a first side sheet second edge portion (332), and a first side sheet third edge portion (333);
the second side flap (34) includes a second side flap first edge portion (341), a second side flap second edge portion (342), and a second side flap third edge portion (343);
a first edge part (21) and a second edge part (22) of the optical system radiation plate are formed at the opposite positions of the edges of the optical system radiation plate (2);
the first side flap first edge portion (331) is arranged on the earth screen first edge portion (38), the first side flap second edge portion (332) is arranged on the optical radiation plate first edge portion (21), the first side flap third edge portion (333), together with the first side flap first edge portion (331) and the first side flap second edge portion (332), encloses a triangular plane, the second side flap first edge portion (341) is arranged on the earth screen second edge portion (39), the second side flap second edge portion (342) is arranged on the optical system radiation plate second edge portion (22), and the second side flap third edge portion (343), together with the second side flap first edge portion (341) and the second side flap second edge portion (342), encloses a triangular plane.
5. Deep low temperature heat dissipation system based on earth screen shading according to claim 1, characterized in that the earth screen (3) is provided with a pressing and releasing device (32), the earth screen (3) is provided with a hole (23) corresponding to the pressing and releasing device (32), and the hole (23) is used for accommodating the pressing and releasing device (32).
6. The earth screen shielding based deep low temperature heat dissipation system according to claim 5, wherein a fire cutter (321) is arranged on the compressing and releasing device (32), and the fire cutter (321) is exploded by fire to cut the compressing rod (37) to release the earth screen (3).
7. The earth screen shielding based deep cryogenic heat dissipation system according to claim 2, characterized in that the camera of the satellite platform (1) comprises a cold box (5) and a lens barrel (4) for an optical heat dissipation system:
the lens cone (4) is arranged in the cold box (5);
and an indium sheet (6) is arranged at the joint of the lens cone (4) and the cold box (5).
8. The earth screen shielding-based deep low-temperature heat dissipation system according to claim 7, wherein a Dewar casing (7) is arranged in the cold box (5), at least one optical system low-temperature heat pipe (8) is arranged on the cold box (5), and the Dewar casing (7) is connected with the optical system low-temperature heat pipe (8) through a graphite cold chain (9).
9. The earth screen shielding-based deep low temperature heat dissipation system according to claim 8, wherein the graphite cold chain (9) is of a U-shaped structure to reduce pulling deformation.
10. The earth screen shielding-based deep low-temperature heat dissipation system according to claim 7, wherein a lens barrel support (41) is arranged below the lens barrel (4), a frame support (111) is arranged on the frame (11), and at least one layer of polyimide (10) is arranged between the lens barrel support (41) and the frame support (111) to reduce the loss of cooling capacity of an optical system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210400111.6A CN114735252B (en) | 2022-04-15 | 2022-04-15 | Deep low-temperature heat dissipation system based on earth screen shielding |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210400111.6A CN114735252B (en) | 2022-04-15 | 2022-04-15 | Deep low-temperature heat dissipation system based on earth screen shielding |
Publications (2)
| Publication Number | Publication Date |
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| CN114735252A true CN114735252A (en) | 2022-07-12 |
| CN114735252B CN114735252B (en) | 2023-12-22 |
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