Multi-environment coupling test and in-situ test analysis system and method for thermal control coating

Abstract

The invention relates to the technical field of space, in particular to a multi-environment coupling test and in-situ test analysis system and method for a thermal control coating. Comprising a vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test cavity, an XPS analysis test cavity and a thermal control performance test cavity. The three test cavities can be in a vacuum environment, and a sample can move in the three test cavities. According to the application, the state of the spacecraft during in-orbit operation is simulated more truly, and the influence of air on a test analysis result is greatly reduced, so that the test analysis accuracy of the structure and performance change of the thermal control coating in a space environment is improved.

Description

Technical Field

[0001] The present application relates to the field of space technology, and in particular to a multi-environment coupling test and in-situ test analysis system and method for thermal control coatings. Background Art

[0002] When a spacecraft is in orbit, it will be affected by a variety of environments at the same time, mainly radiation effects and high and low temperature cycle changes. Low-orbit spacecraft will also be affected by atomic oxygen.

[0003] When sunlight hits the surface of a spacecraft, it will cause some damage to the material. Since the ultraviolet wavelength is short and the photon energy is high, it is an important factor causing the performance degradation of the spacecraft. The energy in the ultraviolet band accounts for about 8.7% of the total solar irradiance, and its photon energy can break the covalent bonds of organic materials, making the materials brittle and causing performance degradation.

[0004] Atomic oxygen mainly exists in the low-orbit environment of 200 to 700 km and has strong oxidizing properties. When a spacecraft is operating in a low-orbit, atomic oxygen will collide with its surface materials with an energy of about 5eV and react, resulting in erosion. Organic polymer materials, carbon fiber composite materials, silver and other materials commonly used in spacecraft are susceptible to erosion by atomic oxygen and performance degradation.

[0005] The spacecraft operates alternately in the sunlight and shadow areas, and the temperature of its surface changes accordingly. Depending on the absorption capacity of sunlight energy and the heat radiation capacity, the temperature of the surface material generally varies between -100℃ and +100℃, and the range of variation may be larger in local locations. Due to the influence of the thermal expansion coefficient, the coating and other materials of the surface will also degrade in performance. Some organic materials will also become cold and brittle at lower temperatures, which will also affect their performance.

[0006] In summary, the materials on the surface of low-orbit spacecraft will be simultaneously affected by vacuum, ultraviolet radiation, atomic oxygen, and high and low temperature thermal cycles. Through prior art search, it was found that the publication number is CN101093228A, which discloses a method and device for simulating the composite environment of low-Earth orbit space. It is possible to conduct tests on the composite environment of atomic oxygen + ultraviolet + temperature cycle, but it is not possible to conduct performance tests and analyze the valence and structure of elements. The publication number is CN202211695405, which discloses an atomic oxygen-ultraviolet environment comprehensive simulation experimental device and its experimental method, which can conduct atomic oxygen + ultraviolet composite environment tests, and can also conduct spectral tests, but it is not possible to conduct high and low temperature cycle tests and analyze the valence and structure of material elements. When the above method conducts elemental state and structural test analysis of the material, the material must be directly exposed to the atmospheric environment during the transfer process, which will cause contamination to the surface elements to be analyzed on the material, affecting the accuracy of the analysis results. Therefore, it is necessary to design a test system that integrates atomic oxygen and ultraviolet radiation environment, high and low temperature environment, and vacuum environment, and can realize automatic transfer of materials in different vacuum environments, and can travel back and forth between the space environment simulation test chamber, thermal control performance test chamber, and XPS analysis chamber many times. This is of great significance for studying the structural evolution behavior and performance change laws of thermal control coating materials in a low-orbit environment. Summary of the invention

[0007] In response to the defects in the prior art, the present application provides a multi-environment coupling test and in-situ test and analysis system and method for thermal control coatings, which can realize the transfer of material samples in different vacuum cavities, and complete the testing and analysis of thermal control coating material samples in one system, avoiding exposure of material samples to the atmospheric environment, greatly reducing the impact of air on the test and analysis results, realizing in-situ test and analysis in space environment simulation tests of spacecraft thermal control coatings, and improving the accuracy of test and analysis.

[0008] To achieve the above objectives, this application provides the following technical solutions:

[0009] In the first aspect, the present application provides a multi-environment coupling test and in-situ test analysis system for thermal control coatings, including: a vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber, an XPS analysis test chamber and a thermal control performance test chamber, wherein:

[0010] The vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber is separated from the XPS analysis test chamber by a first gate valve, and the XPS analysis test chamber is separated from the thermal control performance test chamber by a second gate valve.

[0011] The vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber, the XPS analysis test chamber and the thermal control performance test chamber are provided with a conveying guide rail, and the conveying guide rail is used to transfer the material sample in the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber, the XPS analysis test chamber and the thermal control performance test chamber.

[0012] A first sample stage is arranged inside the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber, a second sample stage is arranged inside the XPS analysis test chamber, and a third sample stage is arranged inside the thermal control performance test chamber. The first sample stage, the second sample stage and the third sample stage are at the same horizontal position.

[0013] Furthermore, the vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber is used for one or more coupling tests among vacuum atomic oxygen test, ultraviolet test and thermal cycle test.

[0014] Furthermore, the maximum thermal cycle temperature of the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber is -180°C to 300°C.

[0015] Furthermore, the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber is also provided with an atomic oxygen source, a vacuum far ultraviolet source, a vacuum near ultraviolet source, and a high and low temperature circulation system, wherein the atomic oxygen source is connected to the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber through the central flange of the upper panel, the vacuum far ultraviolet source is connected to the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber through the right flange of the upper panel, and the vacuum near ultraviolet source is connected to the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber through the left flange of the upper panel; the left flange of the upper panel is arranged on the left side of the central flange of the upper panel at an angle of 25°, and the right flange of the upper panel is arranged on the right side of the central flange of the upper panel at an angle of 25°, so that the oxygen atomic beam and the ultraviolet beam converge together on the sample surface; the high and low temperature circulation system includes a resistance heating wire, a first liquid nitrogen cooling tank and a second liquid nitrogen cooling tank; the first liquid nitrogen cooling tank and the second liquid nitrogen cooling tank are respectively arranged on both sides of the first sample stage; the resistance heating wire is arranged below the first sample stage.

[0016] Furthermore, the XPS analysis test chamber is used for surface element valence state analysis and is also provided with an X-ray source, a sample inlet and a test control system.

[0017] Furthermore, the X-ray source is used to provide X-rays required for XPS analysis, the sample inlet is used to input test samples, and the test control system is used to monitor the test process.

[0018] Furthermore, the thermal control performance test chamber is provided with a solar absorption ratio test module and an emissivity test module, the solar absorption ratio test module is used for solar absorption ratio test, and the emissivity test module is used for emissivity test.

[0019] Furthermore, the ultimate vacuum degree of the vacuum atomic oxygen-ultraviolet-heat cycle coupling space environment test chamber and the thermal control performance test chamber is better than 10 -3 Pa, the vacuum degree of the XPS analysis test chamber is better than 10 -8 Pa.

[0020] In a second aspect, the present application also provides a multi-environment coupling test and in-situ test analysis method for a thermal control coating, using a multi-environment coupling test and in-situ test analysis system for a thermal control coating, including the following steps:

[0021] Step 1: Input the sample to be tested from the injection port and send it to the vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber through the conveyor rail.

[0022] Step 2: Turn on the vacuum system, and when the vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber is evacuated to a vacuum level better than 10-3Pa, turn on the atomic oxygen source, ultraviolet light source, and high and low temperature circulation system according to the test requirements to conduct a space environment simulation test;

[0023] Step 3: When the space environment simulation test reaches a predetermined dose, the atomic oxygen source, the ultraviolet light source, and the high and low temperature circulation system are turned off, the first gate valve is opened, and the sample to be tested is transferred to the XPS analysis test chamber through the manipulator and the transfer rail;

[0024] Step 4: evacuate the XPS analysis test chamber to a pressure better than 10-8 Pa, and perform XPS analysis on the sample to be tested;

[0025] Step 5: Open the second gate valve, and transfer the sample to be tested to the thermal control performance test chamber through the manipulator and the transfer rail;

[0026] Step 6: Testing the solar absorption ratio and emissivity of the sample to be tested;

[0027] Step 7: as needed, the sample to be tested is sent back to the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber, the space environment simulation test is continued, and steps 2 to 6 are repeated;

[0028] Step 8: After all tests and test analysis are completed, take out the sample to be tested, and implement multi-environment coupling test and in-situ test analysis of the sample.

[0029] The technical solution of this application has the following beneficial effects:

[0030] 1. The multi-environment coupling test and in-situ test and analysis system and method for thermal control coatings provided by this application integrate atomic oxygen and ultraviolet radiation environments, high and low temperature environments, and vacuum environments, and can realize the transfer of material samples in chambers with different vacuum degrees, ensuring that the material samples are always in an environment isolated from the outside atmosphere during the entire process of space environment simulation tests, performance tests, and XPS analysis, effectively isolating the test and analysis errors caused by air contamination of the samples. This application more realistically simulates the state of the spacecraft during in-orbit operation, greatly reducing the impact of air on the test and analysis results, thereby improving the test and analysis accuracy of the structure and performance changes of the thermal control coating in the space environment.

[0031] 2. The multi-environment coupling test and in-situ test and analysis system and method for the thermal control coating provided in this application can perform space environment simulation tests and test analyses repeatedly, which is of great significance for studying the structural evolution behavior and performance change laws of thermal control coating materials in a low-orbit environment.

[0032] 3. The multi-environment coupling test and in-situ test analysis system and method for thermal control coatings provided in this application can simultaneously carry out vacuum atomic oxygen-ultraviolet-thermal cycle coupling tests, and can also independently carry out single environmental simulation tests. It is easy to use and has comprehensive functions.

[0033] 4. The multi-environment coupling test and in-situ test and analysis system and method for thermal control coatings provided in this application can flexibly arrange tests and analyses, has strong scalability, and is easy to connect with other test and analysis equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] The drawings constituting a part of this application are used to provide a further understanding of this application, so that other features, purposes and advantages of this application become more obvious. The schematic embodiment drawings and their descriptions of this application are used to explain this application and do not constitute an improper limitation on this application. In the drawings:

[0035] Figure 1 is a schematic diagram of a multi-environment coupling test and in-situ test analysis system for a thermal control coating provided according to an embodiment of the present application;

[0036] Figure 2 It is a schematic diagram of the principle of a multi-environment coupling test and in-situ test analysis method for a thermal control coating provided in an embodiment of the present application;

[0037] In the figure:

[0038] 1- vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber, 11- first sample stage, 12- atomic oxygen source, 13- vacuum far ultraviolet source, 14- vacuum near ultraviolet source, 15- resistance heating wire, 16- first liquid nitrogen cooling tank, 17- second liquid nitrogen cooling tank;

[0039] 2-XPS analysis test chamber, 21-second sample stage, 22-X-ray source, 23-injection port;

[0040] 3- thermal control performance test chamber, 31- third sample stage, 32- solar absorption ratio test module, 33- emissivity test module;

[0041] 4- first gate valve;

[0042] 5- second gate valve;

[0043] 6-Transmission rail;

[0044] 7-Vacuum system. DETAILED DESCRIPTION

[0045] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present application.

[0046] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequential order. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present application described here. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device comprising a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0047] In the present application, the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings. These terms are mainly used to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation.

[0048] In addition, some of the above terms may be used to express other meanings in addition to indicating orientation or positional relationship. For example, the term "on" may also be used to express a certain dependency or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to specific circumstances.

[0049] In addition, the term "plurality" shall mean two or more.

[0050] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0051] like Figure 1 As shown, the present application provides a multi-environment coupling test and in-situ test analysis system for a thermal control coating, comprising a vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber 1, an XPS analysis test chamber 2 and a thermal control performance test chamber 3; the vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber 1 and the XPS analysis test chamber 2 are separated by a first plug valve 4, and the XPS analysis test chamber 2 and the thermal control performance test chamber are separated by a second plug valve 5; a conveying guide rail 6 is provided inside the vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber 1, the XPS analysis test chamber 2 and the thermal control performance test chamber 3.

[0052] Furthermore, a first sample stage 11 is arranged inside the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber 1, a second sample stage 21 is arranged inside the XPS analysis test chamber 2, and a third sample stage 31 is arranged inside the thermal control performance test chamber 3; the first sample stage 11, the second sample stage 21 and the third sample stage 31 are at the same horizontal position.

[0053] Furthermore, the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber 1 is also provided with an atomic oxygen source 12, a vacuum far ultraviolet source 13, a vacuum near ultraviolet source 14, and a high and low temperature circulation system; the atomic oxygen source 12 is connected to the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber 1 through the central flange of the upper panel, the vacuum far ultraviolet source 13 is connected to the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber 1 through the right flange of the upper panel, and the vacuum near ultraviolet source 14 is connected to the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber 1 through the left flange of the upper panel; the left flange of the upper panel is arranged on the left side of the central flange of the upper panel at an angle of 25°, and the right flange of the upper panel is arranged on the right side of the central flange of the upper panel at an angle of 25°, so that the oxygen atomic beam and the ultraviolet beam converge on the sample surface together.

[0054] Furthermore, the high and low temperature circulation system includes a resistance heating wire 15, a first liquid nitrogen cooling tank 16 and a second liquid nitrogen cooling tank 17; the first liquid nitrogen cooling tank 16 and the second liquid nitrogen cooling tank 17 are respectively arranged on both sides of the first sample stage 11; the resistance heating wire 15 is arranged below the first sample stage 11.

[0055] Furthermore, the XPS analysis test chamber 2 is also provided with a sample inlet 23, an X-ray source 22 and a test control system.

[0056] Furthermore, the thermal control performance test chamber 3 is also provided with a solar absorption ratio test module 32 and an emissivity test module 33 .

[0057] Furthermore, the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber 1 is used for single tests among vacuum atomic oxygen test, ultraviolet test and thermal cycle test or coupled tests of these tests; the XPS analysis test chamber 2 is used for surface element valence state analysis; the thermal control performance test chamber 3 is used for solar absorption ratio-emissivity test; the conveying guide rail 6 is arranged inside the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber 1, the XPS analysis test chamber 2 and the thermal control performance test chamber 3, and is used to transfer material samples among the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber 1, the XPS analysis test chamber 2 and the thermal control performance test chamber 3.

[0058] Furthermore, the multi-environment coupling test and in-situ test analysis system for the thermal control coating provided in the embodiment of the present application further includes a vacuum pumping system 7 for the vacuum environment of the vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber 1, the XPS analysis test chamber 2 and the thermal control performance test chamber 3; the ultimate vacuum degree of the vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber 1 and the thermal control performance test chamber 3 is better than 10 -3 Pa, the vacuum degree of XPS test chamber 2 is better than 10 -8 Pa can more realistically simulate the state of a spacecraft when it is in orbit, greatly reducing the impact of air on the test and analysis results, thereby improving the accuracy of the test and analysis of the structure and performance changes of thermal control coatings in a space environment.

[0059] Specifically, the multi-environment coupling test and in-situ test and analysis system for the thermal control coating provided in the embodiment of the present application integrates atomic oxygen and ultraviolet radiation environment, high and low temperature environment, and vacuum environment, and can realize the transfer of material samples in chambers with different vacuum degrees, ensuring that the material samples are always in an environment isolated from the external atmosphere throughout the entire process of space environment simulation test, performance test and XPS analysis, effectively isolating the test and analysis errors caused by air contamination of the samples.

[0060] In addition, if Figure 2As shown, the embodiment of the present application also provides a method for a multi-environment coupling test and an in-situ test analysis system using a thermal control coating, comprising the following steps:

[0061] Step 1: Input the sample to be tested from the sample inlet 23 and send it to the vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber 1 through the conveying guide rail 6.

[0062] Step 2: Turn on the vacuum system 7 and evacuate the vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber 1 to a temperature better than 10 -3 At Pa, the atomic oxygen source 12, the vacuum far ultraviolet source 13, the vacuum near ultraviolet source 14, the resistance heating wire 15, the first liquid nitrogen cooling tank 16, and the second liquid nitrogen cooling tank 17 are turned on according to the test requirements to carry out a space environment simulation test;

[0063] Step 3: When the space environment simulation test reaches a predetermined dose, turn off the atomic oxygen source 12, the vacuum far ultraviolet source 13, the vacuum near ultraviolet source 14, the resistance heating wire 15, the first liquid nitrogen cooling tank 16, and the second liquid nitrogen cooling tank 17, open the first gate valve 4, and transfer the sample to the XPS analysis test chamber 2 through the manipulator and the transfer guide rail 6;

[0064] Step 4: Evacuate the XPS analysis test chamber 2 to a vacuum better than 10 -8 Pa, XPS analysis of samples;

[0065] Step 5: Open the second gate valve 5 and transfer the sample to the thermal control performance test chamber 3 through the manipulator and the transfer rail 6;

[0066] Step 6: Test the solar absorption ratio and emissivity of the sample;

[0067] Step 7: As needed, the sample is sent back to the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber 1 to continue the space environment simulation test, and steps 2 to 7 are repeated;

[0068] Step 8: After all tests and test analysis are completed, take out the samples to carry out multi-environment coupling tests and in-situ test analysis of the samples.

[0069] The embodiment of the present application integrates atomic oxygen and ultraviolet radiation environment, high and low temperature environment, and vacuum environment, realizes the transfer of material samples in chambers with different vacuum degrees, ensures that the material samples are always in an environment isolated from the outside atmosphere during the entire process of space environment simulation test, performance test and XPS analysis, effectively isolates the test and analysis errors caused by air contamination of the sample, more realistically simulates the state of the spacecraft during orbital operation, greatly reduces the impact of air on the test and analysis results, and thus improves the test and analysis accuracy of the structure and performance changes of the thermal control coating in the space environment. The embodiment of the present application can repeatedly perform space environment simulation tests, XPS analysis and performance tests, is flexible and convenient, has strong scalability, and is easy to connect and use with other test and analysis equipment.

[0070] The above description is only the preferred embodiment of the present application and is not intended to limit the present application. For those skilled in the art, the present application may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A multi-environment coupling test and in-situ test analysis system for thermal control coatings. include: Vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber, XPS analysis test chamber and thermal control performance test chamber, among which, The vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber is separated from the XPS analysis test chamber by a first gate valve, and the XPS analysis test chamber is separated from the thermal control performance test chamber by a second gate valve. The vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber, the XPS analysis test chamber and the thermal control performance test chamber are provided with a conveying guide rail, and the conveying guide rail is used to transfer the material sample in the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber, the XPS analysis test chamber and the thermal control performance test chamber. A first sample stage is provided inside the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber, a second sample stage is provided inside the XPS analysis test chamber, and a third sample stage is provided inside the thermal controllable solar absorption ratio-emissivity test chamber. The first sample stage, the second sample stage and the third sample stage are at the same horizontal position.

2. The multi-environment coupling test and in-situ test analysis system for thermal control coatings according to claim 1, It is characterized in that The vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber is used for a vacuum atomic oxygen test, an ultraviolet test, a thermal cycle test, or a coupling test of multiple tests.

3. The multi-environment coupling test and in-situ test analysis system for thermal control coatings according to claim 1, It is characterized in that The maximum thermal cycle temperature of the vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber is -180°C to 300°C.

4. The multi-environment coupling test and in-situ test analysis system for thermal control coatings according to claim 1, It is characterized in that The vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber is also provided with an atomic oxygen source, a vacuum far ultraviolet source, a vacuum near ultraviolet source, and a high and low temperature circulation system, wherein the atomic oxygen source is connected to the vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber through the central flange of the upper panel, the vacuum far ultraviolet source is connected to the vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber through the right flange of the upper panel, and the vacuum near ultraviolet source is connected to the vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber through the left flange of the upper panel; the left flange of the upper panel is arranged on the left side of the central flange of the upper panel at an angle of 25°, and the right flange of the upper panel is arranged on the right side of the central flange of the upper panel at an angle of 25°, so that the oxygen atomic beam and the ultraviolet beam converge together on the sample surface; the high and low temperature circulation system includes a resistance heating wire, a first liquid nitrogen cooling tank and a second liquid nitrogen cooling tank; the first liquid nitrogen cooling tank and the second liquid nitrogen cooling tank are respectively arranged on both sides of the first sample stage; the resistance heating wire is arranged below the first sample stage.

5. The multi-environment coupling test and in-situ test analysis system for thermal control coatings according to claim 1, It is characterized in that The XPS analysis test chamber is used for surface element valence state analysis and is also provided with an X-ray source, a sample inlet and a test control system.

6. The multi-environment coupling test and in-situ test analysis system for thermal control coatings according to claim 1, It is characterized in that The thermal control performance test chamber is used for solar absorption ratio-emissivity test, and is also provided with a solar absorption ratio test module and an emissivity test module. The solar absorption ratio test module is used for solar absorption ratio test, and the emissivity test module is used for emissivity test.

7. The multi-environment coupling test and in-situ test analysis system for thermal control coatings according to claim 1, It is characterized in that The ultimate vacuum degree of the vacuum atomic oxygen-ultraviolet-heat cycle coupling space environment test chamber and the thermal control performance test chamber is better than 10 -3 Pa, the vacuum degree of the XPS analysis test chamber is better than 10 -8 Pa.

8. A multi-environment coupling test and in-situ test analysis method for thermal control coatings. It is characterized in that The multi-environment coupling test and in-situ test analysis system for the thermal control coating according to any one of claims 1 to 8 comprises the following steps: Step 1: Input the sample to be tested from the injection port and send it to the vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber through the conveyor rail. Step 2: Turn on the vacuum system and evacuate the vacuum atomic oxygen-ultraviolet-thermal cycle coupling space environment test chamber to a vacuum better than 10 -3 At Pa, the atomic oxygen source, ultraviolet light source, and high and low temperature circulation system are turned on according to the test requirements to conduct a space environment simulation test; Step 3: When the space environment simulation test reaches a predetermined dose, the atomic oxygen source, the ultraviolet light source, and the high and low temperature circulation system are turned off, the first gate valve is opened, and the sample to be tested is transferred to the XPS analysis test chamber through the manipulator and the transfer rail; Step 4: evacuate the XPS analysis test chamber to a pressure better than 10-8 Pa, and perform XPS analysis on the sample to be tested; Step 5: Open the second gate valve, and transfer the sample to be tested to the thermal control performance test chamber through the manipulator and the transfer rail; Step 6: Testing the solar absorption ratio and emissivity of the sample to be tested; Step 7: as needed, the sample to be tested is sent back to the vacuum atomic oxygen-ultraviolet-thermal cycle coupled space environment test chamber, the space environment simulation test is continued, and steps 2 to 6 are repeated; Step 8: After all tests and test analysis are completed, take out the sample to be tested to implement multi-environment coupling test and in-situ test analysis of the sample.

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