A large temperature change environment space solar cell piece electric performance test cavity

Abstract

The application discloses a kind of big temperature change environment space solar cell piece electric performance test cavity, including AM0 light source incidence module, heat radiation protection module, vacuum cavity module, vacuum suction platform module, cooling circulating water module, low temperature module, high temperature module;The heat radiation protection module is installed with AM0 light source incidence glass, for passing through light source;Heat radiation protection module includes heat radiation protection plate;The heat radiation protection plate is installed in the outside of AM0 light source incidence glass;The vacuum cavity module is used to place vacuum suction platform module;The cooling circulating water module is used to control the heating rate of cell piece;The low temperature module is used to cool the vacuum cavity;The high temperature module is used to heat the vacuum cavity.The application can simulate deep space extremely low and extremely high temperature environment, meet the test demand of space solar cell in specific temperature or vacuum continuous temperature change electric performance data;Through vacuum suction, prevent cell piece displacement, can improve electric performance test data stability.

Description

Technical Field

[0001] This invention belongs to the field of space solar cell testing technology, specifically relating to a test chamber for the electrical performance of space solar cells in a large temperature variation environment. Background Technology

[0002] With the rapid development of my country's aerospace technology, the demand for spacecraft and satellites for deep space exploration missions to Jupiter, Mars, Saturn, and other planets is increasing. However, the space environment for deep space exploration missions is extremely complex, characterized by low light intensity, extremely low temperatures, and extremely high temperatures. Solar arrays provide energy to satellites and are an important component of them. Therefore, accurately calculating the electrical performance of solar arrays in the space environment during deep space exploration missions is crucial, which places high demands on the electrical performance testing of space solar cells in environments with large temperature variations.

[0003] Currently, the electrical performance testing of conventional Earth-orbiting satellite solar arrays on the ground mainly uses the AM0 solar simulator at room temperature. However, compared to Earth orbit, the deep space environment has extreme temperatures and extremely low light intensity. Under these extreme temperature and low light conditions, the electrical performance parameters of solar cells differ significantly from those in conventional Earth orbit. Therefore, the electrical performance testing methods for conventional Earth-orbiting satellite solar arrays cannot meet the increasingly urgent demand for testing solar cells in deep space exploration satellites. Currently, there are no dedicated testing chambers or equipment for deep space exploration solar cells, making it impossible to conduct electrical performance testing simulating the space environment. The design calculations for deep space exploration satellite solar cell circuits can only refer to the electrical performance test data of conventional Earth-orbiting satellites. This not only leads to inaccurate power design data for deep space exploration satellites but also risks overestimating the power generation performance of space solar cells, potentially causing deep space exploration mission failures. This severely limits the country's development in the field of deep space exploration satellites.

[0004] Therefore, there is an urgent need to develop a space solar cell electrical performance testing chamber that can be used in deep space exploration under large temperature variation environments. This chamber can simulate the deep space environment on the ground and perform electrical performance testing of solar cells under extreme temperatures or different light conditions, laying a technical foundation for the engineering implementation of missions to traverse the Jupiter system and other planets. Summary of the Invention

[0005] To address the aforementioned issues, this invention provides a space solar cell electrical performance testing chamber for a large temperature variation environment. This chamber can provide extremely low and extremely high vacuum temperatures. When a space solar cell is placed inside the testing chamber, its electrical performance can be tested under any vacuum temperature condition within the temperature range of -260℃ to +500℃, thus meeting the requirements for electrical performance data of space solar cells under specific temperatures or continuous vacuum temperature variations.

[0006] The specific technical solution of this invention is as follows:

[0007] A test chamber for the electrical performance of solar cells in a large temperature variation environment, the test chamber comprising an AM0 light source incident module, a thermal radiation protection module, a vacuum chamber module, a vacuum adsorption platform module, a cooling circulating water module, a low temperature module 6, and a high temperature module 7;

[0008] The thermal radiation protection module is equipped with an AM0 light source incident glass 2, which is used to transmit light sources.

[0009] The thermal radiation protection module includes a thermal radiation protection plate 1. The thermal radiation protection plate 1 is installed on the outside of the AMO light source incident glass 2 and can rotate horizontally 360 degrees. It is used to insulate the test chamber, preventing the chamber temperature from dropping during heating and preventing the temperature from rising during cooling due to direct AMO light source irradiation. The thermal radiation protection plate is only rotated horizontally away when testing battery electrical performance. After testing, the thermal radiation protection plate is returned to its original position, covering the vacuum chamber, thus avoiding battery performance degradation caused by prolonged direct AMO light source irradiation.

[0010] The vacuum chamber module is used to house the vacuum adsorption platform module; the vacuum adsorption platform module provides a platform for the battery cell under test to be placed horizontally for electrical performance testing;

[0011] The cooling circulating water module 5 controls the heating rate of the battery cells by controlling the circulating water flow rate.

[0012] The cryogenic module 6 is used to cool the vacuum chamber 3;

[0013] The high-temperature module 7 is used to heat the vacuum chamber 3.

[0014] The vacuum chamber module includes a vacuum chamber 3, a vacuum chamber evacuation air path 31, a molecular pump 32, a mechanical pump 33, and a vacuum sensor 34.

[0015] The air density sensor 34 and the vacuum chamber evacuation air circuit 31 are installed inside the vacuum chamber module;

[0016] The vacuum mechanical pump 33 and the molecular pump 32 are installed outside the vacuum chamber module;

[0017] The vacuum chamber evacuation air path 31 is connected to the vacuum mechanical pump 33 and molecular pump 32 through the vacuum air sealing valve on the vacuum chamber module. By evacuating the vacuum chamber 3, the chamber can be cooled or heated to simulate the vacuum environment with large temperature variation.

[0018] The vacuum adsorption platform module includes a vacuum adsorption platform 4;

[0019] The vacuum adsorption platform 4 is equipped with a test fixture 41, a four-probe test circuit 42, a light intensity calibration standard battery cell 43, a sample test platform 44, and a test fixture 47; the vacuum adsorption platform 4 is equipped with a temperature sensor 46 and a vacuum air evacuation channel 45.

[0020] There are four back electrode plate clamps 41, which are located at the four corners of the vacuum adsorption platform 4 and are used to fix the back electrode plate that supports the battery cell.

[0021] The four-probe test circuit 42 is used to transmit test data, including electrode contact probes and leads of the battery cell under test.

[0022] The light intensity calibration standard solar cell 43 is used to calibrate the standard light intensity. It is installed on one side of the vacuum adsorption platform 4, and its height is consistent with that of the sample testing platform 44. The light intensity calibration standard solar cell 43 includes one standard solar cell.

[0023] The sample testing platform 44 fixes the battery cell to be tested by vacuum adsorption to prevent displacement; the surface material of the sample testing platform 44 is gold, and the thickness of the gold layer is 1-1000um; more preferably 10-200um; more preferably 80um.

[0024] The vacuum adsorption platform vacuum circuit 45 is connected to the vacuum mechanical pump 33 outside the test chamber through a vacuum airtight valve on the vacuum chamber module; the vacuum chamber module and the vacuum adsorption platform module share the vacuum mechanical pump 33 outside the test chamber.

[0025] The test fixture 47 is used to fix the N end of the battery cell during testing; the spacing of the test fixture 47 can be adjusted according to the electrodes of different battery cell specifications; more preferably, the battery cell sizes that can be used for testing include: 40mm*60mm, 40mm*40mm, 40mm*80mm, 20mm*40mm, 40mm*90mm, and 67mm*145mm.

[0026] The back electrode plate clamp 41 is fixed by tightening and can be used for electrical performance testing of flexible rolled batteries or irregularly shaped batteries; the back electrode plate clamp 41 can be adjusted horizontally and vertically according to the outer shape of the back electrode plate; the back electrode plate clamp 41 can test battery cells with short side length ranging from 1 to 200 mm, long side length ranging from 1 to 200 mm, and vertical thickness ranging from 1 to 50 mm.

[0027] The cooling circulating water passage 5 is installed below the high-temperature module 7 of the vacuum adsorption platform 4 and is used to cool the sample testing platform 44.

[0028] The cooling circulating water module 5 controls the heating rate of the battery cells by controlling the circulating water flow rate. The heating rate is controlled between 0.1℃ / min and +10℃ / min, and more preferably 2℃ / min.

[0029] The cryogenic module 6 is used to cool the vacuum chamber 3 and includes a gas compressor 61 and a liquid helium circulation path 62.

[0030] The liquid helium circulation gas path 62 is installed inside the vacuum chamber 3 to enable the reusability of liquid helium gas; the liquid helium gas compressor 61 can achieve low temperatures of 5K, 15K, and 55K; preferably, the low temperature of 55K is selected.

[0031] The high-temperature module 7 is used to heat the vacuum chamber 3, with a temperature range of 0℃ to +500℃, preferably 40℃ to 200℃.

[0032] The heat radiation protection plate 1 is a metal plate that is black on both sides; preferably, the metal plate is an aluminum plate or a steel plate.

[0033] Furthermore, the solar cell under test refers to a gallium arsenide solar cell.

[0034] Furthermore, the AM0 light source incident glass 2 is made of high-strength fused silica glass, preferably high-strength fused silica glass with ultraviolet radiation grade.

[0035] Compared with the prior art, the beneficial effects achieved by the present invention are as follows:

[0036] (1) Through this invention, the extremely low and extremely high temperature environment of deep space can be simulated on the ground. The battery cell to be tested is placed in the test chamber, and the electrical performance test of the battery cell can be realized under any temperature condition in the temperature range of -260℃ to +500℃. It can meet the needs of electrical performance data of space solar cells under specific temperature or vacuum continuous temperature variation, and avoids excessive data deviation caused by theoretical derivation.

[0037] (2) Vacuum adsorption can be used to test the electrical performance of flexible batteries. The calibration module can be used to test the electrical performance of the battery cells under different light intensities. The fused silica glass AMO light source incident module can minimize the loss of incident light and make the test data more accurate.

[0038] (3) Vacuum adsorption is used to fix the battery cells to prevent the battery cells from shifting during the test and causing inaccurate test data. This can improve the consistency, stability and repeatability of electrical performance test data, and further improve the accuracy of test data. Attached Figure Description

[0039] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0040] Figure 1 This is a schematic diagram of the electrical performance testing cavity for solar cells in a large temperature variation environment according to the present invention.

[0041] In the diagram: 1 is the thermal radiation protection plate; 2 is the AM0 light source incident glass; 3 is the vacuum chamber; 31 is the vacuum chamber evacuation air path; 32 is the molecular pump; 33 is the mechanical pump; 34 is the vacuum degree sensor; 4 is the vacuum adsorption platform; 41 is the back electrode plate fixture; 42 is the four-probe test probe; 43 is the light intensity calibration standard battery cell; 44 is the sample test platform; 45 is the vacuum adsorption platform evacuation air path; 46 is the temperature sensor; 47 is the test fixture; 5 is the cooling circulating water path; 6 is the low temperature module; 61 is the gas compressor; 62 is the liquid helium circulating gas path; 7 is the high temperature module. Detailed Implementation

[0042] The following specific examples illustrate the implementation of the present invention. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present invention.

[0043] It should be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of the present invention. Therefore, the drawings only show the components related to the present invention and are not drawn according to the actual number, shape and size of the components in the actual implementation. In the actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0044] The following is in conjunction with the appendix Figure 1 The present invention will be described in further detail below.

[0045] A test chamber for the electrical performance of solar cells in a high-temperature-varying environment, such as Figure 1 As shown, the test chamber includes an AM0 light source incident module, a thermal radiation protection module, a vacuum chamber module, a vacuum adsorption platform module, a cooling circulating water module, a low temperature module 6, and a high temperature module 7.

[0046] The thermal radiation protection module is equipped with an AM0 light source incident glass 2, which is used to transmit light sources.

[0047] The thermal radiation protection module includes a thermal radiation protection plate 1. The thermal radiation protection plate 1 is installed on the outside of the AMO light source incident glass 2 and can rotate horizontally 360 degrees. It is used for heat preservation of the test chamber, preventing the temperature of the vacuum chamber module from decreasing during heating, and simultaneously preventing the temperature inside the vacuum chamber module from rising due to direct irradiation by the AMO light source during cooling. The thermal radiation protection plate 1 is only rotated horizontally away when testing the battery's electrical performance. After the test, the thermal radiation protection plate 1 is returned to its original position, covering the vacuum chamber module, thus avoiding battery performance degradation caused by prolonged direct irradiation by the AMO light source.

[0048] The vacuum chamber module is used to house the vacuum adsorption platform module; the vacuum adsorption platform module provides a platform for the battery cell under test to be placed horizontally for electrical performance testing;

[0049] The cooling circulating water passage 5 controls the heating rate of the battery cell under test by controlling the circulating water flow rate.

[0050] The cryogenic module 6 is used to cool the vacuum chamber module;

[0051] The high-temperature module 7 is used to heat the vacuum chamber module.

[0052] The vacuum chamber module includes a vacuum chamber 3, a vacuum chamber evacuation air path 31, a molecular pump 32, a mechanical pump 33, and a vacuum degree sensor 34.

[0053] The vacuum sensor 34 and the vacuum chamber evacuation air path 31 are installed inside the vacuum chamber module;

[0054] The mechanical pump 33 and the molecular pump 32 are installed outside the vacuum chamber module;

[0055] The vacuum chamber evacuation circuit 31 is connected to the mechanical pump 33 and the molecular pump 32 through the vacuum airtight valve on the vacuum chamber module. By evacuating the vacuum chamber 3 and simultaneously cooling or heating the chamber, the simulation of a vacuum environment with large temperature variations can be achieved.

[0056] The vacuum adsorption platform module includes a vacuum adsorption platform 4;

[0057] The vacuum adsorption platform 4 is equipped with a back electrode plate clamp 41, a four-probe test probe 42, a light intensity calibration standard battery cell 43, a sample test platform 44, and a test clamp 47; the vacuum adsorption platform 4 is equipped with a temperature sensor 46 and a vacuum adsorption platform vacuum air evacuation channel 45.

[0058] There are four back electrode plate clamps 41, which are located at the four corners of the vacuum adsorption platform 4 and are used to fix the back electrode plate that holds the battery cell to be tested.

[0059] The four-probe test probe 42 is used to transmit test data, including the electrode contact probe and lead wire of the battery cell under test.

[0060] The light intensity calibration standard solar cell 43 is used to calibrate the standard light intensity. It is installed on one side of the vacuum adsorption platform 4, and its height is consistent with that of the sample testing platform 44. The light intensity calibration standard solar cell 43 includes one standard solar cell.

[0061] The sample testing platform 44 fixes the battery cell to be tested by vacuum adsorption to prevent displacement; the surface material of the sample testing platform 44 is gold, and the thickness of the gold layer is 1-1000um; more preferably 10-200um; more preferably 80um.

[0062] The vacuum adsorption platform vacuum path 45 is connected to the mechanical pump 33 outside the test chamber through a vacuum airtight valve on the vacuum chamber module; the vacuum chamber module and the vacuum adsorption platform module share the mechanical pump 33 outside the test chamber.

[0063] The test fixture 47 is used to fix the N end of the battery cell during testing; the spacing of the test fixture 47 can be adjusted according to the electrodes of different battery cell specifications; more preferably, the battery cell sizes that can be used for testing include: 40mm*60mm, 40mm*40mm, 40mm*80mm, 20mm*40mm, 40mm*90mm, and 67mm*145mm.

[0064] The back electrode plate clamp 41 is fixed by tightening and can be used for electrical performance testing of flexible rolled batteries or irregularly shaped batteries; the back electrode plate clamp 41 can be adjusted horizontally and vertically according to the outer shape of the back electrode plate; the back electrode plate clamp 41 can test battery cells with short side length ranging from 1 to 200 mm, long side length ranging from 1 to 200 mm, and vertical thickness ranging from 1 to 50 mm.

[0065] The cooling circulating water passage 5 is installed below the high-temperature module 7 of the vacuum adsorption platform 4 and is used to cool the sample testing platform 44.

[0066] The cooling circulating water module 5 controls the heating rate of the battery cells by controlling the circulating water flow rate. The heating rate is controlled between 0.1℃ / min and +10℃ / min, and more preferably 2℃ / min.

[0067] The cryogenic module 6 is used to cool the vacuum chamber 3 and includes a gas compressor 61 and a liquid helium circulation path 62.

[0068] The liquid helium circulation gas path 62 is installed inside the vacuum chamber 3 to enable the reusability of liquid helium gas; the liquid helium gas compressor 61 can achieve low temperatures of 5K, 15K, and 55K; preferably, the low temperature of 55K is selected.

[0069] The high-temperature module 7 is used to heat the vacuum chamber 3, with a temperature range of 0℃ to +500℃, preferably 40℃ to 200℃.

[0070] The heat radiation protection plate 1 is a metal plate that is black on both sides; preferably, the metal plate is an aluminum plate or a steel plate.

[0071] Furthermore, the solar cell under test refers to a gallium arsenide solar cell.

[0072] Furthermore, the AM0 light source incident glass 2 is made of high-strength fused silica glass, preferably high-strength fused silica glass with ultraviolet radiation grade.

[0073] use Figure 1 The diagram shows a test chamber for the electrical performance of solar cells in a high-temperature-varying environment. The specific process is as follows:

[0074] S1. Rotate the heat radiation protection plate 1 180 degrees horizontally, flip up the AM0 light source incident glass 2, open the vacuum chamber module, and place the gallium arsenide solar cell to be tested (40mm*60mm) onto the sample testing platform 44 of the inner vacuum adsorption platform 4.

[0075] S2. Contact the P-end of the solar cell to be tested with the sample test platform 44. Use the test fixture 47 to clamp the gallium arsenide solar cell to ensure that the cell does not shift. Contact the N-end electrode of the solar cell with the four-probe test probe 42. Check and confirm that the light intensity calibration standard solar cell 43 and the sample to be tested are on the same platform.

[0076] S3. Start the mechanical pump 33, check and confirm that the sample to be tested is adsorbed on the sample test platform 44 by the vacuum adsorption platform through the vacuum adsorption platform vacuum air path 45, cover the AM0 light source incident glass 2 downwards to close the vacuum chamber 3, rotate 180 degrees horizontally to close the heat radiation protection plate 1 on the outside of the AM0 light source incident glass 2.

[0077] S4. Open the cooling circulating water passage 5 and use circulating water to cool down the sample testing platform 44. The temperature of the sample testing platform 44 is monitored in real time by the temperature sensor 46. The vacuum chamber 3 reaches a low vacuum environment of less than 5000Pa through the vacuum chamber vacuum air passage 31. The molecular pump 32 is turned on and the vacuum degree of the vacuum chamber 3 is monitored in real time by the vacuum degree sensor 34 built into the vacuum chamber 3.

[0078] S5. Turn on the high-temperature module 7, set the heating rate to 2℃ / min, and when it reaches 60℃, turn on the AM0 solar simulator. Rotate the heat radiation protection plate 1 180 degrees horizontally to open it, and start the test equipment to test the IV electrical performance characteristics of the sample at 60℃. Rotate the heat radiation protection plate 1 180 degrees horizontally back to close it and cover the outside of the AM0 light source incident glass 2. Continue heating to 80℃, 100℃, 120℃, 140℃, and 200℃, and repeat the operation method of this step to continue testing the IV electrical performance characteristics of the sample at different high temperatures.

[0079] S6. Turn off the high-temperature module 7, turn on the liquid helium gas compressor 61, turn on the low-temperature module 6, and maintain continuous cooling through the liquid helium circulation gas path 62. Monitor the temperature of the sample test platform 44 in real time through the temperature sensor 46. When the temperature reaches -60℃, turn on the AM0 solar simulator, rotate the heat radiation protection plate 1 180 degrees horizontally to open it, start the test equipment to test the IV electrical performance characteristics of the sample under test at -60℃, rotate the heat radiation protection plate 1 180 degrees horizontally back to close it and cover the outside of the AM0 light source incident glass 2; continue to cool down to -80℃, -100℃, -120℃, and -140℃, and repeat the operation method of this step to continue testing the IV electrical performance characteristics of the sample under test at different low temperatures.

[0080] This invention provides a space solar cell electrical performance testing chamber for a large temperature variation environment, enabling the simulation of space environments with extremely low and high temperatures. By placing the solar cell under test within this chamber, electrical performance testing can be conducted at any vacuum temperature within the range of -260℃ to +500℃. This meets the requirements for electrical performance data of space solar cells under specific temperatures or continuous vacuum temperature variations, avoiding excessive data deviations caused by theoretical derivations. This invention develops a space solar cell electrical performance testing chamber device suitable for deep space exploration in a large temperature variation environment. It not only solves the problem of the lack of electrical performance testing methods for solar cells under extreme temperatures and extremely low light intensity environments in deep space, but also, by simulating the deep space environment, accurately calculates the electrical performance of solar cell arrays in deep space exploration missions, obtaining accurate cell temperatures and test loss factors. This effectively improves the accuracy of power design data for deep space exploration satellites and enhances the ability of solar cells to withstand extreme space temperature environments.

[0081] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A test chamber for the electrical performance of solar cells in a large temperature variation environment, characterized in that, The test chamber includes an AM0 light source incident module, a thermal radiation protection module, a vacuum chamber module, a vacuum adsorption platform module, a cooling circulating water module, a low temperature module (6), and a high temperature module (7); The thermal radiation protection module is equipped with an AMO light source incident glass (2), which is used to transmit light sources; The thermal radiation protection module includes a thermal radiation protection plate (1); the thermal radiation protection plate (1) is installed on the outside of the AM0 light source incident glass (2) and can rotate horizontally 360 degrees to keep the test cavity warm, prevent the cavity temperature from dropping during the heating process, and prevent the temperature from rising due to blackbody radiation during the cooling process. The vacuum chamber module is used to house the vacuum adsorption platform module; the vacuum adsorption platform module provides a platform for the battery cell under test to be placed horizontally for electrical performance testing; The cooling circulating water module (5) controls the heating rate of the battery cells by controlling the circulating water flow rate; The cryogenic module (6) is used to cool the vacuum chamber (3); The high-temperature module (7) is used to heat the vacuum chamber (3); The vacuum adsorption platform module includes a vacuum adsorption platform (4); The vacuum adsorption platform (4) is equipped with a back electrode plate clamp (41), a four-probe test circuit (42), a light intensity calibration standard battery cell (43), a sample test platform (44), and a test clamp (47); the vacuum adsorption platform (4) is equipped with a temperature sensor (46) and a vacuum air extraction circuit (45). There are four back electrode plate clamps (41), which are located at the four corners of the vacuum adsorption platform (4) and are used to fix the back electrode plate that supports the battery cell. The four-probe test circuit (42) is used to transmit test data, including the electrode contact probes and leads of the cell under test; The light intensity calibration standard solar cell (43) is used to calibrate the standard light intensity. It is installed on one side of the vacuum adsorption platform (4) at the same height as the sample test platform (44). The sample testing platform (44) fixes the battery cell to be tested by vacuum adsorption to prevent displacement; The vacuum suction path (45) of the vacuum adsorption platform is connected to the vacuum mechanical pump (33) outside the test chamber through the vacuum airtight valve on the vacuum chamber module; the vacuum chamber module and the vacuum adsorption platform module share the vacuum mechanical pump (33) outside the test chamber. The test fixture (47) is used to fix the N end of the battery cell during testing.

2. The electrical performance testing chamber for a large temperature variation environment solar cell as described in claim 1, characterized in that, The vacuum chamber module includes a vacuum chamber (3), a vacuum chamber evacuation air path (31), a molecular pump (32), a mechanical pump (33), and a vacuum sensor (34); The vacuum sensor (34) and the vacuum chamber evacuation air path (31) are installed inside the vacuum chamber module; The vacuum mechanical pump (33) and molecular pump (32) are installed outside the vacuum chamber module; The vacuum chamber vacuum path (31) is connected to the vacuum mechanical pump (33) and molecular pump (32) through the vacuum airtight valve on the vacuum chamber module. By evacuating the vacuum chamber (3) and simultaneously cooling or heating the chamber, the simulation of a large temperature change space environment can be achieved.

3. The electrical performance testing chamber for a large temperature variation environment solar cell as described in claim 1, characterized in that, The back electrode plate clamp (41) is fixed by tightening and can be used for electrical performance testing of flexible coiled batteries or irregularly shaped batteries; the back electrode plate clamp (41) can be adjusted horizontally and vertically according to the shape of the back electrode plate.

4. The electrical performance testing chamber for a large temperature variation environment solar cell as described in claim 1, characterized in that, The spacing of the test fixture (47) can be adjusted according to the electrode specifications of different battery cells.

5. The electrical performance testing chamber for a large temperature variation environment solar cell as described in claim 1, characterized in that, The cooling circulating water module (5) is installed below the high temperature module (7) and is used to cool the sample testing platform (44).

6. The electrical performance testing chamber for a large temperature variation environment solar cell as described in claim 5, characterized in that, The cooling circulating water module (5) controls the heating rate of the battery cell by controlling the circulating water flow rate, and the heating rate is controlled at 0.1℃ / min to +10℃ / min.

7. The electrical performance testing chamber for a large temperature variation environment solar cell as described in claim 1, characterized in that, The cryogenic module (6) is used to cool the vacuum chamber (3) and includes a liquid helium gas compressor (61) and a liquid helium circulation gas path (62). The liquid helium circulation path (62) is installed inside the vacuum chamber (3) to enable the reusability of liquid helium gas; the liquid helium gas compressor (61) can achieve low temperatures of 5K, 15K or 55K.

8. The electrical performance testing chamber for a large temperature variation environment solar cell as described in claim 1, characterized in that, The high-temperature module (7) is used to heat the vacuum cavity (3) in a temperature range of 0℃ to +500℃.

9. The electrical performance testing chamber for a large temperature variation environment space solar cell as described in claim 1, characterized in that, The heat radiation protection plate (1) is a metal plate with black sides.

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