Vacuum test device

Abstract

The invention provides a vacuum test device which is used for testing a product to be tested, the vacuum test device comprises a test shell and a moving structure, the product to be tested is detachably arranged on the moving structure, the moving structure is arranged in the test shell, and at least part of the moving structure is movably arranged. The to-be-tested product is driven to move in the test shell through at least part of the moving structure; the cold plate structure is arranged in the test shell so as to form a cold area for cooling the to-be-tested product; the hot plate structure is arranged in the test shell to form a hot area for heating the to-be-tested product; the cold plate structure and the hot plate structure are respectively arranged at two ends in the test shell, and an area between the cold plate structure and the hot plate structure in the test shell forms a transition area; the problem of low accuracy caused by testing by using a single vacuum cavity in the prior art is solved.

Description

Technical Field

[0001] This application relates to the field of vacuum testing technology, and more specifically, to a vacuum testing apparatus. Background Technology

[0002] In the field of spacecraft research and development and testing, thermal vacuum testing is a crucial environmental simulation test used to verify the performance and reliability of spacecraft and their components under high vacuum and extreme temperature conditions. Currently, most thermal vacuum test chambers are designed based on the principle of a single vacuum chamber and an integrated temperature control system. This architecture can provide a certain temperature environment and vacuum level to meet basic testing requirements.

[0003] Existing thermal vacuum testing methods, in order to achieve rapid temperature changes of spacecraft components under large temperature differences, necessitate a strategy of first maintaining a low temperature within a single vacuum chamber, then breaking the vacuum and physically transferring the product to another independent high-temperature environment for heating. Afterwards, a high vacuum condition must be re-established to complete the entire test cycle. This series of operations inevitably disrupts the continuity of the vacuum environment, contradicting the natural environment where spacecraft operate under a constant high vacuum, thus affecting the realism and accuracy of the test. Summary of the Invention

[0004] The main objective of this invention is to provide a vacuum testing device to solve the accuracy problem caused by using a single vacuum chamber for testing in the prior art.

[0005] To achieve the above objectives, according to one aspect of the present invention, a vacuum testing apparatus is provided for testing a product under test. The vacuum testing apparatus includes a test housing and a movable structure. The product under test is detachably disposed on the movable structure, and the movable structure is disposed within the test housing. At least a portion of the movable structure is movably disposed so as to drive the product under test to move within the test housing via the at least portion of the movable structure.

[0006] A cold plate structure is set inside the test housing to form a cold zone for cooling the product under test;

[0007] A hot plate structure is set inside the test housing to form a hot zone for heating the product to be tested;

[0008] The cold plate structure and the hot plate structure are respectively set at both ends of the test shell, and the area between the cold plate structure and the hot plate structure in the test shell forms a transition zone.

[0009] Furthermore, the cold plate structure includes a first cold plate disposed within the test housing, the first cold plate having a first bearing surface for bearing the product to be tested via the first bearing surface;

[0010] A cooling medium containing assembly, at least a portion of which is used to contain coolant, is disposed on one side of the test housing, and the output end of the cooling medium containing assembly is connected to a first cold plate to deliver cooling medium into the first cold plate for cooling the product to be tested.

[0011] The controller is electrically connected to the cooling medium containment assembly to adjust the cooling temperature of the coolant input into the first cold plate.

[0012] Furthermore, the cold plate structure also includes a first heat sink, disposed within the test housing and surrounding the inner wall of the test housing. The first heat sink is connected to the cooling medium receiving assembly and the controller to radiate cooling of the cold zone. The first cold plate is disposed on the side of the first heat sink away from the moving structure, and the inner surface of the first heat sink is provided with a first black coating. And / or,

[0013] The first protective component is installed on the first bearing surface.

[0014] Furthermore, the hot plate structure also includes a second cold plate disposed inside the test housing. The second cold plate has a second bearing surface to support the product to be tested.

[0015] A thermally conductive medium containing assembly, at least a portion of which is used to contain a thermally conductive medium, is disposed on one side of the test housing, and the output end of the thermally conductive medium containing assembly is used to communicate with a second cold plate to deliver a thermally conductive medium into the second cold plate for heating the product to be tested;

[0016] The controller is electrically connected to the heat transfer medium containment assembly to adjust the heat transfer temperature of the heat transfer medium input into the second cold plate.

[0017] Furthermore, the hot plate structure also includes a second heat sink, disposed within the test housing and surrounding the inner wall of the test housing. The second heat sink is connected to the heat-conducting medium containment assembly and the controller to radiate heat to the hot zone. A second cold plate is disposed on the side of the second heat sink away from the moving structure, and a second black coating is provided on the inner surface of the second heat sink.

[0018] The second protective component is installed on the second bearing surface.

[0019] Furthermore, the movable structure includes a support component disposed on the inner wall of the test housing on the side away from the cold plate structure and the hot plate structure;

[0020] A movable component is movably mounted on a supporting component, and the product under test is mounted on the movable component;

[0021] The controller, connected to the moving component, controls the moving component to move within the test housing along the extension direction of the support component, thereby causing the product under test to switch between cold and hot zones.

[0022] Furthermore, the movable component includes a movable body, which is movably disposed on the support member;

[0023] The connecting component is retractably mounted on the movable body;

[0024] A suspension component is provided on the connecting component. The suspension component has a suspension part to control the extension of the connecting component when a test is required, so as to place the product to be tested on the suspension part.

[0025] Furthermore, the support component is provided with meshing teeth, and the moving assembly also includes:

[0026] A gear structure is mounted on the moving body and meshes with meshing teeth;

[0027] A driving element is mounted on the moving body. The driving end of the driving element is connected to the gear structure to drive the gear structure to move, so that the moving body moves relative to the supporting component.

[0028] Furthermore, the movable structure also includes two limiting members, which are respectively arranged close to both ends of the supporting component to limit the movement distance of the movable component.

[0029] Furthermore, the vacuum testing device also includes temperature detection components, which are respectively installed on the cold plate structure, the hot plate structure and the product under test, to detect the cold plate temperature of the cold plate structure, the hot plate temperature of the hot plate structure and the real-time temperature of the product under test.

[0030] Both the electrical connector and the temperature monitoring instrument are mounted on the test housing. The electrical connector is connected to the temperature detection component, and the temperature monitoring instrument is connected to the electrical connector to receive the cold plate temperature, hot plate temperature, and real-time temperature through the electrical connector.

[0031] By applying the technical solution of this invention, the testing efficiency and accuracy of spacecraft components under extreme temperature conditions are significantly improved through the coordinated operation of the moving structure and independent cold and hot plate structures. Specifically, the precise positioning and rapid transfer capability of the moving structure enables the product under test to achieve temperature switching between cold and hot zones within ≤3 minutes, without disrupting the vacuum environment, and maintaining a temperature of ≤6.65×10 throughout the process. -3The high vacuum of Pa more realistically simulates the extreme temperature difference environment of spacecraft in orbit, meeting the requirements of GJB 1027A-2005 standard for rapid temperature change and environmental continuity. The independent temperature control design of the cold and hot plate structures ensures that the cold zone temperature range is -80℃ to +150℃, and the hot zone temperature remains stable within the user-set high temperature value, with temperature uniformity ≤2.0℃ and deviation ≤±2.0℃, achieving precise control and rapid change of the surface temperature of the product under test. The transition zone utilizes the natural attenuation characteristics of thermal radiation to avoid thermal crosstalk between the cold and hot zones, ensuring the independence and accuracy of temperature testing. Attached Figure Description

[0032] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0033] Figure 1 This paper shows a schematic diagram of the vacuum testing apparatus according to an embodiment of the present application from a first-view perspective;

[0034] Figure 2 This invention provides a schematic diagram of the vacuum testing apparatus according to an embodiment of the present application from a second perspective.

[0035] Figure 3 A schematic diagram of the movable structure according to an embodiment of this application is shown.

[0036] The above figures include the following reference numerals:

[0037] 1. Test housing; 2. Moving structure; 21. Supporting component; 211. Meshing gear; 22. Moving assembly; 221. Moving body; 222. Connecting component; 223. Gear structure; 224. Driving element; 225. Suspension component; 3. Product under test; 4. Cold plate structure; 41. First cold plate; 42. First heat sink; 5. Hot plate structure; 51. Second cold plate; 52. Second heat sink; 6. Transition zone. Detailed Implementation

[0038] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0039] In the field of spacecraft research and development and testing, thermal vacuum testing is a crucial environmental simulation test used to verify the performance and reliability of spacecraft and their components under high vacuum and extreme temperature conditions. Currently, most thermal vacuum test chambers are designed based on the principle of a single vacuum chamber and an integrated temperature control system. This architecture can provide a certain temperature environment and vacuum level to meet basic testing requirements.

[0040] Existing thermal vacuum testing methods, in order to achieve rapid temperature changes of spacecraft components under large temperature differences, necessitate a strategy of first maintaining a low temperature within a single vacuum chamber, then breaking the vacuum and physically transferring the product to another independent high-temperature environment for heating. Afterwards, a high vacuum condition must be re-established to complete the entire test cycle. This series of operations inevitably disrupts the continuity of the vacuum environment, contradicting the natural environment where spacecraft operate under a constant high vacuum, thus affecting the realism and accuracy of the test.

[0041] like Figures 1 to 3 As shown, the main objective of this application is to provide a vacuum testing device to address the above-mentioned problems. This vacuum testing device is used to test a product 3 under test. The vacuum testing device includes a test housing and a movable structure 2 disposed within the test housing 1. The product 3 under test is detachably disposed on the movable structure 2. The movable structure 2 can move relative to the test housing 1 within the test housing 1 along the length direction of the test housing 1, thereby driving the product 3 under test to move along the length direction of the test housing 1. The test housing 1 has three zones, namely a cold zone, a transition zone, and a hot zone. A cold plate structure 4 and a hot plate structure 5 are disposed within the test housing 1. The cold plate structure 4 is disposed on one side of the test housing 1 to form a cold zone for cooling the product 3 under test. The hot plate structure 5 is disposed on the other side of the test housing 1 to form a hot zone for heating the product 3 under test.

[0042] The cold plate structure 4 includes a first heat sink 42 surrounding the inner wall of the test housing 1. A first cold plate 41 is positioned inside the first heat sink 42 at a location relatively far from the moving structure 2. The first cold plate 41 has a first bearing surface for supporting the product under test 3. A first protective element is also provided on the first bearing surface. The first protective element is made of thermally conductive silicone or graphite with a high thermal conductivity, and its thickness is 5mm. The first protective element enhances the heat transfer efficiency of the first cold plate 41 to the product under test 3 and also acts as a shock absorber when placing the product under test 3, preventing damage. The test measures the damage caused by direct contact between product 3 and the first cold plate 41. The first cold plate 41 has a first coolant flow channel, and the first heat sink 42 has a second coolant flow channel. The vacuum test apparatus also includes a cooling medium containment assembly and a controller. The cooling medium containment assembly includes a first containment chamber containing a refrigeration component. The refrigeration component stores the cooling medium and is used to cool the cooling medium. The outlet of the first containment chamber is connected to a first pipe, and a first pump is installed on the first pipe to introduce the cooling medium from the refrigeration component into the first pipe. The first pipe is also equipped with a heating element for selectively heating the cooling medium. The outlet end of the first pipe is connected to both a first coolant flow channel and a second coolant flow channel, for conveying the cooling medium into the first cold plate 41 and the first heat sink 42 to form a cold zone, thereby cooling the product 3 to be tested. The surface temperature range of the first cold plate 41 is between -80.0℃ and +150.0℃, and the temperature uniformity of the first cold plate 41 is less than or equal to 2.0℃. The inner surface of the first heat sink 42 is coated with a first black coating. The coating is used to simulate the background of outer space. The surface temperature of the first heat sink 42 is between -80.0℃ and +150.0℃, and the temperature uniformity is less than or equal to 2.0℃. The first pipe is sealed to the test shell 1 to ensure that the vacuum in the test shell 1 will not leak. When the temperature of the cooling medium is high, it needs to be cooled by the cooling component. When the temperature of the cooling medium is low, it needs to be heated by the heating component to keep the temperature of the cooling medium entering the first cold plate 41 within the range of -80.0℃ to +150.0℃.

[0043] Optionally, a temperature detection component is provided on the first cold plate 41 to detect the cold plate temperature of the first cold plate 41. The temperature detection component is connected to a controller, which is also connected to a refrigeration component and a heating component to control whether to use the refrigeration component to lower the temperature of the cooling medium or to use the heating component to raise the temperature of the cooling medium based on the temperature of the first cold plate 41.

[0044] When the temperature of the first cold plate 41 is greater than +150.0℃, the refrigeration components need to be activated to lower the temperature of the cooling medium. When the temperature of the first cold plate 41 is less than -80.0℃, the heating components need to be activated to heat the cooling medium so that the temperature of the cooling medium is between -80.0℃ and +150.0℃.

[0045] The hot plate structure 5 includes a second heat sink 52 surrounding the inner wall of the test housing 1. A second cold plate 51 is positioned inside the second heat sink 52, relatively away from the moving structure 2. The second cold plate 51 has a first bearing surface for supporting the product under test 3. A second protective component is also provided on the first bearing surface. The second protective component is made of thermally conductive silicone or graphite with a high thermal conductivity, and its thickness is 5mm. The second protective component enhances the heat transfer efficiency of the second cold plate 51 to the product under test 3 and also acts as a shock absorber when placing the product under test 3, preventing damage. The test measures the damage caused by direct contact between product 3 and the first cold plate 41. The second cold plate 51 has a third coolant flow channel, and the second heat sink 52 has a fourth coolant flow channel. The vacuum test apparatus also includes a heat-conducting medium containment assembly and a controller. The heat-conducting medium containment assembly includes a second containment chamber, within which a cooling component stores the heat-conducting medium and is used to cool it. The outlet of the second containment chamber is connected to a second pipe, on which a second pump is installed to introduce the heat-conducting medium from the cooling component into the second pipe. The second pipe is also equipped with a heating element for selectively heating the heat transfer medium. The outlet of the second pipe is connected to the third and fourth coolant channels, respectively, to deliver cooling medium into the second cold plate 51 and the second heat sink 52. This forms a cold zone through the second cold plate 51 and the second heat sink 52, thereby cooling the product 3 to be tested. The surface temperature range of the second cold plate 51 is between -80.0℃ and +150.0℃, and the temperature uniformity of the second cold plate 51 is less than or equal to 2.0℃. The inner surface of the second heat sink 52 is coated with a second black coating. The coating is used to simulate the background of outer space. The surface temperature of the second heat sink 52 is between -80.0℃ and +150.0℃, and the temperature uniformity is less than or equal to 2.0℃. The second pipe is sealed to the test shell 1 to ensure that the vacuum in the test shell 1 will not leak. When the temperature of the cooling medium is high, the heat transfer medium needs to be cooled by the refrigeration component. When the temperature of the cooling medium is low, the heat transfer medium needs to be heated by the heating component to keep the temperature of the cooling medium entering the second cold plate 51 within the range of -80.0℃ to +150.0℃.

[0046] Optionally, a temperature detection component is provided on the second cold plate 51 to detect the cold plate temperature of the second cold plate 51. The temperature detection component is connected to a controller, which is also connected to a refrigeration component and a heating component to control whether to use the refrigeration component to lower the temperature of the heat transfer medium or to use the heating component to raise the temperature of the heat transfer medium based on the temperature of the second cold plate 51.

[0047] When the temperature of the second cold plate 51 is greater than +150.0℃, the refrigeration components need to be activated to lower the temperature of the heat transfer medium. When the temperature of the second cold plate 51 is less than -80.0℃, the heating components need to be activated to increase the temperature of the heat transfer medium.

[0048] Among them, the first heat sink 42 and the second heat sink 52 are used to radiate heat up or radiate cool down the product 3 to be tested. Since the heat transfer by thermal radiation is inversely proportional to the square of the distance from the radiation source, no physical insulation is set in the transition zone. The transition zone mainly utilizes the short-distance attenuation characteristics of thermal radiation to weaken the heat transfer between the cold and hot zones and avoid thermal crosstalk.

[0049] The movable structure 2 includes a support member 21 disposed within the test housing 1, the extension direction of the support member 21 being consistent with the extension direction of the test housing 1. A movable component 22 is movably disposed on the support member 21. The support member 21 has meshing teeth 211. The movable component 22 includes a gear structure 223 meshing with the meshing teeth 211. The gear structure 223 is disposed on the movable body 221. A driving element 224 is also disposed on the movable body 221. The driving end of the driving element 224 is connected to the gear structure 223 to drive the gear structure 223 to rotate, thereby enabling the gear structure 223 to move on the support member 21. The device is designed for movement. A connecting component 222 is provided on the moving body 221. The connecting component 222 can be extended or shortened. A suspension component 225 is provided at the free end of the connecting component 222. The suspension component 225 has a suspension part. A drive motor is also provided on the moving body 221. The drive end of the drive motor is connected to one end of the connecting component 222. When the drive motor rotates forward or reverse, the connecting component 222 extends relative to the moving body 221. When the drive motor rotates in reverse or forward, the connecting component 222 shortens. This allows the device to place the product under test 3 in a cold or hot zone, or to move the product under test 3 away from the cold or hot zone.

[0050] Optionally, the driving element is a drive motor.

[0051] Optionally, the connecting component 222 is a rope, and the material of the connecting component 222 is a polytetrafluoroethylene braided rope with a temperature resistance range of -200℃ to +260℃. The extension and retraction of the connecting component 222 is 0.3 meters to 1 meter.

[0052] Optionally, the suspension unit may be made of 304 stainless steel.

[0053] The movable structure 2 also includes two limiting members, which are respectively located near the two ends of the support member 21 to limit the movement distance of the gear structure 223.

[0054] Optionally, the limiting component can be any one of a limiting shaft, a limiting post, or a limiting pin.

[0055] Optionally, laser displacement sensors are provided at the four corners of the product under test 3. The distance between the product under test 3 and the first cold plate 41 and the second cold plate 51 can be controlled by the laser displacement sensors.

[0056] Optionally, the heat transfer medium or cooling medium is heat transfer oil or cooling oil.

[0057] Furthermore, the vacuum testing device also includes a temperature detection component installed on the cold plate structure 4 to detect the cold plate temperature of the cold plate structure 4. Temperature detection is also installed on the product under test 3 and the hot plate structure 5 to detect the real-time temperature of the product under test 3 and the hot plate temperature of the hot plate structure 5, respectively.

[0058] The specific test procedure is as follows: The product under test 3 is fixed to the suspension component 225 via the suspension part, which is made of 304 stainless steel resistant to high and low temperatures, to ensure the stability of the product under test 3 during movement. The connecting component 222 (PTFE braided rope) is kept in the retracted state to prevent the product under test 3 from directly contacting the first cold plate 41 or the second cold plate 51 in its initial position. The test housing 1 is closed, and the high-vacuum pumping system is activated to evacuate the vacuum level inside the test housing 1 to ≤5×10⁻⁶. - 4 Pa ensures that the test environment meets the high vacuum conditions required for spacecraft in orbit.

[0059] The controller starts the drive motor, and through the cooperation of the gear structure 223 and the meshing teeth 211, the moving body 221 is precisely moved along the extension direction of the support component 21, positioning the product under test 3 on the first cold plate 41 in the cold zone. The laser displacement sensor monitors the distance between the product under test 3 and the first cold plate 41 to ensure that the product under test 3 is smoothly lowered to the set position and to avoid damage caused by direct contact.

[0060] The refrigeration components inside the first housing are activated, and the cooling medium is delivered to the first coolant channel through the first pump to cool the first cold plate 41. The second coolant channel of the first heat sink 42 also receives the cooling medium processed by the refrigeration components to ensure uniform temperature distribution.

[0061] The controller commands the drive motor to retract the connecting component 222, lifting the product under test 3 away from the first cold plate 41 while maintaining a safe distance of 10cm. Under the action of the gear structure 223 and the drive element 224, the moving body 221 quickly moves to the hot zone. The laser displacement sensor controls the product under test 3 to accurately descend onto the bearing surface of the second cold plate 51. In the hot zone, the heating component inside the second housing box is activated, and the heat transfer medium is delivered to the third coolant channel through the second pump body to heat the second cold plate 51. The fourth coolant channel of the second heat sink 52 also receives the heat transfer medium processed by the heating component to ensure uniform temperature in the hot zone.

[0062] The product under test 3 was subjected to a cyclic test between cold and hot zones. Each cycle included the holding time in the cold and hot zones, as well as the transition time between the two temperature ranges. During each cycle, the product under test 3 rapidly switched between the cold and hot zones via the moving structure 2, maintaining a temperature ≤6.65×10 throughout. -3 A high vacuum of Pa is achieved without the need to break the vacuum.

[0063] Through an independent hot and cold zone temperature control system, rapid temperature change of the product under test 3 between -80.0℃ and +150.0℃ was achieved, with a change time of no more than 3 minutes. This meets the requirements of GJB 1027A-2005 standard for rapid temperature change with large temperature difference. The transfer of the product under test 3 between the hot and cold zones does not require breaking the vacuum and maintains a high vacuum throughout the process, which more realistically simulates the on-orbit operating environment of spacecraft and improves the realism of the test and the accuracy of the data.

[0064] The linkage between the controller and the temperature detection component, drive motor, heating component, and cooling component enables the automation and intelligence of the testing process, reducing the time and errors of manual intervention, and improving testing efficiency and safety. The setting of the first and second protective components, as well as the cooperation between the laser displacement sensor and the suspension component, ensures the protection and positioning accuracy of the product during movement, avoiding damage caused by hard contact with the hot and cold plates.

[0065] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0066] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0067] In the description of this invention, it should be understood that the orientation or positional relationship indicated by directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" is generally based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing this invention and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this invention; the directional terms "inner" and "outer" refer to the inner and outer contours relative to the outline of each component itself.

[0068] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0069] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0070] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A vacuum testing apparatus for testing a product (3) to be tested, characterized in that, The vacuum testing apparatus includes: The test housing (1) and the moving structure (2) are provided. The product to be tested (3) is detachably disposed on the moving structure (2). The moving structure (2) is disposed inside the test housing (1). At least a portion of the moving structure (2) is movably disposed so as to drive the product to be tested (3) to move inside the test housing (1) through at least a portion of the moving structure (2). A cold plate structure (4) is provided inside the test housing (1) to form a cold zone for cooling the product to be tested (3); A hot plate structure (5) is disposed inside the test housing (1) to form a hot zone for heating the product to be tested (3); The cold plate structure (4) and the hot plate structure (5) are respectively disposed at both ends of the test housing (1), and the area between the cold plate structure (4) and the hot plate structure (5) in the test housing (1) forms a transition zone (6).

2. The vacuum testing apparatus according to claim 1, characterized in that, The cold plate structure (4) includes: A first cold plate (41) is disposed inside the test housing (1). The first cold plate (41) has a first bearing surface to bear the product to be tested (3) through the first bearing surface. A cooling medium containing assembly, at least a portion of which is used to contain coolant, the cooling medium containing assembly being disposed on one side of the test housing (1), the output end of which is used to communicate with the first cold plate (41) to deliver cooling medium into the first cold plate (41) to cool the product under test (3). The controller is electrically connected to the cooling medium containing assembly to adjust the cooling temperature of the coolant input into the first cold plate (41).

3. The vacuum testing apparatus according to claim 2, characterized in that, The cold plate structure (4) also includes: A first heat sink (42) is disposed inside the test housing (1) and surrounds the inner wall of the test housing (1). The first heat sink (42) is connected to the cooling medium receiving assembly and the controller to radiate cooling of the cold zone through the first heat sink (42). A first cold plate (41) is disposed on the side of the first heat sink (42) away from the moving structure (2). The inner surface of the first heat sink (42) is provided with a first black coating. And / or, The first protective component is disposed on the first bearing surface.

4. The vacuum testing apparatus according to claim 1, characterized in that, The hot plate structure (5) also includes: A second cold plate (51) is disposed inside the test housing (1). The second cold plate (51) has a second bearing surface to support the product to be tested (3) through the second bearing surface. A thermally conductive medium containing assembly, at least a portion of which is used to contain a thermally conductive medium, the thermally conductive medium containing assembly being disposed on one side of the test housing (1), the output end of which is used to communicate with the second cold plate (51) to deliver the thermally conductive medium into the second cold plate (51) to heat the product under test (3); The controller is electrically connected to the thermally conductive medium containing assembly to adjust the thermally conductive temperature of the thermally conductive medium input into the second cold plate (51).

5. The vacuum testing apparatus according to claim 4, characterized in that, The hot plate structure (5) also includes: A second heat sink (52) is disposed inside the test housing (1) and surrounds the inner wall of the test housing (1). The second heat sink (52) is connected to the heat-conducting medium receiving assembly and the controller to radiate heat to the hot zone through the second heat sink (52). The second cold plate (51) is disposed on the side of the second heat sink (52) away from the moving structure (2). A second black coating is disposed on the inner surface of the second heat sink (52). The second protective component is disposed on the second bearing surface.

6. The vacuum testing apparatus according to claim 1, characterized in that, The moving structure (2) includes: A support component (21) is disposed on the inner wall of the test housing (1) on the side away from the cold plate structure (4) and the hot plate structure (5); A movable component (22) is movably disposed on the support component (21), and the product to be tested (3) is disposed on the movable component (22); A controller, connected to the moving component (22), controls the moving component (22) to move within the test housing (1) along the extension direction of the support component (21) to drive the product under test (3) to switch between the cold zone and the hot zone.

7. The vacuum testing apparatus according to claim 6, characterized in that, The moving component (22) includes: The movable body (221) is movably mounted on the support member (21); A connecting component (222) is retractably mounted on the movable body (221); A suspension component (225) is disposed on the connecting component (222). The suspension component (225) has a suspension portion to control the extension of the connecting component (222) when a test is required, so as to place the product under test (3) on the suspension portion.

8. The vacuum testing apparatus according to claim 7, characterized in that, The support component (21) is provided with meshing teeth (211), and the moving component (22) further includes: A gear structure (223) is disposed on the movable body (221) and meshes with the meshing teeth (211); A driving element (224) is disposed on the movable body (221). The driving end of the driving element (224) is connected to the gear structure (223) to drive the gear structure (223) to move, so that the movable body (221) moves relative to the support member (21).

9. The vacuum testing apparatus according to claim 7, characterized in that, The movable structure (2) also includes two limiting members, which are respectively arranged close to the two ends of the support member (21) to limit the movement distance of the movable component (22).

10. The vacuum testing apparatus according to claim 1, characterized in that, The vacuum testing apparatus also includes: Temperature detection components are respectively installed on the cold plate structure (4), the hot plate structure (5) and the product under test (3) to detect the cold plate temperature of the cold plate structure (4), the hot plate temperature of the hot plate structure (5) and the real-time temperature of the product under test (3); Both the electrical connector and the temperature monitoring instrument are mounted on the test housing (1). The electrical connector is connected to the temperature detection component, and the temperature monitoring instrument is connected to the electrical connector to receive the cold plate temperature, the hot plate temperature, and the real-time temperature through the electrical connector.

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