Electric performance test cavity for solar cell in large temperature change environment space

Abstract

The invention discloses an electrical performance test cavity for a solar cell in a large temperature change environment space. The electrical performance test cavity comprises an AM0 light source incidence module, a thermal radiation protection module, a vacuum cavity module, a vacuum adsorption platform module, a cooling circulating water module, a low-temperature module and a high-temperature module, the thermal radiation protection module is provided with AM0 light source incidence glass used for allowing a light source to penetrate through. The thermal radiation protection module comprises a thermal radiation protection plate; the thermal radiation protection plate is mounted on the outer side of the AM0 light source incidence glass; the vacuum cavity module is used for placing the vacuum adsorption platform module; the cooling circulating water module is used for controlling the heating rate of the battery piece; the low-temperature module is used for cooling the vacuum cavity; and the high-temperature module is used for heating the vacuum cavity. According to the invention, deep space extremely-low and extremely-high temperature environments can be simulated, and the test requirements of electrical performance data of the space solar cell at a specific temperature or vacuum continuous temperature change are met; the battery piece is prevented from shifting through vacuum adsorption, and the stability of electrical performance test data can be improved.

Description

Technical Field

[0001] The invention belongs to the technical field of space solar cell testing, and in particular relates to a space solar cell electrical performance testing chamber in a large temperature change environment. Background Art

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

[0003] Currently, ground-based electrical performance testing of solar arrays for conventional Earth-orbiting satellites primarily uses AM0 solar simulators at room temperature. However, compared to Earth orbit, deep space environments have extreme temperatures and extremely low light intensities. Under these extreme temperatures and low light levels, the electrical performance of solar cells differs significantly from that in conventional Earth orbit. Therefore, conventional Earth-orbiting satellite electrical performance testing methods cannot meet the increasingly urgent demand for testing solar cells for deep space exploration satellites. Currently, there are no dedicated test chambers or equipment specifically designed for deep space exploration solar cells, making it impossible to perform electrical performance testing of these cells in a simulated space environment. Design calculations for solar cell circuits for deep space exploration satellites rely solely on electrical performance test data from conventional Earth-orbiting satellites. This not only leads to inaccurate power design data for deep space exploration satellites, but also creates a high risk of overestimating the power generation performance of space solar cells, potentially leading to mission failure. This significantly limits China's development in the field of deep space exploration satellites.

[0004] Therefore, it is urgently necessary to develop a space solar cell electrical performance test cavity equipment suitable for deep space exploration in a large temperature change environment. It can simulate the deep space environment on the ground and realize the electrical performance test of solar cells under extreme temperature or different lighting environments on the ground, laying a technical foundation for the engineering implementation of the Jupiter system and planetary crossing mission. Summary of the Invention

[0005] In order to solve the above problems, the present invention provides a space solar cell electrical performance test chamber with a large temperature change environment. The chamber can provide extremely low and extremely high vacuum temperatures. The space solar cell is placed in the test chamber, and the electrical performance test of the cell can be achieved under any vacuum temperature condition in the temperature range of -260℃ to +500℃, which can meet the requirements of electrical performance data of space solar cells under specific temperatures or continuous vacuum temperature changes.

[0006] The specific technical scheme of the present application is as follows:

[0007] A large temperature change environment space solar cell piece electric performance test cavity, the test cavity contains AM0 light source incidence module, heat radiation protection module, vacuum cavity module, vacuum adsorption platform module, cooling circulating water module, low temperature module 6, high temperature module 7;

[0008] The heat radiation protection module is installed with AM0 light source incidence glass 2, and the AM0 light source incidence glass 2 is used for transmitting light source;

[0009] The heat radiation protection module contains a heat radiation protection plate 1; the heat radiation protection plate 1 is installed on the outside of the AM0 light source incidence glass 2, can rotate horizontally in 360-degree direction, is used for heat preservation of the test cavity, prevents the cavity temperature from reducing during the heating process, and simultaneously prevents the cavity temperature from rising due to direct irradiation of the AM0 light source during the cooling process. Only when the electric performance of the battery is tested, the heat radiation protection plate is horizontally turned open, and after the test is completed, the heat radiation protection plate is restored to the original position, that is, covers the vacuum cavity, so that the performance degradation of the battery caused by long-time direct irradiation of the AM0 light source can be avoided.

[0010] The vacuum cavity module is used for placing the vacuum adsorption platform module; the vacuum adsorption platform module provides a horizontal platform for the battery piece to be tested to perform electric performance test;

[0011] The cooling circulating water module 5 controls the heating rate of the battery piece during heating by controlling the circulating water flow rate;

[0012] The low temperature module 6 is used for cooling the vacuum cavity 3;

[0013] The high temperature module 7 is used for heating the vacuum cavity 3.

[0014] The vacuum cavity module contains a vacuum cavity 3, a vacuum cavity evacuation air path 31, a molecular pump 32, a mechanical pump 33 and a vacuum degree sensor 34;

[0015] The vacuum degree sensor 34 and the vacuum cavity evacuation air path 31 are installed in the vacuum cavity module;

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

[0017] The vacuum cavity evacuation air path 31 is connected with the evacuation mechanical pump 33 and the molecular pump 32 through the vacuum air-tight valve on the vacuum cavity module, and the cavity cooling or heating is performed by evacuating the vacuum cavity 3, so that the simulation of the vacuum large temperature change space environment is realized.

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

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

[0020] There are four back electrode plate fixtures 41, which are respectively located at the four corners of the vacuum adsorption platform 4 and are used to fix the back electrode plate holding the battery cell;

[0021] The four-probe test circuit 42 is used to transmit test data, and includes contact probes and leads for the electrodes of the cell to be tested.

[0022] The light intensity calibration standard cell 43 is used to calibrate the standard light intensity and is installed on one side of the vacuum adsorption platform 4 at the same height as the sample test platform 44 ; the light intensity calibration standard cell 43 includes one standard cell.

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

[0024] The vacuum adsorption platform vacuum air path 45 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;

[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 battery cells of different specifications; further 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 fixture 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 fixture 41 can be adjusted horizontally and vertically according to the shape of the back electrode plate; the back electrode plate fixture 41 can test battery cells with a short side length in the range of 1 to 200 mm, a long side length in the range of 1 to 200 mm, and a vertical thickness in the range of 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 cell by controlling the circulating water flow rate. The heating rate is controlled within a range of 0.1°C / min to +10°C / minn, and more preferably 2°C / min.

[0029] The low temperature module 6 is used to cool the vacuum chamber 3 and includes a gas compressor 61 and a liquid helium circulation gas circuit 62;

[0030] The liquid helium circulation gas circuit 62 is installed inside the vacuum chamber 3 to achieve 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 increase the temperature of the vacuum chamber 3 , and the temperature range is 0° C. to +500° C., preferably 40° C. to 200° C.

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

[0033] Furthermore, the cell to be tested is a gallium arsenide solar cell.

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

[0035] Compared with the prior art, the present invention has the following beneficial effects:

[0036] (1) The present invention can simulate the extremely low and high temperature environments in deep space on the ground. The solar cells to be tested are placed in the test chamber, and the electrical performance of the solar cells can be tested under any temperature condition in the temperature range of -260°C to +500°C. This can meet the demand for electrical performance data of space solar cells under specific temperature or vacuum continuous temperature change, and avoid excessive data deviation caused by theoretical derivation.

[0037] (2) Vacuum adsorption can be used to test the electrical performance of flexible batteries, and the calibration module can be used to test the electrical performance of cells under different light intensities. The fused quartz glass AM0 light source incident module can minimize the loss of incident light, making the test data more accurate.

[0038] (3) Fixing the battery cells through vacuum adsorption can prevent the battery cells from shifting during testing, which can cause inaccurate test data. This can improve the consistency, stability and repeatability of electrical performance test data, and further improve the accuracy of test data. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0040] Figure 1 This is a schematic diagram of the structure of the solar cell electrical performance test chamber in a large temperature change environment space of the present invention.

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

[0042] The following describes the embodiments of the present invention through specific examples. Those skilled in the art will readily understand the other advantages and benefits of the present invention from the disclosure herein. The present invention may also be implemented or applied through various other specific embodiments, and the details in this specification may be modified or altered 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 merely schematic illustrations of the basic concept of the present invention. Therefore, the illustrations only show components related to the present invention and are not drawn according to the number, shape, and size of components in actual implementation. In actual implementation, the type, quantity, and proportion of each component may be changed arbitrarily, and the component layout may also be more complex.

[0044] The following is combined with Figure 1 The present invention is described in further detail.

[0045] A solar cell electrical performance test chamber with a large temperature change 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, and the AM0 light source incident glass 2 is used to transmit the light source;

[0047] The thermal radiation protection module includes a thermal radiation shield 1, which is mounted outside the AM0 light source incident glass 2 and can be rotated 360 degrees horizontally. This shield is used to maintain the temperature of the test cavity, preventing the vacuum cavity module from cooling during heating and preventing temperature increases caused by direct exposure to the AM0 light source during cooling. The shield is only rotated horizontally to test battery performance. After the test is complete, the shield is returned to its original position, covering the vacuum cavity module, to prevent battery performance degradation caused by prolonged exposure to the AM0 light source.

[0048] The vacuum chamber module is used to place a vacuum adsorption platform module; the vacuum adsorption platform module provides a horizontal platform for the battery cell to be tested to perform electrical performance testing;

[0049] The cooling circulating water passage 5 controls the temperature rise rate of the battery cell to be tested by controlling the flow rate of the circulating water;

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

[0051] The high temperature module 7 is used to increase the temperature of the vacuum chamber module.

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

[0053] The vacuum degree sensor 34 and the vacuum chamber vacuum air circuit 31 are installed in 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 air path 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 cooling or heating the chamber at the same time, the simulation of the vacuum space environment with large temperature changes is achieved.

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

[0057] The vacuum adsorption platform 4 is integrated with a back electrode plate fixture 41, a four-probe test probe 42, a light intensity calibration standard cell 43, a sample test platform 44 and a test fixture 47; the vacuum adsorption platform 4 is provided with a temperature sensor 46 and a vacuum adsorption platform vacuum air circuit 45;

[0058] There are four back electrode plate fixtures 41, which are respectively located at the four corners of the vacuum adsorption platform 4 and are used to fix the back electrode plate holding the battery cell to be tested;

[0059] The four-probe test probe 42 is used to transmit test data, and includes contact probes and leads for the electrodes of the cell to be tested.

[0060] The light intensity calibration standard cell 43 is used to calibrate the standard light intensity and is installed on one side of the vacuum adsorption platform 4 at the same height as the sample test platform 44 ; the light intensity calibration standard cell 43 includes one standard cell.

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

[0062] The vacuum adsorption platform vacuum pumping air circuit 45 is connected to the 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 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 battery cells of different specifications; further 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 fixture 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 fixture 41 can be adjusted horizontally and vertically according to the shape of the back electrode plate; the back electrode plate fixture 41 can test battery cells with a short side length in the range of 1 to 200 mm, a long side length in the range of 1 to 200 mm, and a vertical thickness in the range of 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 cell by controlling the circulating water flow rate. The heating rate is controlled within a range of 0.1°C / min to +10°C / minn, and more preferably 2°C / min.

[0067] The low temperature module 6 is used to cool the vacuum chamber 3 and includes a gas compressor 61 and a liquid helium circulation gas circuit 62;

[0068] The liquid helium circulation gas circuit 62 is installed inside the vacuum chamber 3 to achieve 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 increase the temperature of the vacuum chamber 3 , and the temperature range is 0° C. to +500° C., preferably 40° C. to 200° C.

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

[0071] Furthermore, the cell to be tested is a gallium arsenide solar cell.

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

[0073] use Figure 1 The following is a test chamber for the electrical performance of solar cells in a large temperature-variable environment.

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

[0075] S2. Contact the P-terminal of the 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 four-probe test probe 42 with the N-terminal electrode of the solar cell. Check and confirm that the light intensity calibration standard 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 testing platform 44 through the vacuum adsorption platform vacuum air path 45, cover the AM0 light source incident glass 2 downward to close the vacuum chamber 3, and rotate the heat radiation protection plate 1 180 degrees horizontally to close the outer side of the AM0 light source incident glass 2.

[0077] S4. Open the cooling circulating water passage 5, use the circulating water to cool the sample test platform 44, monitor the temperature of the sample test platform 44 in real time through the temperature sensor 46, and evacuate the vacuum chamber 3 to a low vacuum environment of less than 5000Pa through the vacuum chamber air passage 31. Turn on the molecular pump 32, and monitor the vacuum degree of the vacuum chamber 3 in real time through 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°C / min, and when heated to 60°C, turn on the AM0 solar simulator, rotate the thermal radiation protection plate 1 180 degrees horizontally, start the test equipment to test the IV electrical performance characteristics of the sample to be tested at 60°C, rotate it back 180 degrees horizontally to close the thermal radiation protection plate 1 and cover the outside of the AM0 light source incident glass 2; continue heating to 80°C, 100°C, 120°C, 140°C, and 200°C, and repeat the operation method of this step to continue testing the IV electrical performance characteristics of the sample to be tested 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, maintain the continuous cooling function 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, and when the temperature reaches -60°C, turn on the AM0 solar simulator, rotate 180 degrees horizontally to open the thermal radiation protection plate 1, start the test equipment to test the IV electrical performance characteristics of the sample to be tested at -60°C, rotate back 180 degrees horizontally to close the thermal radiation protection plate 1 and cover the outside of the AM0 light source incident glass 2; continue to cool to -80°C, -100°C, -120°C, and -140°C, and repeat the operation method of this step to continue testing the IV electrical performance characteristics of the sample to be tested at different low temperatures.

[0080] The invention provides a space solar cell electrical performance test chamber with a large temperature variation environment, which can simulate the space environment with extremely low and extremely high vacuum temperatures. By placing the cell to be tested in the test chamber, the electrical performance test of the cell can be realized under any vacuum temperature condition within the temperature range of -260℃ to +500℃, which can meet the demand for electrical performance data of space solar cells under specific temperature or continuous vacuum temperature variation, and avoid the excessive data deviation caused by theoretical deduction. The invention develops a space solar cell electrical performance test chamber device with a large temperature variation environment suitable for deep space exploration. It not only solves the problem of the lack of electrical performance testing means for solar cells in the extreme temperature and extremely low light intensity environment of deep space, but also simulates the deep space environment through the test chamber. It can accurately measure the electrical performance of solar cell arrays in the space environment during deep space exploration missions, obtain accurate cell temperature and test loss factor, effectively improve the accuracy of power design data of deep space exploration satellites, and improve the ability of solar cells to withstand extreme temperature environments in space.

[0081] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements 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 solar cell electrical performance test chamber in a large temperature change environment, characterized in that: The test cavity comprises an AM0 light source incident module, a thermal radiation protection module, a vacuum cavity 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 AM0 light source incident glass (2), and the AM0 light source incident glass (2) is used to transmit the light source; 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), can be rotated 360 degrees horizontally, and is used to test the heat preservation of the cavity, prevent the cavity temperature from decreasing during the heating process, and prevent the temperature from increasing due to black body radiation during the cooling process; The vacuum chamber module is used to place a vacuum adsorption platform module; the vacuum adsorption platform module provides a horizontal platform for the battery cell to be tested to perform electrical performance testing; The cooling circulating water module (5) controls the heating rate of the battery cell by controlling the flow rate of the circulating water; The low-temperature module (6) is used to cool the vacuum chamber (3); The high-temperature module (7) is used to increase the temperature of the vacuum cavity (3).

2. A solar cell electrical performance test chamber in a large temperature change environment as claimed in claim 1, characterized in that: The vacuum cavity module comprises a vacuum cavity (3), a vacuum cavity evacuation air path (31), a molecular pump (32), a mechanical pump (33), and an airiness sensor (34); The air space sensor (34) and the vacuum chamber vacuum air path (31) are installed in the vacuum chamber module; The vacuum mechanical pump (33) and the molecular pump (32) are installed outside the vacuum chamber module; The vacuum cavity evacuation air path (31) is connected to a vacuum mechanical pump (33) and a molecular pump (32) via a vacuum airtight valve on the vacuum cavity module. By evacuating the vacuum cavity (3) and cooling or heating the cavity at the same time, a simulation of a space environment with large temperature changes is achieved.

3. A solar cell electrical performance test chamber in a large temperature change environment as claimed in claim 1, characterized in that: The vacuum adsorption platform module includes a vacuum adsorption platform (4); The vacuum adsorption platform (4) is integrated with a back electrode plate fixture (41), a four-probe test circuit (42), a light intensity calibration standard cell (43), a sample test platform (44) and a test fixture (47); a temperature sensor (46) and a vacuum air circuit (45) are provided in the vacuum adsorption platform (4); There are four back electrode plate clamps (41), which are respectively 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, and includes contact probes and leads for electrodes of the battery cell to be tested; The light intensity calibration standard cell (43) is used for calibrating the standard light intensity and is installed on one side of the vacuum adsorption platform (4) at a height consistent with that of 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 adsorption platform vacuum air path (45) is connected to the vacuum mechanical pump (33) outside the test cavity through a vacuum airtight valve on the vacuum cavity module; the vacuum cavity module and the vacuum adsorption platform module share the vacuum mechanical pump (33) outside the test cavity; The test fixture (47) is used to fix the N end of the battery cell during testing.

4. A solar cell electrical performance test chamber in a large temperature change environment as claimed in claim 3, characterized in that: The back electrode plate fixture (41) is fixed by tightening and can be used for electrical performance testing of flexible curled batteries or irregularly shaped batteries; the back electrode plate fixture (41) can be adjusted in the horizontal and vertical directions according to the outer shape of the back electrode plate.

5. A solar cell electrical performance test chamber in a large temperature change environment as claimed in claim 3, characterized in that: The spacing between the test fixtures (47) can be adjusted according to different specifications of battery cell electrodes.

6. A solar cell electrical performance test chamber in a large temperature change environment as claimed in claim 1, characterized in that: 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).

7. A solar cell electrical performance test chamber in a large temperature change environment as claimed in claim 6, characterized in that: The cooling circulating water module (5) controls the heating rate of the battery cell when heating up by controlling the circulating water flow rate, and the heating rate is controlled within a range of 0.1°C / min to +10°C / min.

8. A solar cell electrical performance test chamber in a large temperature change environment as claimed in claim 1, characterized in that: The low temperature module (6) is used to cool the vacuum chamber (3), and comprises a gas compressor (61) and a liquid helium circulation gas circuit (62); The liquid helium circulation gas circuit (62) is installed inside the vacuum chamber (3) to achieve the reusability of liquid helium gas; the liquid helium gas compressor (61) can achieve low temperatures of 5K, 15K, and 55K.

9. A solar cell electrical performance test chamber in a large temperature change environment as claimed in claim 1, characterized in that: The high-temperature module (7) is used to increase the temperature of the vacuum cavity (3), and the temperature range is 0°C to +500°C.

10. A solar cell electrical performance test chamber in a large temperature change environment space as claimed in claim 1, characterized in that: The heat radiation protection plate (1) is a metal plate with both sides being black.

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