A method for monitoring the failure of a solar cell array for space use

Abstract

The application provides a space solar cell array fault monitoring method, comprising the following steps: preparing a solar cell array component, leading out wires from the positive and negative ends of the component, and placing the component in a simulated space environment test tank to apply a space high vacuum and thermal alternating environment; connecting the solar cell array component leading-out wires with a constant current source and a resistor in series outside the test tank to form a loop; connecting the voltage collection device with the resistor in parallel; connecting the voltage collection device with a computer, monitoring and recording the loop voltage value in a whole cycle; calculating and setting the current and voltage provided by the constant current source device according to the battery type, size of the space solar cell array component and the change characteristics under the space high-low temperature alternating environment; and positioning the circuit on-off and fault generation time of the space solar cell array according to the whole cycle voltage value.

Description

Technical Field

[0002] This invention belongs to the field of space solar cell array technology, and specifically relates to a fault monitoring method for space solar cell arrays. Background Technology

[0004] Solar arrays provide energy to satellites and are an important component of satellites. Therefore, the safe and trouble-free operation of solar arrays in the space environment is crucial, which places high demands on satellite solar arrays with high reliability and long lifespan.

[0005] Currently, ground-based monitoring of satellite solar array faults primarily relies on environmental testing. This involves conducting simulated space environment tests on the ground, inspecting the solar array's appearance, flatness, and electrical performance before and after the tests. However, with the increasing demand for satellite solar array development, this method of checking before and after tests is not only time-consuming and labor-intensive, but manual inspection also carries the risk of uncertainty due to personnel changes. Furthermore, this method can only detect defects in the solar array statically under normal temperature and pressure conditions; it cannot quantitatively pinpoint the time and conditions of the fault throughout the entire lifecycle, nor can it quantitatively determine whether the fault is an open circuit, shading, or current decay. Currently, prototype products can be tested by heating the solar array with specific lamp arrays in a thermal vacuum test and collecting current data in real time to check circuit continuity. However, this method has extremely high requirements for hardware such as lamp arrays, thermal vacuum chambers, power control, and data acquisition devices, and is only applicable to prototype products. If a product malfunctions, it involves multiple processes such as transportation and rework, which will seriously affect the development schedule. Therefore, current methods for monitoring solar cell array faults are no longer suitable for the rapidly developing field of satellite solar cell array manufacturing. Summary of the Invention

[0007] This invention provides a method for monitoring faults in space-based solar arrays to solve the problems of the inability to easily, quickly, and in real-time monitor and record faults of solar arrays throughout their entire lifecycle in the aforementioned ground-based environmental tests.

[0008] According to the present invention, a method for monitoring faults in a space-based solar array is provided, the method for monitoring faults throughout the entire lifecycle of the solar array includes:

[0009] Prepare a space solar cell array module, and lead wires from the positive and negative ends of the module. Place the module in a test tank that simulates the space environment and apply a high vacuum and thermal alternation environment.

[0010] Outside the test tank, lead wires from the solar cell array components are connected in series with a constant current source and a resistor to form a circuit;

[0011] Connect the voltage acquisition device in parallel with a resistor;

[0012] Connect the voltage acquisition device to the computer to monitor and record the circuit voltage value throughout the entire cycle;

[0013] Based on the cell type, size, and variation characteristics of the space solar cell array components under alternating high and low temperatures in space, calculate the current and voltage that the constant current source device should provide.

[0014] Based on the full-cycle voltage values, determine the circuit continuity and fault occurrence time of the satellite's solar cell array.

[0015] In one embodiment of the present invention, the current value to be provided by the constant current source device is calculated as follows:

[0016] J 设置 =J m S

[0017] Among them, J 设置 The current value that should be set for the constant current source device, J m Let S be the area of ​​a single cell in the solar cell module, where S represents the optimal operating current density. If all cells in a string of solar cells are of the same size, the constant current source current parameters can be calculated using the formula described above. If the cells in a string of solar cells are of different sizes, to prevent the module from burning out due to overcurrent, the constant current source current parameters should be calculated based on the area of ​​the smallest solar cell.

[0018] In one embodiment of the present invention, the voltage value to be provided by the constant current source device is calculated as follows:

[0019] V 设置 =V OC N+R 电阻 J 设置 +α (T0-T L )N

[0020] Among them, V 设置 The voltage that should be set for the constant current source device, V OC J is the open-circuit voltage of the cells in the solar cell module, N is the total number of cells in each string of solar cells, and J is the open-circuit voltage of the cells in the solar cell module. 设置 The current value that should be set for the constant current source device, R 电阻 V represents the resistance of the series resistor in the circuit. Because in the simulated space environment, alternating high and low temperatures cause significant temperature differences in the environment, and V... OC The data was obtained under room temperature (T0) conditions. As the temperature decreases, the open-circuit voltage increases slightly according to the temperature coefficient α. Therefore, under low-temperature conditions (T... LWhen the open-circuit voltage increases to a certain extent, the open-circuit voltage under low-temperature conditions must be considered when calculating the voltage value to be provided by the constant current source device. The accurate open-circuit voltage must be calculated according to the temperature coefficient. Otherwise, the set voltage value may be inaccurate, preventing the module from conducting, or even causing irreversible damage to the cells due to excessive voltage setting, leading to performance degradation.

[0021] In one embodiment of the present invention, the device for simulating a space environment refers to a high-low temperature test chamber that can provide a high-low temperature cyclic environment, wherein the low temperature range of the test chamber is -200℃ to -30℃, preferably -180℃ to -80℃. The high temperature range of the test chamber is +50℃ to +300℃, preferably +80℃ to +140℃.

[0022] In one embodiment of the present invention, the aforementioned lead wires from the positive and negative ends of the module refer to the process of leading the wires from the device simulating the space environment to the outside of the tank after the connecting pieces of the positive and negative ends of the solar cell array module are resistance welded to the wires. Specifically:

[0023] (1) According to the series and parallel connection relationship of the manufactured solar cell array components, mark the positive and negative terminals of each string of cells respectively;

[0024] (2) Take one end of a wire and solder it to one end of the battery string; take another wire and solder it to the other end of the battery string. Continue in this manner to solder the remaining battery strings to the wires. The welding method for the wires to the positive and negative ends of the battery string is resistance welding, with a welding current of 20~200A and a welding pressure of 0.2~20N.

[0025] (3) Lead all the welded wires out of the tank through a device that simulates the space environment.

[0026] In one embodiment of the present invention, the space solar cell array component refers to a III-V compound semiconductor solar cell component; the wire refers to a space-level wire.

[0027] In one embodiment of the present invention, the constant current source includes a device that can provide constant current and voltage, preferably a constant current source. The resistance value of the resistor can be different as needed, preferably 1 ohm.

[0028] In one embodiment of the present invention, the loop connection step includes:

[0029] First, the solar cell array components are placed in a simulated space environment device, and the lead wires are led out of the device through the tank wall.

[0030] Outside the container, connect the wire at the P end of the solar cell array to one end of a resistor, connect the other end of the resistor to the positive end of a constant current source, and connect the negative end of the constant current source to the N end wire of the solar cell array.

[0031] In one embodiment of the present invention, the voltage acquisition device includes a voltage data acquisition card or a data acquisition unit.

[0032] In one embodiment of the present invention, the voltage acquisition device and the resistor are connected in parallel as follows:

[0033] The positive terminal of each channel on the data acquisition card is connected to the positive terminal of the constant current source;

[0034] The negative terminal of the data acquisition card channel is connected to the P terminal of the solar cell array component.

[0035] In one embodiment of the present invention, connecting the voltage acquisition device to the computer refers to connecting the data cable of the voltage acquisition card to the computer host to complete the software reception of the acquired data. The full-cycle monitoring and recording of the loop voltage value includes the following steps:

[0036] (1) After the circuit is connected, start the working condition of the simulated space environment, and at the same time turn on all instruments in the circuit and input all setting parameters as required;

[0037] (2) Open the computer software. The voltage values ​​of the resistor collected by the acquisition card throughout the test cycle will be recorded in the software in chronological order.

[0038] (3) Based on the resistance value in the circuit, the current value flowing through the circuit is obtained through data processing, which is the current value flowing through the solar cell circuit;

[0039] (4) By comparing the current value set by the constant current source with the current value collected by the acquisition card, the functional characteristics of the solar cell array can be determined, and the time of the fault and the number of cell strings can be quickly located after a fault occurs.

[0040] In one embodiment of the present invention, the type of the battery includes a single-junction gallium arsenide solar cell and a multi-junction gallium arsenide solar cell. The dimensions include 20×40mm, 30×40mm, 40×60mm, 40×80mm, 10×10mm, 5×5mm, and 4×4mm.

[0041] In one embodiment of the present invention, the method for switching the positioning satellite solar array circuit on and off is as follows: by judging the voltage data, if the voltage data is zero, the circuit is off; if the voltage data is not zero, the circuit is on. The specific criteria for judging the voltage data are:

[0042] (1) First, the current J in the circuit needs to be calculated based on the collected voltage value and the resistance value of the series resistor in the circuit.采集 ;

[0043] (2) If J 采集 =J 设置 If J is connected, the circuit is open and the solar cell circuit is normal; if J is connected, the circuit is open. 采集 =J 设置 Meanwhile, V 设置 Change to V 设置 =R 电阻 J 设置 If so, the possible fault in the solar cell circuit is a short circuit;

[0044] (3) If J 采集 If the value is 0, then the circuit is open.

[0045] In one embodiment of the present invention, the faults include open circuits and short circuits in the solar cell array components.

[0046] The beneficial effects of this invention are that it enables real-time monitoring of faults in space-use solar arrays under simulated space environment conditions on the ground, and collects and records test data values ​​throughout the entire lifecycle. By processing the data, it achieves full-cycle monitoring of the solar array, allowing for the pinpointing of the time of solar array fault occurrence. This method is simple in principle, has low hardware requirements, is flexible in operation, applicable to different environmental test sites, exhibits good consistency in test results, has small test errors, and the test results do not change due to movement of the test site or solar array components. It can monitor the current on / off status of the solar array in real time, saving time and costs, exposing problems before the delivery or launch of satellite solar array products, improving the reliability of solar array products, and increasing the efficiency of research and development and production. Attached Figure Description

[0048] Figure 1 Flowchart of a full-cycle monitoring method for faults in space-based solar cell arrays during the invention process;

[0049] Figure 2 This is a schematic diagram of the loop connection in the invention;

[0050] Figure 3 A graph showing the circuit voltage values ​​tested during the invention;

[0051] Figure 4 This is a fault curve graph detected during the invention. Detailed Implementation

[0053] The specific embodiments of the present invention will be further described in detail below with reference to the accompanying drawings. It should be noted that the drawings are all in a very simplified form and use non-precise ratios, and are only used to facilitate and clarify the explanation of the embodiments of the present invention.

[0054] This invention provides a simple and quick way to supply power to solar cell arrays by establishing a series circuit between the solar cell array components, a constant current source, and a resistor. This reduces the constraints imposed by hardware conditions such as lamp arrays, hot vacuum tanks, and factory sites on the testing method. The current and voltage calculation method for the constant current source device proposed in this application can accurately obtain the required current and voltage values ​​based on different cell types, sizes, and series connection methods. By recording the voltage values ​​in the circuit throughout the entire cycle, the current value of the cell string can be calculated, and monitoring values ​​can be recorded in real time. When a problem occurs, the exact moment of the problem can be accurately and quantitatively located. The full-cycle monitoring method for space-use solar cell array faults according to this invention will now be described in detail.

[0055] See Figure 1 The full-cycle monitoring method for solar array faults includes the following steps:

[0056] 1. Prepare a space solar cell array module and lead wires from the positive and negative ends of the module. Place the module in a test tank that simulates the space environment and apply a high vacuum and thermal alternation environment.

[0057] 2. Connect the space solar cell array components in series with a constant current source and a resistor to form a circuit;

[0058] 3. Connect the voltage acquisition device in parallel with the resistor;

[0059] 4. Connect the voltage acquisition device to the computer to monitor and record the circuit voltage value throughout the entire cycle;

[0060] 5. Based on the cell type, size, and variation characteristics of the space solar cell array components under alternating high and low temperatures in space, calculate and set the current and voltage to be provided by the constant current source device;

[0061] 6. Based on the full-cycle voltage values, determine the circuit continuity and fault occurrence time of the satellite solar array.

[0062] The present invention calculates the required current and voltage values ​​for the constant current source device based on the specific type, efficiency characteristics, and size of the battery. The main purpose is to avoid damage to the solar cell due to excessive current setting or insufficient voltage setting that prevents the solar cell's PN junction from opening, thus leaving the circuit in an open-circuit state and affecting subsequent data interpretation. The current value to be provided by the constant current source device in this invention is calculated as follows:

[0063] J 设置 =J m S

[0064] Among them, J 设置 To calculate the required current for the constant current source device, J mLet S be the area of ​​a single cell in the solar cell module, where S represents the optimal operating current density. If all cells in a string of solar cells are of the same size, the constant current source current parameters can be calculated using the formula described above. If the cells in a string of solar cells are of different sizes, to prevent the module from burning out due to overcurrent, the constant current source current parameters should be calculated based on the area of ​​the smallest solar cell.

[0065] The voltage value provided by the constant current source device in this invention shall be calculated as follows:

[0066] V 设置 =V OC N+R 电阻 J 设置 +α (T0-T L )N

[0067] The voltage provided by the constant current source device should consider three parts: first, the voltage of the battery module itself; second, the voltage drop across the series resistor in the test circuit; and third, the voltage fluctuation of the space solar cell caused by temperature changes in the high and low temperature cycling device. 设置 The accuracy of the numerical value is crucial; if V 设置 If the value is too small to be sufficient to activate the space solar cell, the cell will be unable to conduct current due to the low voltage. This will prevent the acquisition system from collecting current and voltage data, interfering with the test results of the full-cycle monitoring of solar cell array faults. In the formula, V 设置 The voltage that should be set for the constant current source device, V OC J is the open-circuit voltage of the cells in the space solar cell module, N is the total number of cells in each string of solar cells, and J is the open-circuit voltage of the cells in the space solar cell module. 设置 To calculate the required current for the constant current source device, R 电阻 Let α be the resistance value of the series resistor in the circuit, and α be the temperature coefficient.

[0068] During the monitoring of faults in space satellite solar cell arrays, due to the high vacuum and alternating temperature environment of space, the open-circuit voltage of the space solar cells changes with temperature variations. This change in open-circuit voltage is reflected by the temperature coefficient α. Since the temperature coefficient α is closely related to the epitaxial structure of the gallium arsenide solar cell, gallium arsenide solar cells with different epitaxial structures exhibit varying temperature coefficients α and V. OC They are all different; for a specific gallium arsenide solar cell epitaxial structure, it has specific α and V values. OC Numerical value. In high and low temperature cycling environments, significant temperature differences can occur in the ambient environment, while V... OCThe data was obtained under room temperature (T0) conditions. As the temperature decreases, the open-circuit voltage of the space solar cell will change accordingly according to the temperature coefficient α. For space-use III-V compound semiconductor solar cells, the temperature coefficient α is the data obtained by comprehensive analysis of its compound structure and the measured values ​​of mass-produced products. Therefore, when monitoring satellite solar cell arrays with different structures on the ground, the influence of the change in the temperature coefficient on the open-circuit voltage setting should be considered. Otherwise, the set value may be deviated, making it impossible for the module to conduct, or even causing irreversible damage to the cell due to excessive voltage setting, resulting in performance degradation.

[0069] In step 1 of this invention, the wires leading from the positive and negative terminals of the component are mainly led out from inside the test tank to outside the tank. To ensure reliable wire welding and the wires' ability to withstand the harsh environment of the simulated space, space-grade wires are selected, and resistance welding is used. The specific steps are as follows:

[0070] (1) According to the series and parallel connection relationship of the solar cell array components, mark the positive and negative terminals of each cell string respectively;

[0071] (2) Take one end of a wire and solder it to one end of the battery string; take another wire and solder it to the other end of the battery string. Continue in this manner until the remaining battery strings are soldered to the wires. The welding method for the wires to the positive and negative ends of the battery string is resistance welding, with a welding current of 20~200A, preferably 110~130A. The welding pressure is 0.2~20N, preferably 8~12N.

[0072] (3) Lead all the welded wires out of the tank through a device that simulates the space environment.

[0073] The loop connection in this invention is mainly for providing current and voltage to the solar cell array using a constant current source. This utilizes the characteristic that the solar cell itself is also a diode. By providing current to the loop, the current flowing through the solar cell array components can be monitored. The loop connection steps in this invention are as follows:

[0074] (1) Lead wires of the solar cell array components are led out of the tank through the tank wall of the simulated space environment device;

[0075] (2) Outside the container, connect the wire at the P end of the solar cell array to one end of the resistor, connect the other end of the resistor to the positive end of the constant current source, and connect the negative end of the constant current source to the N end wire of the solar cell array.

[0076] In this invention, a constant current source refers to a device that can provide constant current and voltage, such as a constant current source or a solar cell array simulator. A constant current source is preferred.

[0077] The space solar cell array assembly in this invention refers to a III-V compound semiconductor solar cell assembly. III-V compound semiconductor solar cells include assemblies composed of one or more of single-junction gallium arsenide solar cells, multi-junction gallium arsenide solar cells, and flexible thin-film gallium arsenide solar cells. Multi-junction gallium arsenide solar cell assemblies are preferred. More preferably, triple-junction gallium arsenide solar cell assemblies with a photoelectric conversion efficiency of 30% are preferred.

[0078] In this invention, the resistor refers to resistors of different resistance values. Preferably, it is 1 ohm. The purpose of connecting the resistor in this invention is primarily to collect the voltage value in the circuit and calculate the current value flowing through the circuit based on the voltage value of the resistor. By comparing the real-time collected current value with the current value set by the constant current source, abnormal values ​​in the collected current can be detected, and the moment of battery failure can be located.

[0079] The voltage acquisition device in this invention refers to a voltage data acquisition card or acquisition unit capable of acquiring voltage. The voltage acquisition device in this invention is connected in parallel with a resistor as follows:

[0080] (1) Connect the positive terminal of each channel on the acquisition card to the positive terminal of the constant current source;

[0081] (2) The negative terminal of the acquisition card channel is connected to the P terminal of the solar cell array resistor.

[0082] The full-cycle monitoring and recording of loop voltage values ​​in this invention refers to recording the voltage value across the series resistor in the loop. Based on the resistance value, the current flowing through the loop can be calculated. The full-cycle monitoring and recording of loop voltage values ​​includes the following steps:

[0083] (1) After the circuit is connected, turn on the operating condition of the high and low temperature test tank that simulates the space environment, set the parameters such as high temperature, low temperature and heat preservation time of the test tank, and turn on all instruments in the circuit and input all the setting parameters as required;

[0084] (2) Open the computer software. The voltage values ​​of the resistor collected by the acquisition card throughout the test cycle will be recorded in the software in chronological order.

[0085] (3) Based on the resistance value in the circuit, the current value flowing through the circuit can be obtained through data processing, which is the current value flowing through the solar cell circuit.

[0086] (4) By comparing the current value set by the constant current source with the current value collected by the acquisition card, the functional characteristics of the solar cell array can be determined, and the time of the fault and the cell string can be quickly located after a fault occurs.

[0087] The types of batteries in this invention include single-junction gallium arsenide solar cells and multi-junction gallium arsenide solar cells. Multi-junction gallium arsenide solar cells are preferred. Triple-junction gallium arsenide solar cells with a photoelectric conversion efficiency of 30% are more preferred. The dimensions include 20×40mm, 30×40mm, 40×60mm, 40×80mm, 10×10mm, 5×5mm, and 4×4mm. 40×60mm and 40×80mm are preferred.

[0088] The faults in this invention include open circuits and short circuits in the solar array components. The specific criteria for determining the continuity of the positioning satellite solar array circuit in this invention are as follows:

[0089] (1) First, the current J in the circuit needs to be calculated based on the collected voltage value and the resistance value of the series resistor in the circuit. 采集 ;

[0090] (2) If J 采集 =J 设置 If J is connected, the circuit is open and the solar cell circuit is normal; if J is connected, the circuit is open. 采集 =J 设置 Meanwhile, V 设置 Change to V 设置 =R 电阻 J 设置 If so, the possible fault in the solar cell circuit is a short circuit;

[0091] (3) If J 采集 If the value is 0, then the circuit is open.

[0092] Example 1

[0093] This embodiment provides a method for fault monitoring of a space-based solar cell array, specifically including the following steps:

[0094] (1) Prepare a 30% efficiency triple-junction gallium arsenide solar cell array module and lead wires from the positive and negative ends of the module. Specifically, the number of modules is 18 strings and 6 parallels, and the size of the triple-junction gallium arsenide solar cells is 40×60mm. According to the series and parallel connection relationship of the prepared solar cell array module, mark the positive and negative ends of each string of cells. Take one end of a wire and weld it to one end of the cell string; take another wire and weld it to the other end of the cell string. In this way, weld the remaining cell strings to the wires. The welding method of the wires to the positive and negative ends of the cell strings is resistance welding, the welding current value is 120A, and the welding pressure value is 10N. After the space-level wires are welded to the positive and negative ends of each cell string by resistance welding, the solar cell array module is placed in a simulated space environment device, and the space-level wires are led out of the simulated space environment device to the outside of the tank according to the sequence number of the solar cell strings.

[0095] (2) Connect the solar cell array components in series with the constant current source and resistor to form a circuit, see [reference]. Figure 2 Specifically, the lead wires of the solar cell array are led out through the tank wall of the simulated space environment device to the outside of the tank; outside the tank, the lead wire at the P end of each solar cell array is connected to one end of a resistor, wherein the resistance value is selected as 1 ohm, and the other end of the resistor is connected to the positive end of a constant current source, and the negative end of the constant current source is connected to the N end lead wire of the solar cell array.

[0096] (3) Connect the voltage acquisition device in parallel with the resistor. Specifically, select a voltage acquisition card with 40 channels and use a total of 6 channels. The positive terminal of each channel is connected to the positive terminal of the corresponding constant current source, and the negative terminal of each channel on the voltage acquisition card is connected to the P terminal of the corresponding solar cell array component.

[0097] (4) Connect the voltage acquisition device to the computer, monitor and record the loop voltage value throughout the entire cycle. Specifically: connect the data cable of the voltage acquisition card to the computer host. After the connection is completed, start the high and low temperature test chamber simulating the space environment, and set the parameters of the test chamber such as high temperature, low temperature and holding time. The temperature is set to -100℃~+135℃, and the holding time is 10min at the lowest and highest temperatures respectively, with a heating rate >10℃ / min. Turn on the constant current source, computer, voltage acquisition device and high and low temperature cycle device in the loop, and input all the setting parameters as required. Turn on the computer software. The voltage values ​​of the resistor acquired by the acquisition card throughout the entire test cycle will be recorded in the software in chronological order. See the loop voltage value curve for the test. Figure 3 Since the resistance in the circuit is 1 ohm, the voltage value collected is also the current value flowing through the solar cell circuit. By comparing the current value set by the constant current source with the current value collected by the acquisition card, the functional characteristics of the solar cell array can be determined, and the time of the fault and the number of cell strings can be quickly located after a fault occurs.

[0098] (5) Based on the cell type and size of the solar cell array, calculate the current and voltage to be provided by the constant current source device according to the calculation method formula. Specifically: the selected cell is a triple-junction gallium arsenide solar cell with a size of 40×60mm. According to the formula, the current provided by the constant current source device is calculated to be 405 mA. The voltage provided by the constant current source device is calculated to be 60 V.

[0099] (6) Based on the full-cycle voltage values, determine the circuit continuity and fault occurrence time of the satellite solar array. See [reference needed]. Figure 4Specifically, computer software is used to collect voltage-time data throughout the entire test cycle. Since the selected resistor has a resistance of 1 ohm, the voltage-time data is equivalent to the current-time data. The continuity of the solar cell circuit is determined based on the data curve. By interpreting the voltage data, if the voltage data is zero, the circuit is open; if the voltage data is not zero, the circuit is continuous. If the circuit is determined to be open, the solar cell array may have malfunctioned, including open circuit or cell rupture.

[0100] In summary, the method provided by this invention can effectively monitor and record the entire lifecycle of solar cell array faults in space satellites. By establishing a series circuit between the solar cell array components, a constant current source, and a resistor, the power supply to the solar cell array can be provided quickly and easily, reducing the constraints of hardware conditions such as lamp arrays, hot vacuum tanks, and factory sites on the testing method. The proposed current and voltage calculation method for the constant current source device can accurately obtain the required current and voltage values ​​based on different cell types, sizes, and series connection methods. By recording the voltage values ​​in the circuit throughout the entire lifecycle, the current value of the cell string can be calculated, and monitoring values ​​can be recorded in real time, allowing for quantitative location of the problem when it occurs. This method is simple in principle, has low hardware requirements, is flexible in operation, and is applicable to different environmental test sites. The test results have good consistency, small test errors, and do not change due to changes in the test site or solar cell array components. Real-time monitoring of the current flow of the solar cell array saves time and costs, allowing for early detection of problems before the delivery or launch of the satellite solar cell array product, improving the reliability of the solar cell array product and increasing the efficiency of research and development.

[0101] The contents not described in detail in this specification are prior art known to those skilled in the art. It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within the present invention.

Claims

1. A method for fault monitoring of a space-based solar cell array, characterized in that, Includes the following steps: Step 1: Prepare a space solar cell array component and lead wires from the positive and negative ends of the component. Place the component in a test tank that simulates the space environment and apply a high vacuum and thermal-low temperature alternating environment in the test tank. Step 2: Outside the test tank, connect the lead wires from the solar cell array assembly in series with a constant current source and a resistor to form a test circuit; Step 3: Connect the voltage acquisition device in parallel with the resistor; Step 4: Connect the voltage acquisition device to the computer to monitor and record the voltage value of the test circuit throughout the entire cycle. Step 5: Calculate and set the current and voltage values ​​that the constant current source should provide based on the cell type, size, and variation characteristics of the space solar cell array component under alternating high and low temperatures in space. Step 6: Based on the voltage values ​​recorded during the entire monitoring cycle, determine the circuit on / off status and fault occurrence time of the space solar cell array.

2. The method for fault monitoring of a space-based solar cell array as described in claim 1, characterized in that, The constant current source should provide the current value J. 设置 Calculate using the following formula: J 设置 =J m S in which J 设置 J is the current value that the constant current source should be set to. m S represents the optimal operating current density of the solar cell module, and S represents the area of ​​a single cell in the solar cell module. If the dimensions of the solar cells in a solar cell array are not consistent, the constant current source current parameters are calculated based on the area of ​​the solar cell with the smallest area.

3. The method for fault monitoring of a space-based solar cell array as described in claim 2, characterized in that, The constant current source should provide a voltage value V. 设置 Calculate using the following formula: V 设置 =V OC N+R 电阻 J 设置 +α (T0-T L )N Among them, V 设置 The voltage that the constant current source should be set to, V OC R is the open-circuit voltage of the cells in the space solar cell module, N is the total number of cells in each string of solar cells, and R is the open-circuit voltage of the cells in the space solar cell module. 电阻 Let α be the resistance value of the series resistor in the circuit, α be the temperature coefficient of the solar cell, T0 be the room temperature, and T be the temperature coefficient of the solar cell. L To simulate the low-temperature operating conditions in the space environment.

4. The method for fault monitoring of a space-based solar cell array as described in claim 1, characterized in that, The test chamber simulating the space environment is a high and low temperature test chamber, with a low temperature range of -200°C to -30°C and a high temperature range of +50°C to +300°C.

5. The method for fault monitoring of a space-based solar cell array as described in claim 1, characterized in that, Step 1, specifically the step of drawing wires from the positive and negative terminals of the component, includes the following steps: Step 11: According to the series and parallel connection relationship of the solar cell array components, mark the positive and negative terminals of each cell string respectively. Step 12: Take a wire, weld one end of the wire to one end of the battery string using resistance welding, and weld one end of the other wire to the other end of the battery string using resistance welding. Step 13: Lead all the welded wires out of the test tank in the simulated space environment.

6. The method for fault monitoring of a space-based solar cell array as described in claim 1, characterized in that, Step 2, which involves connecting the lead wires from the solar cell array assembly in series with a constant current source and a resistor to form a test circuit, specifically includes the following steps: Step 21: Connect the lead wire at the P end of the solar cell array component to one end of the resistor; Step 22: Connect the other end of the resistor to the positive terminal of the constant current source; Step 23: Connect the negative terminal of the constant current source to the N terminal lead wire of the solar cell module.

7. The method for fault monitoring of a space-based solar cell array as described in claim 1, characterized in that, The voltage acquisition device is a voltage data acquisition card. The step of connecting the voltage acquisition device in parallel with the resistor is as follows: connect the positive terminal of each acquisition channel on the acquisition card to the positive terminal of the constant current source, and connect the negative terminal of each acquisition channel to the P terminal of the solar cell array component.

8. The method for fault monitoring of a space-based solar cell array as described in claim 1, characterized in that, Step 4, specifically the step of monitoring and recording the circuit voltage value throughout the entire cycle, includes: Step 41: Activate the operating conditions of the simulated space environment and start all instruments in the test loop; Step 42: Using the software on the computer, record the voltage values ​​of the resistor collected by the voltage acquisition device throughout the entire test cycle in chronological order. Step 43: Calculate the current flowing through the solar cell module based on the recorded voltage value, according to the resistance value of the resistor.

9. The method for fault monitoring of a space-based solar cell array as described in claim 1, characterized in that, The method for determining the on / off state of the circuit of the positioning space solar cell array is as follows: by reading the voltage value, if the voltage value is zero, the circuit is determined to be in an off state; if the voltage value is not zero, the circuit is determined to be in a conducting state. The faults include open circuits and short circuits in the solar cell array components.

10. A method for monitoring faults in a space-based solar array as described in claim 9, characterized in that, The method for locating the time of fault occurrence is as follows: by interpreting voltage-time data, the moment when the voltage data anomaly first occurred is found, so as to locate the time of fault occurrence.

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