A system for testing radiant cooler and its internal satellite-ground compatible dewar structure

Abstract

The invention belongs to the technical field of radiant coolers, and discloses a system for testing radiant coolers and an internal satellite-to-ground compatible dewar structure thereof, comprising a vacuum system, a refrigeration system and a satellite-to-ground compatible dewar structure. The satellite-to-ground compatible dewar structure is applied to different radiant coolers and has different structures. The vacuum system is used to provide a vacuum environment inside the satellite-to-ground compatible dewar structure, and the refrigeration system is used to provide a low-temperature environment inside the satellite-to-ground compatible dewar structure. Through the cooperation of the vacuum system and the refrigeration system, a vacuum and low-temperature environment is provided inside the satellite-to-ground compatible dewar structure, and a working environment is provided for an infrared detector inside the radiant cooler, thereby simulating a normal working environment of infrared detection in a ground environment, so as to perform debugging and correction. The invention solves the problem in the prior art that infrared detectors cannot work normally in a ground environment, resulting in failure to perform debugging and correction, and is suitable for radiant cooler testing.

Description

Technical Field

[0001] The present invention relates to the technical field, and in particular to a system for testing a radiant cooler and an internal satellite-to-ground compatible dewar structure thereof. Background Art

[0002] Generally, an infrared detector is installed on the secondary component of the radiation cooler, and the infrared detector needs to work in a low-temperature environment. The instrument is debugged on the ground in an atmospheric environment, but the radiation cooler is only suitable for use in a cold black, vacuum environment. Therefore, the radiation cooler cannot work during debugging in an atmospheric environment; therefore, a system that can simulate a vacuum low-temperature environment during the ground test phase is needed to ensure that the infrared detector can be effectively debugged and optically calibrated during the ground test phase. Summary of the invention

[0003] The present invention is intended to provide a system for testing a radiant cooler and its internal satellite-to-ground compatible dewar structure. The present invention designs a satellite-to-ground compatible dewar structure on the second stage of the radiant cooler, installs the infrared detector on the cold platform of the dewar, and simulates the working environment below 100K required by the infrared detector through the cooperation of the vacuum system and the refrigeration system. At the same time, the satellite-to-ground compatible dewar structure is applied to both geosynchronous orbit radiant coolers and sun-synchronous orbit radiant coolers.

[0004] The present invention provides the following technical solutions:

[0005] A system for testing a radiant cooler, the system is applied to the testing of a geosynchronous orbit radiant cooler and a sun-synchronous orbit radiant cooler, the system comprises a vacuum system, a refrigeration system and a satellite-to-ground compatible dewar structure, the inside of the satellite-to-ground compatible dewar structure is used to place detector components, the vacuum system provides a vacuum environment inside the satellite-to-ground compatible dewar structure, and the refrigeration system cools the inside of the satellite-to-ground compatible dewar structure;

[0006] The vacuum system includes a molecular adsorption pump, a vacuum detector and a mechanical pump. The molecular adsorption pump and the mechanical pump cooperate to evacuate the inside of the satellite-to-earth compatible Dewar structure, and the vacuum detector is used to detect the vacuum degree. The refrigeration system includes a liquid nitrogen cylinder, an infusion gun and an infusion pipeline. Liquid nitrogen is stored in the liquid nitrogen cylinder. Liquid nitrogen serves as a cold source and is input into the satellite-to-earth compatible Dewar structure through the infusion gun and the infusion pipeline for refrigeration.

[0007] Furthermore, when the system is applied to ground experimental tests of geosynchronous orbit radiant coolers, its internal satellite-ground compatible dewar structure includes: a detector platform and a dewar shell. The detector platform is arranged inside the dewar shell. The detector platform is used to provide a mounting surface for the detector. The detector platform is integrally formed and installed with a cold head seat. An inner cylinder support is installed and connected to the outer side of the cold head seat. An insulating block is arranged between the cold head seat and the inner cylinder support. An outer cylinder support is connected and installed to the outer side of the inner cylinder support. A short-circuit cold chain is connected to the upper side of the cold head seat. The dewar shell and the dewar rear cover are connected by a lead ring. The lead ring is a circular ring-shaped part. The upper surface of the lead ring is sealed with the dewar shell, and the lower surface of the lead ring is sealed with the dewar rear cover. , the outer cylinder support is connected and installed with the lead ring, and a refrigeration window is arranged on the rear cover of the Dewar; the Dewar cover is detachably connected with the Dewar cover on the upper side of the Dewar shell, and the Dewar cover includes a pumping port, a Dewar cover body, an elastic cold knife, a liquid nitrogen inlet pipe and a liquid nitrogen outlet pipe, and the liquid nitrogen inlet pipe and the liquid nitrogen outlet pipe are both arranged inside the elastic cold knife, and the length of the liquid nitrogen inlet pipe is greater than that of the liquid nitrogen outlet pipe, and the pumping port, the elastic cold knife, the liquid nitrogen inlet pipe and the liquid nitrogen outlet pipe are all welded and sealed with the Dewar cover body; the pumping port is connected with the vacuum system for evacuating the inside of the satellite-to-ground compatible Dewar structure, the liquid nitrogen inlet pipe is connected with the refrigeration system for entering liquid nitrogen for refrigeration, and the liquid nitrogen outlet pipe is connected with the outside world for discharging liquid nitrogen; the nitrogen protection system introduces nitrogen by setting a nitrogen pipeline.

[0008] Furthermore, when the system is applied to a solar synchronous orbit radiant cooler, its internal satellite-to-ground compatible dewar structure includes: a secondary cold block seat and a detachable dewar upper cover, the detachable dewar upper cover is detachably connected to the secondary cold block seat, the interior of the secondary cold block seat is used to place the detector, the secondary cold block seat is provided with a secondary window, a Kovar terminal and a cold chain, the interior of the detachable dewar upper cover is provided with a liquid nitrogen cavity, the liquid nitrogen cavity is connected with a liquid nitrogen pipeline, the interior of the detachable dewar upper cover is connected with a vacuum exhaust port, when the detachable dewar upper cover is connected to the secondary cold block seat, the secondary cold block seat, the secondary window and the detachable dewar upper cover form a sealed cavity; the vacuum exhaust port is connected to the vacuum system, the interior of the satellite-to-ground compatible dewar structure is evacuated through the vacuum exhaust port, the liquid nitrogen pipeline is connected to the refrigeration system for the introduction and discharge of liquid nitrogen; the nitrogen protection system includes a window and a window bracket, the window and the window bracket form a semi-enclosed space, and nitrogen is introduced into the semi-enclosed space through the window.

[0009] Furthermore, in the satellite-to-ground compatible dewar structure used in the geosynchronous orbit radiant cooler, the detachable connection between the dewar shell and the dewar cover adopts an O-ring seal, and the connection is realized by a mounting part, and the contact part between the mounting part, the dewar cover and the dewar shell is made of polytetrafluoroethylene.

[0010] Through the above settings, the use of polytetrafluoroethylene material can protect the parts and avoid scratches and damage to the pressing surface after multiple disassembly and assembly. At the same time, the use of mounting parts to connect the Dewar shell and the Dewar cover can avoid setting threads and threaded holes on the Dewar shell and the Dewar cover, avoiding the risk of damage to the threaded holes after multiple disassembly and assembly.

[0011] Furthermore, the satellite-to-ground compatible Dewar structure used in the geosynchronous orbit radiant cooler has an elastic cold knife of a stainless steel structure, and the elastic cold knife is provided with a bellows structure.

[0012] Through the above-mentioned arrangement, the elastic cold knife has a certain axial compression, and the bellows can be compressed and has a certain compression when it contacts the detector platform; having a certain compression can ensure that the bottom surface of the elastic cold knife is in good contact with the top of the detector platform, thereby ensuring the stability of the cooling temperature. At the same time, there will be no risk of the bottom surface of the elastic cold knife detaching from the top of the detector mounting platform after low temperature, resulting in the risk of failure to cool the detector.

[0013] Furthermore, in the system used for ground experimental testing of geosynchronous orbit radiant coolers, a plastic protective cover is provided on the outer side of the satellite-ground compatible dewar structure.

[0014] Through the above settings, interference from the external atmospheric environment can be further avoided.

[0015] Furthermore, a satellite-to-ground compatible Dewar structure is used for a geosynchronous orbit radiant cooler, and the support includes an inner tube support and an outer tube support. The inner tube support is installed and connected to the outer side of a cold head seat. An insulation block is arranged between the cold head seat and the inner tube support. The insulation block is made of polyimide. The outer side of the inner tube support is connected and installed with an outer tube support, and the outer tube support is connected and installed with a lead ring.

[0016] Through the above settings, this connection and installation method provides a good mechanical installation environment, ensures a good mechanical environment for the detector, and improves reliability; at the same time, it greatly extends the path of cold loss, reduces cold loss, and improves the refrigeration performance of the radiant cooler. The longer the cold loss, the smaller the cold loss. The path from the detector to the Dewar shell is: detector mounting surface-cold head seat-insulation pad-inner tube support-outer tube support-lower end of the outer tube support-lead ring-Dewar shell.

[0017] Furthermore, the satellite-to-ground compatible Dewar structure used for the geosynchronous orbit radiant cooler has an inner tube support and an outer tube support that are thin-walled titanium alloy structures with a wall thickness of 0.3 to 1 mm, and an array of circular holes is arranged on the inner tube support and the outer tube support.

[0018] Through the above arrangement, a thin-walled titanium alloy structure is adopted, which has strong structural strength and low thermal conductivity. The circular holes arranged in an array on the thin wall can increase the thermal resistance of the parts and further improve the thermal conductivity and insulation performance of the inner and outer tubes.

[0019] Furthermore, a satellite-to-ground compatible dewar structure is used for a geosynchronous orbit radiant cooler, and when the structure is in orbit, the dewar cover is replaced by a cold block.

[0020] With the above arrangement, when in orbit (after being launched into space), the cold block radiates heat to the deep cold space to achieve detector cooling.

[0021] Furthermore, a satellite-to-ground compatible dewar structure is used for a sun-synchronous orbit radiant cooler. When the structure is in orbit, the dewar upper cover can be removed and replaced with a cold block.

[0022] With the above arrangement, when in orbit (after being launched into space), the cold block radiates heat to the deep cold space to achieve detector cooling.

[0023] Principle of the technical solution: When the ground test of the geosynchronous orbit radiant cooler is carried out under the ground atmospheric environment, the detector is installed on the detector platform, and the dewar cover and the dewar shell are connected by mounting parts to form a sealed chamber. The vacuum system is connected through the pumping port to evacuate the inside of the dewar. An elastic cold knife is provided on the dewar cover. The inside of the elastic cold knife is connected to the refrigeration system through a liquid nitrogen inlet pipe. The liquid nitrogen outlet pipe is connected to the outside to form a liquid nitrogen flow pipeline. The bottom of the elastic cold knife is in close contact with the detector platform, so that the cold energy is transferred to the detector; thereby simulating a vacuum low temperature environment. Nitrogen protection is introduced into the interior through a nitrogen pipeline to ensure that the optical window of the detector will not condense or frost. After the test is completed, the dewar cover is removed, and the cold block is connected to the dewar shell. When in orbit, the cold block radiates heat to the deep cold space to achieve detector cooling.

[0024] When conducting ground tests of the sun-synchronous orbit radiant cooler in the ground atmosphere, the detector is installed inside the secondary cold block seat. The secondary cold block seat, the secondary window and the removable dewar cover form a sealed chamber. The vacuum exhaust port is connected to the vacuum system to evacuate the interior of the dewar. The liquid nitrogen pipeline is connected to the refrigeration system, and the liquid nitrogen flows into the liquid nitrogen chamber, thereby transferring the cold to the detector; this simulates a vacuum and low-temperature environment. Nitrogen is filled into the semi-enclosed space of the window for protection, thereby protecting the optical window of the detector from condensation and frost. After the test is completed, the removable dewar cover is removed, and the cold block is connected to the secondary cold block seat. When in orbit, the cold block performs radiation heat exchange with the deep cold space to achieve detector cooling.

[0025] The beneficial effects of the technical solution are: the system and the satellite-to-ground compatible dewar structure in the system cooperate with each other to simulate the vacuum and low-temperature environment of the detector components when working in space, so that the detector components can be debugged and calibrated on the ground; the system can be applied to the testing of geosynchronous orbit radiant coolers and sun-synchronous orbit radiant coolers at the same time. For the testing of different radiant coolers, the corresponding satellite-to-ground dewar structures are different, and its applicability is strong. A nitrogen protection system is set in the system, which can protect the optical window of the detector from condensation and frost by filling nitrogen. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1The ground test system of the geosynchronous orbit radiant cooler of the present invention;

[0027] Figure 2 This is a diagram of the geosynchronous satellite's compatible dewar structure;

[0028] Figure 3 The structure diagram of the cryostat cover for the geosynchronous satellite ground-compatible cryostat structure;

[0029] Figure 4 It is the on-orbit state diagram of the geosynchronous satellite's ground-compatible dewar structure;

[0030] Figure 5 It is a ground test system for the sun-synchronous orbit radiant cooler of the present invention;

[0031] Figure 6 The structure diagram of the dewar compatible with the sun-synchronous star;

[0032] Figure 7 The on-orbit state diagram of the earth-compatible dewar structure of the sun-synchronous satellite;

[0033] The names of the corresponding marks in the accompanying drawings are: vacuum system 1, refrigeration system 2, geosynchronous star compatible dewar structure 3, solar synchronous star compatible dewar structure 4, nitrogen protection system 5, detector 6, plastic protective cover 7, cold block 8, molecular sieve adsorption pump 11, vacuum detector 12, mechanical pump 13, liquid nitrogen cylinder 21, infusion gun 22, infusion pipeline 23, detector platform 31, dewar shell 32, cold head seat 33, support 34, inner cylinder support 341, outer cylinder support 342, partition Heat block 35, short-circuit cold chain 36, Dewar rear cover 37, refrigeration window 371, lead ring 38, Dewar cover 39, extraction port 391, Dewar cover body 392, elastic cold knife 393, liquid nitrogen inlet pipe 394, liquid nitrogen outlet pipe 395, mounting part 396, secondary cold block seat 41, detachable Dewar upper cover 42, secondary window 43, Kovar terminal 44, liquid nitrogen chamber 45, liquid nitrogen pipeline 46, vacuum extraction port 47, cold chain 48, nitrogen pipeline 51, window 52, ​​window bracket 53. DETAILED DESCRIPTION

[0034] The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments:

[0035] Embodiment 1, geosynchronous orbit radiant cooler test system:

[0036] like Figure 1-Figure 4As shown, a system for testing a radiant cooler includes a vacuum system 1, a refrigeration system 2, a nitrogen protection system 5 and a geosynchronous satellite-compatible Dewar structure 3. The vacuum system 1 includes a molecular sieve adsorption pump 11, a mechanical pump 13 and a vacuum detector 12. The refrigeration system 2 includes a liquid nitrogen cylinder 21, an infusion gun 22 and an infusion pipeline 23. The nitrogen protection system 5 includes a nitrogen pipeline 51. At the same time, a plastic protective cover 7 is arranged on the outside of the geosynchronous satellite-compatible Dewar structure.

[0037] The geosynchronous satellite-to-earth compatible dewar structure 3 includes a dewar shell 32, a detector platform 31 is arranged inside the dewar shell 32, a detector 6 is connected and installed on the left side of the bottom of the detector platform 31, a cylindrical cold head seat 33 is integrally formed on the top of the detector platform 31, an inner cylinder support 341 is connected and installed on the outer side of the cold head seat 33, an outer cylinder support 342 is connected and installed on the outer side of the inner cylinder support 341, an insulation block 35 is arranged between the inner cylinder support 341 and the outer cylinder support 342, and the insulation block 35 is made of polyimide. The lower end of the outer cylinder support 342 is connected to the outer cylinder support 342. The lead ring 38 is connected and installed. The inner cylinder support 341 and the outer cylinder support 342 are both thin-walled titanium alloy structures with a wall thickness of 0.3 to 1 mm, and circular holes are arranged in an array on the thin wall. The top of the cold head seat 33 is connected to a short-circuit cold chain 36. The lower side of the Dewar shell 32 is connected to the Dewar rear cover 37 through the lead ring 38. The lead ring 38 is a circular ring part. The upper surface of the lead ring 38 is connected and sealed with the Dewar shell 32, and the lower surface of the lead ring 38 is connected and sealed with the Dewar rear cover 37. A refrigeration window 371 is provided on the Dewar rear cover 37, and the nitrogen pipeline 51 is connected to the Dewar shell 32 through the refrigeration. Window 371 is filled with nitrogen protection inside the Dewar, and the top of the Dewar shell 32 is connected to the Dewar cover 39 by an o-ring seal through a mounting piece 396. The mounting piece 396 is divided into an upper and lower part. The contact part of the mounting piece 396 with the Dewar shell 32 and the Dewar cover 39 is made of polytetrafluoroethylene. The Dewar cover 39 includes a Dewar cover body 392, and a sealed extraction port 391, an elastic cold knife 393, a liquid nitrogen inlet pipe 394 and a liquid nitrogen outlet pipe 395 are welded on the Dewar cover body 392. The liquid nitrogen inlet pipe 394 and the liquid nitrogen outlet pipe 395 are both arranged on the elastic Inside the elastic cold knife 393, the length of the liquid nitrogen inlet pipe 394 is greater than the length of the liquid nitrogen outlet pipe 395, and a bellows structure is arranged on the elastic cold knife 393, wherein the pumping port 391 selects a KF vacuum pumping port, and the pumping port 391 is connected to the vacuum system 1 to provide a vacuum environment for the inside of the Dewar structure, the liquid nitrogen inlet pipe 394 is connected to the refrigeration system 2, and the liquid nitrogen enters the inside of the Dewar structure from the liquid nitrogen inlet pipe 394, and the liquid nitrogen outlet pipe 395 is connected to the outside world, and the liquid nitrogen outlet pipe 395 is used to discharge liquid nitrogen; the nitrogen pipeline 51 is used to fill with protective nitrogen.

[0038] The specific implementation process is as follows: During the ground test, liquid nitrogen is used as a cold source. The liquid nitrogen is stored in a liquid nitrogen cylinder 21. The liquid nitrogen is input into the geosynchronous satellite compatible dewar structure 33 through the infusion gun 22 through the infusion pipeline 23 and the liquid nitrogen inlet pipe 394. The liquid nitrogen inlet pipe 394 is relatively long and close to the bottom of the elastic cold knife 393. After the liquid nitrogen contacts and exchanges heat with the bottom of the elastic cold knife 393, it will be gasified. The gasified nitrogen is discharged through the liquid nitrogen outlet pipe 395. The cold energy is transferred from the bottom of the elastic cold knife 393 to the detector platform 31, and then from the detector platform 31 to the detector 6 for refrigeration; the suction port 391 is connected to the vacuum system 1, and the interior of the geosynchronous satellite compatible dewar structure 33 is evacuated by turning on the molecular adsorption pump 11 and the mechanical pump 1313, and the internal vacuum degree is detected by the vacuum detector 12; the lower nitrogen pipeline 51 is passed with protective gas nitrogen, so as to protect the optical window of the internal detector 6. After the environmental simulation is completed, the test can be carried out.

[0039] After the test is completed, the dewar cover 39 is disassembled, and the cold block 8 is installed and connected to the dewar shell 32. After the dewar structure is launched into space, the cold block 8 performs radiation heat exchange with the deep cold space to achieve detector cooling.

[0040] Embodiment 2, sun-synchronous orbit radiant cooler test system:

[0041] like Figure 5-Figure 7 As shown, a system for testing a radiant cooler includes a vacuum system 1, a refrigeration system 2, a nitrogen protection system 5 and a sun-synchronous star-compatible Dewar structure 4, wherein the vacuum system 1 includes a molecular sieve adsorption pump 11, a mechanical pump 13 and a vacuum detector 12, the refrigeration system 2 includes a liquid nitrogen cylinder 21, an infusion gun 22 and an infusion pipeline 23; the nitrogen protection system 5 includes a window 52 and a window bracket 53, and the window 52 and the window bracket 53 form a semi-enclosed space structure.

[0042] The solar-synchronous star-to-earth compatible dewar structure 4 includes a secondary cold block seat 41, which can be regarded as a dewar shell, a detector 6 is placed inside the secondary cold block seat 41, a secondary window 43 is on the left side of the secondary cold block seat 41, a Kovar terminal 44 is on the lower side of the secondary cold block seat 41, and a removable dewar cover 42 is detachably connected to the right side of the secondary cold block seat 41. A liquid nitrogen chamber 45 is arranged inside the removable dewar cover 42, and the liquid nitrogen chamber 45 is connected to a liquid nitrogen pipeline 46. A vacuum pumping port 47 is connected to the inside of the removable dewar cover 42, and a cold chain 48 is connected to the right side of the secondary cold block seat. The vacuum system 1 is connected to the vacuum pumping port 47 through a pipeline, and the infusion pipeline 23 of the refrigeration system 2 is connected to the liquid nitrogen pipeline 46. The nitrogen protection system 5 includes a window 52 and a window bracket 53. The window 52 and the window bracket 53 form a semi-enclosed space structure, and the secondary window 43 is arranged in the semi-enclosed space.

[0043] Specific implementation process: During the ground test, liquid nitrogen is used as a cold source. The liquid nitrogen is stored in a liquid nitrogen cylinder 21. The liquid nitrogen is input into the interior of the sun-synchronous star compatible dewar structure 4 through the infusion gun 22 and the infusion pipeline 23. The liquid nitrogen is stored in a liquid nitrogen chamber 45. The liquid nitrogen chamber 45 is in contact with one end of a cold chain 48, and the cold energy is transferred to the detector 6 through the cold chain 48; the vacuum pumping port 47 is connected to the vacuum system 1, and the interior of the sun-synchronous star compatible dewar structure 3 is evacuated by turning on the molecular adsorption pump 11 and the mechanical pump 13, and the internal vacuum degree is detected by the vacuum detector 12; nitrogen is filled into the semi-enclosed space in the window bracket 53 through the window 52, ​​so as to protect the optical window of the detector 6. The test can be carried out after the environmental simulation is completed.

[0044] After the test is completed, the detachable Dewar upper cover 42 is removed, and after removal, the cold block 8 is installed and connected to the secondary cold block seat 41. The cold block 8 is connected to the cold chain 48. After the Dewar structure is launched into space, the cold block 8 performs radiation heat exchange with the deep cold space to realize detector refrigeration.

[0045] The above is only an embodiment of the present invention, and the common knowledge such as the known specific technical solutions or characteristics in the solution is not described in detail here. It should be pointed out that for those skilled in the art, several modifications and improvements can be made without departing from the technical solution of the present invention, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicality of the patent. The scope of protection required by this application shall be based on the content of its claims, and the specific implementation methods and other records in the specification can be used to interpret the content of the claims.

Claims

1. A system for testing a radiant cooler, characterized in that: The system is applied to the testing of geosynchronous orbit radiant coolers or sun-synchronous orbit radiant coolers, and comprises a vacuum system (1), a refrigeration system (2), a nitrogen protection system (5), and a satellite-to-ground compatible dewar structure, wherein the inside of the satellite-to-ground compatible dewar structure is used to place a detector (6), the vacuum system (1) provides a vacuum environment for the inside of the satellite-to-ground compatible dewar structure, the refrigeration system (2) cools the inside of the satellite-to-ground compatible dewar structure, and the nitrogen protection system (5) is used to protect the detector (6); The vacuum system (1) comprises a molecular adsorption pump (11), a vacuum detector (12) and a mechanical pump (13); the molecular adsorption pump (11) cooperates with the mechanical pump (13) to evacuate the interior of the satellite-to-earth compatible dewar structure; the vacuum detector (12) is used to detect the degree of vacuum; the refrigeration system comprises a liquid nitrogen cylinder (21), an infusion gun (22) and an infusion pipeline (23); liquid nitrogen is stored in the liquid nitrogen cylinder (21); the liquid nitrogen serves as a cold source; and the liquid nitrogen is input into the interior of the satellite-to-earth compatible dewar structure through the infusion gun (22) and the infusion pipeline (23) for refrigeration; When the system for testing a radiant cooler is applied to a ground experiment test of a geosynchronous orbit radiant cooler, its internal satellite-to-ground compatible dewar structure comprises: a detector platform (31) and a dewar shell (32); the detector platform (31) is arranged inside the dewar shell (32); the detector platform (31) is used to provide a mounting surface for the detector (6); the detector platform (31) is integrally formed with a cold head seat (33); the outer side of the cold head seat (33) is connected to a support (34); the upper side of the cold head seat (33) is connected to a short-circuit cold chain (36); the dewar shell (32) and the dewar rear cover (37) are connected via a lead ring (38); the lead ring (38) is a circular ring-shaped part; the upper surface of the lead ring (38) is sealed with the dewar shell (32); and the lower surface of the lead ring (38) is sealed with the dewar shell (32). The Dewar rear cover (37) is installed and sealed, the support (34) is connected and installed with the lead ring (38), and a refrigeration window (371) is provided on the Dewar rear cover (37); the Dewar shell (32) is detachably connected with a Dewar cover (39) on the upper side, and the Dewar cover (39) comprises a withdrawal port (391), a Dewar cover body (392), an elastic cold knife (393), a liquid nitrogen inlet pipe (394) and a liquid nitrogen outlet pipe (395), the liquid nitrogen inlet pipe (394) and the liquid nitrogen outlet pipe (395) are both arranged inside the elastic cold knife (393), the liquid nitrogen inlet pipe (394) is longer than the liquid nitrogen outlet pipe (395), and the withdrawal port (391), the elastic cold knife (393), the liquid nitrogen inlet pipe (394) and the liquid nitrogen outlet pipe (395) are all welded and sealed with the Dewar cover body (392); The extraction port (391) is connected to the vacuum system (1) for evacuating the interior of the satellite-to-ground compatible dewar structure; the liquid nitrogen inlet pipe (394) is connected to the refrigeration system for introducing liquid nitrogen for refrigeration; the liquid nitrogen outlet pipe (395) is connected to the outside for discharging liquid nitrogen; the nitrogen protection system (5) is provided with a nitrogen pipeline for introducing nitrogen; When the system for testing a radiant cooler is applied to testing a radiant cooler in a sun-synchronous orbit, its internal satellite-to-ground compatible dewar structure comprises: a secondary cold block seat (41) and a detachable dewar upper cover (42); the detachable dewar upper cover (42) is detachably connected to the secondary cold block seat (41); the interior of the secondary cold block seat (41) is used to place a detector (6); the secondary cold block seat (41) is provided with a secondary window (43), a Kovar terminal (44) and a cold chain (48); the interior of the detachable dewar upper cover (42) is provided with a liquid nitrogen cavity (45); the liquid nitrogen cavity (45) is connected to a liquid nitrogen pipeline (46); the interior of the detachable dewar upper cover (42) is connected to a vacuum exhaust port (47); when the detachable dewar upper cover (42) is connected to the secondary cold block seat (41), the secondary cold block seat (41), the secondary window (43) and the detachable dewar upper cover (42) form a sealed cavity; The vacuum pumping port (47) is connected to the vacuum system (1), and the interior of the satellite-to-ground compatible dewar structure is evacuated through the vacuum pumping port (47); the liquid nitrogen pipeline (46) is connected to the refrigeration system (2) for the intake and discharge of liquid nitrogen; the nitrogen protection system (5) comprises a window (52) and a window bracket (53); the window (52) and the window bracket (53) form a semi-enclosed space, and nitrogen is introduced into the semi-enclosed space through the window (52).

2. The system for testing a radiant cooler according to claim 1, characterized in that: For a satellite-to-ground compatible dewar structure used for testing a geosynchronous orbit radiant cooler, the dewar shell (32) and the dewar cover (39) are detachably connected using an O-ring seal, and the connection is achieved by a mounting member (396). The mounting member (396) consists of an upper and lower part, and the contact portion of the mounting member (396) with the dewar cover (39) and the dewar shell (32) is made of polytetrafluoroethylene.

3. The system for testing a radiant cooler according to claim 1, characterized in that: For a satellite-to-ground compatible dewar structure used for testing a geosynchronous orbit radiant cooler, the elastic cold knife (393) is a stainless steel structure, and the elastic cold knife (393) is provided with a bellows structure.

4. The system for testing a radiant cooler according to claim 1, characterized in that: When used in ground experimental tests of geosynchronous orbit radiant coolers, a plastic protective cover (7) is arranged on the outer side of the satellite-ground compatible dewar structure.

5. The system for testing a radiant cooler according to claim 1, characterized in that: For a satellite-to-ground compatible dewar structure used for testing a geosynchronous orbit radiant cooler, the support (34) comprises an inner tube support (341) and an outer tube support (342); the outer side of the cold head seat (33) is connected to the inner tube support (341); a heat insulation block (35) is provided between the cold head seat (33) and the inner tube support (341); the heat insulation block (35) is made of polyimide; the outer side of the inner tube support (341) is connected to the outer tube support (342); and the outer tube support (342) is connected to the lead ring (38).

6. The system for testing a radiant cooler according to claim 5, characterized in that: For a satellite-to-ground compatible dewar structure used for testing a geosynchronous orbit radiant cooler, the inner cylinder support (341) and the outer cylinder support (342) are thin-walled titanium alloy structures with a wall thickness of 0.3 to 1 mm, and circular holes are arranged in an array on the inner cylinder support (341) and the outer cylinder support (342).

7. The system for testing a radiant cooler according to claim 1, characterized in that: For a satellite-to-ground compatible cryostat structure used for testing a geosynchronous orbit radiant cooler, when the structure is in an on-orbit state, the cryostat cover (39) is replaced by a cold block (8).

8. The system for testing a radiant cooler according to claim 1, characterized in that: For a satellite-to-ground compatible dewar structure used for testing a sun-synchronous orbit radiant cooler, when the structure is in an on-orbit state, the detachable dewar upper cover (42) is replaced by a cold block (8).

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