Load test method and system for aviation power supply system

Abstract

The invention provides a load test method and system for an aviation power supply system. The load test method for the aviation power supply system comprises the following steps: testing a target aviation power supply system to be tested according to an initial load capacity, and obtaining a test data value of the target aviation power supply system; acquiring a gradient value of load increase according to a test data value corresponding to the initial load test of the target aviation power supply system; the load capacity is gradually increased according to the gradient numerical value of load increase, and a test data value of the target aviation power supply system corresponding to the load capacity increased each time is acquired; and judging whether the operation of the target aviation power supply system meets the load test performance requirement or not according to the test data value of the target aviation power supply system corresponding to the load capacity increased each time. The system comprises modules corresponding to the steps of the method.

Description

Technical Field

[0001] The invention provides a load testing method and system for an aviation power supply system, belonging to the technical field of load testing. Background Art

[0002] With the rapid development of aviation technology, the aviation power supply system is an important part of the aircraft, and its stability and reliability are directly related to flight safety and the success of mission execution. The aviation power supply system not only needs to meet the power demand of the aircraft under normal flight conditions, but also needs to have the ability to maintain the power supply of key equipment in emergency or abnormal situations. Therefore, comprehensive and rigorous testing of the aviation power supply system to ensure its stable operation under various load conditions is an indispensable part of the aviation industry. The traditional aviation power supply system test method mainly relies on static load testing, that is, under preset fixed load conditions, the system's operating parameters, such as voltage, current, frequency and power factor, are observed and recorded to evaluate the system's performance. However, this method often cannot fully reflect the various dynamic load changes that the system may encounter in actual flight, especially when the load suddenly increases or decreases, the system's responsiveness and stability are difficult to be fully verified. In addition, with the increase in the number of avionics equipment and the increase in power demand, the aviation power supply system faces a more complex load environment. The traditional static load test method can no longer meet the needs of modern aviation power supply system performance testing. There is an urgent need for a test method that can simulate the dynamic changes of loads in actual flight and accurately evaluate the performance of the system under various load conditions. Summary of the invention

[0003] The present invention provides a load testing method and system for an aviation power supply system. By gradually increasing the load, the dynamic changes of the load in actual flight are simulated, and the test data values ​​of the system are acquired and analyzed in real time, so as to comprehensively evaluate the operating performance and stability of the aviation power supply system under various load conditions. This method can not only improve the accuracy and comprehensiveness of the test, but also provide strong data support for the design and optimization of the aviation power supply system, and further improve the safety and reliability of the aircraft. The load testing method and system for an aviation power supply system provided by the present invention are used to solve the technical problems existing in the above-mentioned prior art, and the technical solutions adopted are as follows:

[0004] A load testing method for an aviation power supply system, the load testing method for an aviation power supply system comprising:

[0005] Testing the target aviation power supply system to be tested according to the initial load, and obtaining test data values ​​of the target aviation power supply system;

[0006] Obtaining a gradient value of load increase according to a test data value corresponding to an initial load test of the target aviation power supply system;

[0007] The load is gradually increased according to the gradient value of the load increase, and a test data value of the target aviation power supply system corresponding to each load increase is obtained;

[0008] Whether the operation of the target aviation power supply system meets the load test performance requirements is determined based on the test data value of the target aviation power supply system corresponding to each load increase.

[0009] Further, the target aviation power supply system to be tested is tested according to the initial load, and test data values ​​of the target aviation power supply system are obtained, including:

[0010] Retrieve the initial load from the database, where the unit is kw;

[0011] The target aviation power supply system to be tested is tested according to the initial load, and test data values ​​of the target aviation power supply system are obtained, wherein the test data values ​​include voltage, current, frequency and power factor.

[0012] Further, obtaining a gradient value of load increase according to a test data value corresponding to the initial load test of the target aviation power supply system includes:

[0013] Retrieve the test data value corresponding to the initial load test of the target aviation power supply system;

[0014] Retrieve the standard data value corresponding to the initial load test;

[0015] Obtaining a gradient adjustment coefficient using a difference between a test data value and a standard data value corresponding to an initial load test of the target aviation power supply system;

[0016] The gradient adjustment coefficient is obtained by the following formula:

[0017]

[0018] Where Q represents the gradient adjustment coefficient; n represents the number of types contained in the test data value, that is, n = 4; X i represents the value corresponding to the i-th test data value; X zi represents the standard data value corresponding to the i-th test data value; L0 represents the value of the initial load of the target aviation power supply system; L m Indicates the maximum value of the test load corresponding to the load test;

[0019] Retrieve the initial gradient from the database;

[0020] The gradient value of the load increase is obtained by using the gradient adjustment coefficient in combination with the initial gradient value;

[0021] The load increase gradient value is obtained by the following formula:

[0022]

[0023] Among them, L t Indicates the gradient value of load increase; L c represents the initial gradient; Q represents the gradient adjustment coefficient; L0 represents the value of the initial load of the target aviation power supply system.

[0024] Further, the load is gradually increased according to the gradient value of the load increase, and the test data value of the target aviation power supply system corresponding to each load increase is obtained, including:

[0025] After the initial load test is completed, the initial load is adjusted to the first load, the second load and the third load respectively; wherein the first load is L0+L t , the second load is L0+2.5L t , the third load is L0+5Lt; wherein L0 represents the initial load; L t Indicates the gradient value of the load increase;

[0026] The load of the target aviation power supply system is adjusted from the initial load to the first load, and the first load is maintained for 30 minutes to 40 minutes to obtain a first test data value; wherein the first test data value includes the test data fluctuation rate corresponding to the test data at the moment of load increase and the test data value after stabilization;

[0027] After the first test data value is recorded, the load of the target aviation power supply system is instantly adjusted to the initial load, and the instantaneous fluctuation data of the test data value is obtained and recorded as the first test data fluctuation rate value;

[0028] The load of the target aviation power supply system is adjusted from the initial load to the second load, and the second load is maintained for 20 minutes to 30 minutes to obtain a second test data value; wherein the second test data value includes the test data fluctuation rate corresponding to the test data at the moment of load increase and the test data value after stabilization;

[0029] After the second test data value is recorded, the load of the target aviation power supply system is instantly adjusted to the initial load, and the instantaneous fluctuation data of the test data value is obtained and recorded as the second test data fluctuation rate value;

[0030] The load of the target aviation power supply system is adjusted from the initial load to the third load, and the third load is maintained for 15 minutes to 25 minutes to obtain a third test data value; wherein the third test data value includes the test data fluctuation rate corresponding to the test data at the moment of load increase and the test data value after stabilization;

[0031] After the third test data value is recorded, the load of the target aviation power supply system is instantly adjusted to the initial load, and the instantaneous fluctuation data of the test data value is obtained and recorded as the third test data fluctuation rate value.

[0032] Further, judging whether the operation of the target aviation power supply system meets the load test performance requirements according to the test data value of the target aviation power supply system corresponding to each load increase includes:

[0033] Retrieving a first test data value, a second test data value, and a third test data value;

[0034] Obtaining a first load evaluation coefficient using the first test data value, the second test data value, and the third test data value;

[0035] The first load evaluation coefficient is obtained by the following formula:

[0036]

[0037] Among them, S 01 represents the first load evaluation coefficient; e represents the number of load tests, and e=3; L i represents the load corresponding to the i-th load test; L0 represents the value of the initial load of the target aviation power supply system; R b represents the standard deviation of the data coefficients corresponding to the three load tests; R i represents the data coefficient corresponding to the i-th test data value generated by the i-th load test, and the data coefficient corresponding to the i-th test data value is obtained by the following formula:

[0038]

[0039] Among them, R represents the data coefficient corresponding to the test data value generated by each load test; n represents the number of types contained in the test data value; X fi represents the data volatility corresponding to the i-th test data value; T fi represents the fluctuation duration corresponding to the fluctuation period of the i-th test data value; X zi represents the standard data value corresponding to the i-th test data value; X bi represents the standard deviation of the data value of the i-th test data value during the load test process; X wirepresents the final stable setting of the i-th test data value during the load test;

[0040] Retrieving the first test data volatility value, the second test data volatility value and the third test data volatility value;

[0041] Obtaining a second load evaluation coefficient using the first test data volatility value, the second test data volatility value, and the third test data volatility value;

[0042] The second load evaluation coefficient is obtained by the following formula:

[0043]

[0044] Among them, S 02 represents the second load evaluation coefficient; n represents the number of types contained in the test data value; X fji represents the data volatility corresponding to the i-th test data in the j-th instantaneous fluctuation data; X zji represents the standard data value corresponding to the i-th test data in the j-th instantaneous fluctuation data; T fji represents the fluctuation duration corresponding to the i-th test data in the j-th instantaneous fluctuation data; T ci represents the preset reference value of the fluctuation duration corresponding to the i-th test data; X maxji represents the peak value corresponding to the fluctuation process of the i-th test data in the j-th instantaneous fluctuation data; X minji Indicates the trough value corresponding to the fluctuation process of the i-th test data in the j-th instantaneous fluctuation data;

[0045] Obtaining a comprehensive load evaluation coefficient using the first load evaluation coefficient and the second load evaluation coefficient;

[0046] The comprehensive load evaluation coefficient is obtained by the following formula:

[0047]

[0048] Where S represents the comprehensive load evaluation coefficient; S 01 Represents the first load evaluation coefficient; S 02 represents the second load evaluation coefficient;

[0049] Comparing the comprehensive load evaluation coefficient with a preset load evaluation coefficient threshold;

[0050] When the comprehensive load evaluation coefficient is lower than a preset load evaluation coefficient threshold, it is determined that the load measurement performance requirement is not met.

[0051] A load testing system for an aviation power supply system, the load testing system for an aviation power supply system comprising:

[0052] A first test data value acquisition module is used to test the target aviation power supply system to be tested according to the initial load amount, and obtain the test data value of the target aviation power supply system;

[0053] A gradient value acquisition module, used to acquire a gradient value of load increase according to a test data value corresponding to an initial load quantity test of the target aviation power supply system;

[0054] A second test data value acquisition module is used to gradually increase the load according to the gradient value of the load increase, and obtain the test data value of the target aviation power supply system corresponding to each load increase;

[0055] The performance determination module is used to determine whether the operation of the target aviation power supply system meets the load test performance requirements according to the test data value of the target aviation power supply system corresponding to each load increase.

[0056] Furthermore, the first test data value acquisition module includes:

[0057] An initial load quantity retrieving module is used to retrieve the initial load quantity from a database, wherein the unit is kw;

[0058] The initial test module is used to test the target aviation power supply system to be tested according to the initial load, and obtain the test data values ​​of the target aviation power supply system, wherein the test data values ​​include voltage, current, frequency and power factor.

[0059] Furthermore, the gradient value acquisition module includes:

[0060] A test data value retrieving module, used to retrieve the test data value corresponding to the initial load capacity test of the target aviation power supply system;

[0061] A standard data value retrieving module is used to retrieve the standard data value corresponding to the initial load test;

[0062] A gradient adjustment coefficient acquisition module, used to obtain the gradient adjustment coefficient by using the difference between the test data value and the standard data value corresponding to the initial load test of the target aviation power supply system;

[0063] The gradient adjustment coefficient is obtained by the following formula:

[0064]

[0065] Where Q represents the gradient adjustment coefficient; n represents the number of types contained in the test data value, that is, n = 4; X i represents the value corresponding to the i-th test data value; X zirepresents the standard data value corresponding to the i-th test data value; L0 represents the value of the initial load of the target aviation power supply system; L m Indicates the maximum value of the test load corresponding to the load test;

[0066] An initial gradient amount retrieving module is used to retrieve the initial gradient amount from the database;

[0067] A gradient value calculation module, used to obtain a gradient value of a load increase by using the gradient adjustment coefficient in combination with an initial gradient value;

[0068] The load increase gradient value is obtained by the following formula:

[0069]

[0070] Among them, L t Indicates the gradient value of load increase; L c represents the initial gradient; Q represents the gradient adjustment coefficient; L0 represents the value of the initial load of the target aviation power supply system.

[0071] Furthermore, the second test data value acquisition module includes:

[0072] A load adjustment module, used for adjusting the initial load to a first load, a second load and a third load respectively after the initial load test is completed; wherein the first load is L0+Lt, the second load is L0+2.5Lt, and the third load is L0+5Lt; wherein L0 represents the initial load; and Lt represents the gradient value of the load increase;

[0073] A first test data value acquisition module is used to adjust the load of the target aviation power supply system from an initial load to a first load, and maintain the first load for 30 minutes to 40 minutes to obtain a first test data value; wherein the first test data value includes a test data fluctuation rate corresponding to the test data at the moment of load increase and a test data value after stabilization;

[0074] A first test data fluctuation rate value acquisition module is used to adjust the load of the target aviation power supply system to the initial load instantly after the first test data value is recorded, obtain instantaneous fluctuation data of the test data value, and record it as the first test data fluctuation rate value;

[0075] A second test data value acquisition module is used to adjust the load of the target aviation power supply system from the initial load to the second load, and maintain the second load for 20 minutes to 30 minutes to obtain a second test data value; wherein the second test data value includes the test data fluctuation rate corresponding to the test data at the moment of load increase and the test data value after stabilization;

[0076] A second test data fluctuation rate value acquisition module is used to adjust the load of the target aviation power supply system to the initial load instantly after the second test data value is recorded, obtain instantaneous fluctuation data of the test data value, and record it as the second test data fluctuation rate value;

[0077] A third test data value acquisition module is used to adjust the load of the target aviation power supply system from the initial load to the third load, and continue the third load for 15 minutes to 25 minutes to obtain a third test data value; wherein the third test data value includes the test data fluctuation rate corresponding to the test data at the moment of load increase and the test data value after stabilization;

[0078] The third test data fluctuation rate value acquisition module is used to instantly adjust the load of the target aviation power supply system to the initial load after the third test data value is recorded, obtain the instantaneous fluctuation data of the test data value, and record it as the third test data fluctuation rate value.

[0079] Furthermore, the performance determination module includes:

[0080] A test data value retrieving module, used to retrieve a first test data value, a second test data value and a third test data value;

[0081] A first load evaluation coefficient acquisition module, used to acquire a first load evaluation coefficient using the first test data value, the second test data value and the third test data value;

[0082] The first load evaluation coefficient is obtained by the following formula:

[0083]

[0084] Among them, S 01 represents the first load evaluation coefficient; e represents the number of load tests, and e=3; L i represents the load corresponding to the i-th load test; L0 represents the value of the initial load of the target aviation power supply system; R b represents the standard deviation of the data coefficients corresponding to the three load tests; R i represents the data coefficient corresponding to the i-th test data value generated by the i-th load test, and the data coefficient corresponding to the i-th test data value is obtained by the following formula:

[0085]

[0086] Among them, R represents the data coefficient corresponding to the test data value generated by each load test; n represents the number of types contained in the test data value; X fi represents the data volatility corresponding to the i-th test data value; Tfi represents the fluctuation duration corresponding to the fluctuation period of the i-th test data value; X zi represents the standard data value corresponding to the i-th test data value; X bi represents the standard deviation of the data value of the i-th test data value during the load test process; X wi represents the final stable setting of the i-th test data value during the load test;

[0087] A test data volatility value retrieving module, used to retrieve a first test data volatility value, a second test data volatility value and a third test data volatility value;

[0088] A second load evaluation coefficient acquisition module, used to acquire a second load evaluation coefficient by using the first test data volatility value, the second test data volatility value and the third test data volatility value;

[0089] The second load evaluation coefficient is obtained by the following formula:

[0090]

[0091] Among them, S 02 represents the second load evaluation coefficient; n represents the number of types contained in the test data value; X fji represents the data volatility corresponding to the i-th test data in the j-th instantaneous fluctuation data; X zji represents the standard data value corresponding to the i-th test data in the j-th instantaneous fluctuation data; T fji represents the fluctuation duration corresponding to the i-th test data in the j-th instantaneous fluctuation data; T ci represents the preset reference value of the fluctuation duration corresponding to the i-th test data; X maxji represents the peak value corresponding to the fluctuation process of the i-th test data in the j-th instantaneous fluctuation data; X minji Indicates the trough value corresponding to the fluctuation process of the i-th test data in the j-th instantaneous fluctuation data;

[0092] A comprehensive load evaluation coefficient acquisition module, used to obtain a comprehensive load evaluation coefficient using the first load evaluation coefficient and the second load evaluation coefficient;

[0093] The comprehensive load evaluation coefficient is obtained by the following formula:

[0094]

[0095] Where S represents the comprehensive load evaluation coefficient; S 01 Represents the first load evaluation coefficient; S 02 represents the second load evaluation coefficient;

[0096] An evaluation coefficient comparison module, used for comparing the comprehensive load evaluation coefficient with a preset load evaluation coefficient threshold;

[0097] The load performance determination module is used to determine that the load measurement performance requirement is not met when the comprehensive load evaluation coefficient is lower than a preset load evaluation coefficient threshold.

[0098] Beneficial effects of the present invention:

[0099] The present invention proposes a load testing method and system for an aviation power supply system. By adopting a strategy of gradually increasing the load, the method can simulate the dynamic changes of the load in actual flight, so as to more accurately evaluate the changing performance of the aviation power supply system under different load conditions and the system damage or data distortion caused by excessive stability. Compared with the traditional static load testing method, this method simulates the actual flight conditions by gradually increasing the load, thereby avoiding and reducing the testing cost. The detailed test data and analysis results provided by the method can provide strong data support for the design and optimization of the aviation power supply system. Designers can adjust the system parameters and structure according to the test results to improve the performance and stability of the system. By comprehensively evaluating the performance of the aviation power supply system under various load conditions, the method helps to ensure that the system can operate stably in actual flight, thereby reducing the risk of flight accidents caused by power failures. BRIEF DESCRIPTION OF THE DRAWINGS

[0100] Figure 1 is a flow chart of the method of the present invention;

[0101] Figure 2 The system block diagram of the system of the present invention. DETAILED DESCRIPTION

[0102] The preferred embodiments of the present invention are described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described herein are only used to illustrate and explain the present invention, and are not used to limit the present invention.

[0103] The embodiment of the present invention provides a load test method for an aviation power supply system. Figure 1 As shown, the load testing method of the aviation power supply system includes:

[0104] S1. Testing the target aviation power supply system to be tested according to the initial load, and obtaining the test data value of the target aviation power supply system;

[0105] S2. Obtaining a gradient value of load increase according to a test data value corresponding to an initial load test of the target aviation power supply system;

[0106] S3, gradually increasing the load according to the gradient value of the load increase, and obtaining the test data value of the target aviation power supply system corresponding to each load increase;

[0107] S4. Determine whether the operation of the target aviation power supply system meets the load test performance requirements based on the test data value of the target aviation power supply system corresponding to each load increase.

[0108] The working principle of the above technical solution is as follows: First, a reasonable initial load is selected, which should be able to represent the basic load demand of the aviation power supply system under normal flight conditions. Then, the target aviation power supply system is tested under this load condition, and the key test data values ​​of the system, such as voltage, current, frequency, power factor and temperature, are recorded and obtained. Based on the results of the initial load test, combined with the design specifications and performance requirements of the aviation power supply system, the gradient value of the load increase is calculated and determined. This gradient value represents the amount of each load increase, which is intended to ensure that the test process can fully cover possible load changes without causing system damage or data distortion due to excessive load changes. According to the determined load increase gradient, the load of the system is gradually increased. After each load increase, the target aviation power supply system needs to be retested and the corresponding test data values ​​are recorded. This process is intended to simulate the gradual change of load in actual flight to observe the response and performance of the system under different load conditions. According to the test data values ​​obtained after each load increase, combined with the performance requirements and standards of the aviation power supply system, the operating status of the system is judged. This includes evaluating the system's voltage stability, current output capability, frequency retention capability, and thermal management capability. If the system remains stable and meets the performance requirements under all test load conditions, the target aviation power supply system is considered to have passed the load test.

[0109] The effect of the above technical solution is: through the strategy of gradually increasing the load, this method can simulate the dynamic changes of the load in actual flight, so as to more accurately evaluate the changing performance and excessive stability of the aviation power supply system under different load conditions, thereby avoiding system damage or data distortion caused by excessive load. Compared with the traditional static load test method, this method simulates actual flight conditions by gradually increasing the load, thereby reducing the testing cost. The detailed test data and analysis results provided by this method can provide strong data support for the design and optimization of aviation power supply systems. Designers can adjust system parameters and structures based on the test results to improve the performance and stability of the system. By comprehensively evaluating the performance of the aviation power supply system under various load conditions, this method helps to ensure that the system can operate stably in actual flight, thereby reducing the risk of flight accidents caused by power failures.

[0110] In one embodiment of the present invention, a target aviation power supply system to be tested is tested according to an initial load, and a test data value of the target aviation power supply system is obtained, including:

[0111] S101, retrieve the initial load from the database, wherein the unit is kw;

[0112] S102: Testing the target aviation power supply system to be tested according to the initial load, and obtaining test data values ​​of the target aviation power supply system, wherein the test data values ​​include voltage, current, frequency and power factor.

[0113] The working principle of the above technical solution is as follows: This step first involves a pre-established database, which stores the initial load data under different test scenarios. These data are in kilowatts (kw) and are intended to simulate various load conditions that the aviation power supply system may encounter in actual flight. Before the test begins, the system will retrieve a suitable initial load from the database. The selection of this initial load is usually based on the design specifications, performance requirements and test purposes of the aviation power supply system. After obtaining the initial load, the system will apply this load to the target aviation power supply system to be tested. Subsequently, the system will begin to monitor and record the key test data values ​​of the target aviation power supply system under the initial load, including voltage, current, frequency and power factor. These parameters are important indicators for evaluating the performance and stability of the aviation power supply system.

[0114] The effect of the above technical solution is: by retrieving the initial load from the database, it can be ensured that the same load conditions are used for each test, thereby improving the accuracy and repeatability of the test. At the same time, the load data in the database can be updated and expanded as needed to adapt to different test scenarios and changes in the aviation power supply system. This technical solution can comprehensively evaluate the performance and stability of the system by monitoring and recording key test data values ​​such as voltage, current, frequency and power factor of the target aviation power supply system under the initial load. These data can provide strong data support for the design and optimization of the aviation power supply system, and help improve the overall performance and reliability of the system. Through automated testing and database calls, this technical solution can significantly reduce testing costs and time. Compared with traditional manual testing methods, this technical solution is more efficient and convenient, and can greatly improve testing efficiency. By comprehensively evaluating the performance of the aviation power supply system under various load conditions, this technical solution helps to ensure that the system can operate stably in actual flight. This is of great significance for improving flight safety and reducing the risk of flight accidents.

[0115] In summary, this technical solution achieves a comprehensive evaluation and optimization of the performance of the aviation power supply system through core links such as database call, load test and data collection. This can not only improve the accuracy and repeatability of the test, but also reduce the test cost and time, while improving flight safety.

[0116] In one embodiment of the present invention, obtaining a gradient value of load increase according to a test data value corresponding to an initial load test of the target aviation power supply system includes:

[0117] S201, retrieve the test data value corresponding to the initial load test of the target aviation power supply system;

[0118] S202, retrieving the standard data value corresponding to the initial load test;

[0119] S203, obtaining a gradient adjustment coefficient by using the difference between the test data value and the standard data value corresponding to the initial load test of the target aviation power supply system;

[0120] The gradient adjustment coefficient is obtained by the following formula:

[0121]

[0122] Where Q represents the gradient adjustment coefficient; n represents the number of types contained in the test data value, that is, n = 4; X i represents the value corresponding to the i-th test data value; X zi represents the standard data value corresponding to the i-th test data value; L0 represents the value of the initial load of the target aviation power supply system; L m Indicates the maximum value of the test load corresponding to the load test;

[0123] S204, retrieving the initial gradient value from the database;

[0124] S205, using the gradient adjustment coefficient in combination with the initial gradient value to obtain a gradient value of load increase;

[0125] The load increase gradient value is obtained by the following formula:

[0126]

[0127] Among them, L t Indicates the gradient value of load increase; L c represents the initial gradient; Q represents the gradient adjustment coefficient; L0 represents the value of the initial load of the target aviation power supply system.

[0128] The working principle of the above technical solution is: retrieve the test data values ​​of the target aviation power supply system under the initial load from the test record, and these data values ​​include key parameters such as voltage, current, frequency and power factor. At the same time, retrieve the standard data values ​​corresponding to the initial load test, which are determined based on the design specifications, performance requirements and past test experience of the aviation power supply system. The gradient adjustment coefficient Q is calculated using the difference between the test data value and the standard data value. This coefficient reflects the degree of deviation between the performance of the target aviation power supply system under the initial load and the standard performance. The n in the calculation formula represents the number of types of test data values ​​(i.e., the four parameters of voltage, current, frequency and power factor), and Xi and Xzi represent the i-th test data value and its corresponding standard data value respectively. L0 and Lm represent the initial load value of the target aviation power supply system and the maximum test load value corresponding to the load test respectively. This formula comprehensively considers the deviation between the test data value and the standard data value and the proportional relationship between the initial load and the maximum test load, thereby deriving a gradient adjustment coefficient that can reflect the degree of deviation of system performance. The initial gradient Lc is retrieved from a pre-established database. This initial gradient is determined based on system performance requirements, test objectives, and past test experience, and is used to guide the gradual increase in load. The gradient value Lt of the load increase is calculated using the gradient adjustment coefficient Q and the initial gradient value Lc, combined with the initial load value L0. This value determines the specific amount of load increase each time in subsequent load tests. The calculation formula combines the gradient adjustment coefficient Q, the initial gradient value Lc, and the initial load value L0, and derives the gradient value Lt of the load increase through a certain mathematical relationship to ensure that the load test can gradually and reasonably increase the load, thereby comprehensively evaluating the performance of the target aviation power supply system.

[0129] The effect of the above technical solution is: by introducing the gradient adjustment coefficient Q, the deviation between the test data value and the standard data value and the proportional relationship between the initial load and the maximum test load are comprehensively considered, so that the gradient value of the load increase is more consistent with the actual change of the system performance. This method can more accurately reflect the performance of the target aviation power supply system under different load conditions and improve the accuracy and scientificity of the test. By pre-establishing a database and retrieving the initial gradient value Lc, the cumbersome process of re-determining the gradient value before each test is avoided. The calculation process of the gradient adjustment coefficient Q and the gradient value Lt of the load increase can be automated, thereby improving the efficiency and automation of the test process. By gradually increasing the load and monitoring the changes in system performance, potential performance problems can be discovered and solved in a timely manner. This method helps to optimize the design parameters and structural layout of the aviation power supply system, thereby improving the overall performance and reliability of the system. Compared with the traditional load testing method, the technical solution can more quickly determine the gradient value of the load increase and carry out testing. This helps to reduce the cost and time investment of testing and improve the economy and efficiency of testing work.

[0130] On the other hand, by calculating the gradient adjustment coefficient Q, the deviations of various test data values ​​(voltage, current, frequency, power factor) from the standard data values, as well as the proportional relationship between the initial load and the maximum test load, are comprehensively considered, so that the gradient value of the load increase can be determined more accurately. This helps to improve the accuracy and reliability of the test. The method adopts the method of gradually increasing the load, which can more carefully observe and analyze the performance changes of the target aviation power supply system under different load conditions, so as to more accurately evaluate its performance and reliability. By gradually increasing the load and monitoring the changes in system performance, potential performance problems such as voltage instability, excessive current, frequency fluctuation, etc. can be discovered and solved in time. This helps to optimize the design parameters and structural layout of the aviation power supply system and improve the overall performance of the system. The method can simulate the dynamic changes of the load in actual flight, so as to evaluate the stability and reliability of the target aviation power supply system under different load conditions. By optimizing the design and adjusting the parameters, the reliability of the system can be further improved to ensure its stable operation in various complex environments. The calculation process of the gradient adjustment coefficient Q and the gradient value Lt of the load increase can be realized automatically, which reduces the time and error of manual calculation and improves the test efficiency. By pre-establishing a database and retrieving the initial gradient value Lc, the cumbersome process of redetermining the gradient value before each test is avoided, reducing the number and time of repeated tests. This method can determine the gradient value of the load increase more quickly and carry out testing work, which helps to reduce the cost and time investment of testing and improve the economy and efficiency of testing work. During the test process, the data values ​​of each test can be recorded and data analysis can be performed. This helps to trace and verify the test results later to ensure the accuracy and reliability of the test results. Since this method uses standardized test procedures and data processing methods, the test results have good repeatability. This helps to repeat the test at different times and locations to verify the stability and consistency of system performance.

[0131] In summary, the technical effects of the above technical solutions in terms of performance indicators are mainly reflected in improving the accuracy and reliability of the test, optimizing the system design and performance, reducing the test cost and time, and improving the traceability and repeatability of the test. These technical effects help to improve the overall performance and reliability of the aviation power supply system and provide a strong guarantee for flight safety. At the same time, the technical solution realizes the reasonable determination of the gradient value of the load increase and the test process of gradually increasing the load by comprehensively considering the deviation between the test data value and the standard data value, the proportional relationship between the initial load and the maximum test load, and the pre-established database information. This method can more accurately evaluate the performance of the target aviation power supply system and optimize the system design parameters and structural layout.

[0132] In one embodiment of the present invention, the load is gradually increased according to the gradient value of the load increase, and the test data value of the target aviation power supply system corresponding to each load increase is obtained, including:

[0133] S301, after the initial load test is completed, the initial load is adjusted to the first load, the second load and the third load respectively; wherein the first load is L0+L t , the second load is L0+2.5L t , the third load is L0+5Lt; wherein L0 represents the initial load; L t Indicates the gradient value of the load increase;

[0134] S302, adjusting the load of the target aviation power supply system from the initial load to the first load, and maintaining the first load for 30 minutes to 40 minutes, and obtaining a first test data value; wherein the first test data value includes the test data fluctuation rate corresponding to the test data at the moment of load increase and the test data value after stabilization;

[0135] S303: After the first test data value is recorded, the load of the target aviation power supply system is instantly adjusted to the initial load, and instantaneous fluctuation data of the test data value is obtained and recorded as the first test data fluctuation rate value;

[0136] S304, adjusting the load of the target aviation power supply system from the initial load to the second load, and maintaining the second load for 20 minutes to 30 minutes, and obtaining a second test data value; wherein the second test data value includes the test data fluctuation rate corresponding to the test data at the moment of load increase and the test data value after stabilization;

[0137] S305. After the second test data value is recorded, the load of the target aviation power supply system is instantly adjusted to the initial load, and instantaneous fluctuation data of the test data value is obtained and recorded as the second test data fluctuation rate value;

[0138] S306, adjusting the load of the target aviation power supply system from the initial load to a third load, and maintaining the third load for 15 minutes to 25 minutes, and obtaining a third test data value; wherein the third test data value includes a test data fluctuation rate corresponding to the test data at the moment of load increase and a test data value after stabilization;

[0139] S307. After the third test data value is recorded, the load of the target aviation power supply system is instantly adjusted to the initial load, and the instantaneous fluctuation data of the test data value is obtained and recorded as the third test data fluctuation rate value.

[0140] The working principle of the above technical solution is: after the initial load test is completed, the first load (L0+Lt), the second load (L0+2.5Lt) and the third load (L0+5Lt) are set according to the load increase gradient value Lt. These load settings are intended to simulate different load conditions that the aviation power supply system may encounter in actual flight, so as to comprehensively evaluate its performance.

[0141] For each set load (first, second, and third load), adjust the load of the target aviation power supply system from the initial load to the load and keep it for a period of time (30min-40min, 20min-30min, and 15min-25min, respectively). At the moment of load increase, record the volatility of the test data to evaluate the system's ability to respond to load changes. After the load stabilizes, record the test data value to evaluate the system's performance under the load. After the test is completed, instantly adjust the load back to the initial load, and record the instantaneous fluctuation data of the test data value, that is, the test data volatility value, to evaluate the system's load recovery capability.

[0142] The effect of the above technical solution is: by gradually increasing the load and testing at each load for a period of time, the performance of the target aviation power supply system under different load conditions can be comprehensively evaluated. This helps to discover potential problems of the system under different loads, such as voltage instability, excessive current, frequency fluctuations, etc., so as to optimize and improve them in time. By recording the test data at the moment of load increase and after the load is stable, the system's responsiveness to load changes and performance stability can be more accurately evaluated. At the same time, by recording the test data volatility value, the system load recovery capability can be further evaluated to improve the accuracy and reliability of the test. According to the test results, the design of the target aviation power supply system can be optimized, such as adjusting the circuit structure, improving the heat dissipation method, etc., to improve the system performance and reliability. This helps to reduce the failure rate of the system in actual flight and improve flight safety. By gradually increasing the load for testing, the risk of damage to the system due to excessive load applied at one time can be avoided, thereby reducing the test cost. At the same time, since the test process is carried out in stages, the test plan can be adjusted in time according to the test results to reduce unnecessary test time and waste of resources.

[0143] On the other hand, by gradually increasing the load and recording the test data fluctuation rate at the moment of load increase, the response speed and stability of the target aviation power supply system to load changes can be accurately evaluated. This helps to understand whether the system can quickly adjust and maintain stable output when facing a sudden increase in load. By testing for a period of time at each set load and recording the test data value after stabilization, the stability and reliability of the target aviation power supply system under different load conditions can be verified. This helps to ensure that the system can continuously and stably supply power in actual flight to meet flight requirements. By recording the instantaneous fluctuation data of the test data value (i.e., the test data fluctuation rate value), the recovery ability of the target aviation power supply system after load changes can be quantitatively evaluated. This helps to understand whether the system can quickly return to a stable state after a sudden decrease in load, thereby ensuring flight safety. Based on the above test results, the design of the target aviation power supply system can be optimized, such as adjusting the circuit structure, improving the heat dissipation method, optimizing the control strategy, etc., to improve system performance and reliability. This helps to reduce the failure rate of the system in actual flight and improve flight safety and economy. By gradually increasing the load for testing, the risk of damage to the system caused by applying too large a load at one time can be avoided, thereby reducing the test cost. At the same time, since the test process is carried out in stages, the test plan can be adjusted in time according to the test results, reducing unnecessary test time and resource waste. This technical solution can more accurately evaluate the performance of the target aviation power supply system by testing in stages and recording detailed data. At the same time, since the test process has clear steps and indicators, it can improve test efficiency and ensure the accuracy and reliability of test results.

[0144] In summary, the technical effects of the above-mentioned technical solutions in terms of performance indicators are mainly reflected in accurately evaluating load response capabilities, verifying system stability and reliability, quantitatively evaluating load recovery capabilities, optimizing system design and performance improvement, reducing test costs and time, and improving test efficiency and accuracy. These technical effects help to comprehensively evaluate the performance of the target aviation power supply system and provide strong protection for flight safety. At the same time, the technical solution comprehensively evaluates the performance of the target aviation power supply system under different load conditions by gradually increasing the load and recording test data. This helps to improve the accuracy and reliability of the test, optimize the system design, and reduce test costs and time.

[0145] In one embodiment of the present invention, determining whether the operation of the target aviation power supply system meets the load test performance requirements according to the test data value of the target aviation power supply system corresponding to each load increase includes:

[0146] S401, retrieve a first test data value, a second test data value, and a third test data value;

[0147] S402, obtaining a first load evaluation coefficient using the first test data value, the second test data value and the third test data value;

[0148] The first load evaluation coefficient is obtained by the following formula:

[0149]

[0150] Among them, S 01 represents the first load evaluation coefficient; e represents the number of load tests, and e=3; L i represents the load corresponding to the i-th load test; L0 represents the value of the initial load of the target aviation power supply system; R b represents the standard deviation of the data coefficients corresponding to the three load tests; R i represents the data coefficient corresponding to the i-th test data value generated by the i-th load test, and the data coefficient corresponding to the i-th test data value is obtained by the following formula:

[0151]

[0152] Among them, R represents the data coefficient corresponding to the test data value generated by each load test; n represents the number of types contained in the test data value; X fi represents the data volatility corresponding to the i-th test data value; T fi represents the fluctuation duration corresponding to the fluctuation period of the i-th test data value; X zi represents the standard data value corresponding to the i-th test data value; X bi represents the standard deviation of the data value of the i-th test data value during the load test process; X wi represents the final stable setting of the i-th test data value during the load test;

[0153] S403, retrieve the first test data volatility value, the second test data volatility value and the third test data volatility value;

[0154] Obtaining a second load evaluation coefficient using the first test data volatility value, the second test data volatility value, and the third test data volatility value;

[0155] The second load evaluation coefficient is obtained by the following formula:

[0156]

[0157] Among them, S 02 represents the second load evaluation coefficient; n represents the number of types contained in the test data value; X fji represents the data volatility corresponding to the i-th test data in the j-th instantaneous fluctuation data; Xzji represents the standard data value corresponding to the i-th test data in the j-th instantaneous fluctuation data; T fji represents the fluctuation duration corresponding to the i-th test data in the j-th instantaneous fluctuation data; T ci represents the preset reference value of the fluctuation duration corresponding to the i-th test data; X maxji represents the peak value corresponding to the fluctuation process of the i-th test data in the j-th instantaneous fluctuation data; X minji Indicates the trough value corresponding to the fluctuation process of the i-th test data in the j-th instantaneous fluctuation data;

[0158] S404, obtaining a comprehensive load evaluation coefficient using the first load evaluation coefficient and the second load evaluation coefficient;

[0159] The comprehensive load evaluation coefficient is obtained by the following formula:

[0160]

[0161] Where S represents the comprehensive load evaluation coefficient; S 01 Represents the first load evaluation coefficient; S 02 represents the second load evaluation coefficient;

[0162] S405, comparing the comprehensive load evaluation coefficient with a preset load evaluation coefficient threshold;

[0163] S406: When the comprehensive load evaluation coefficient is lower than a preset load evaluation coefficient threshold, it is determined that the load measurement performance requirement is not met.

[0164] The working principle of the above technical solution is: retrieve the first test data value, the second test data value and the third test data value, which are obtained when testing the target aviation power supply system under different loads. At the same time, retrieve the test data volatility value corresponding to each test to evaluate the system's response speed and stability to load changes. Calculate the first load evaluation coefficient using the test data value (including data volatility, fluctuation duration, standard data value, data value standard deviation and final stable setting, etc.). This coefficient comprehensively considers factors such as the number of load tests, load, data coefficient standard deviation, etc., to evaluate the overall performance of the system during load changes. Calculate the second load evaluation coefficient using the test data volatility value (including data volatility, standard data value, fluctuation duration, peak value and trough value in instantaneous fluctuation data, etc.). This coefficient mainly evaluates the response speed and stability of the system at the moment of load change, as well as the characteristics of the fluctuation process. Combine the first load evaluation coefficient and the second load evaluation coefficient to calculate the comprehensive load evaluation coefficient. This coefficient is a comprehensive evaluation of the system load performance, taking into account the overall performance and instantaneous response capability during load changes. Compare the comprehensive load evaluation coefficient with the preset load evaluation coefficient threshold. If the comprehensive load evaluation coefficient is lower than the threshold, it is determined that the target aviation power supply system does not meet the load measurement performance requirements.

[0165] The effect of the above technical solution is: this technical solution can comprehensively evaluate the performance of the target aviation power supply system during load changes by comprehensively considering various data indicators (such as data volatility, fluctuation duration, standard data value, etc.) during the load test process. By introducing the first load evaluation coefficient and the second load evaluation coefficient, and combining the comprehensive load evaluation coefficient for judgment, the accuracy of the evaluation of the system load performance is improved. Based on the evaluation results, the design of the target aviation power supply system can be optimized to improve its load performance and stability. This technical solution avoids unnecessary repeated testing and reduces testing costs by testing in stages and recording detailed data. The test process has clear steps and indicators, which can quickly complete the test and obtain evaluation results, thereby improving test efficiency. By accurately evaluating the load performance of the target aviation power supply system, potential problems can be discovered and optimized in a timely manner to ensure flight safety.

[0166] On the other hand, by introducing the first load evaluation coefficient and the second load evaluation coefficient, the technical solution can accurately quantify the performance of the target aviation power supply system during load changes. These two coefficients comprehensively consider a variety of test data values, such as data volatility, fluctuation duration, standard data value, etc., so as to more accurately reflect the load performance of the system. The technical solution not only considers the overall performance during the load test (through the first load evaluation coefficient), but also considers the transient response capability (through the second load evaluation coefficient). This comprehensive evaluation method improves the comprehensiveness and accuracy of the system load performance and helps to discover potential performance bottlenecks or problems. By testing in stages and recording detailed data, the technical solution optimizes the load testing process. The test process has clear steps and indicators, and can quickly complete the test and obtain the evaluation results, thereby improving the test efficiency. Since the test process is carried out in stages and analyzed based on detailed test data, unnecessary repeated tests can be avoided. This helps to reduce the test cost while ensuring the accuracy and reliability of the test results. Based on the evaluation results, the design of the target aviation power supply system can be optimized. For example, according to the load performance evaluation results, the circuit structure can be adjusted, the heat dissipation method can be improved, or the control strategy can be optimized to improve the load performance and stability of the system. By accurately evaluating the load performance of the target aviation power supply system, potential problems can be discovered and optimized in a timely manner. This helps ensure that the system can continuously and stably supply power during flight, thereby improving flight safety. This technical solution helps to discover unstable factors in the system during load changes by comprehensively evaluating the system's load performance. By optimizing the design and improving measures, the reliability of the system can be enhanced and the failure rate can be reduced.

[0167] In summary, the technical effects of the above technical solutions in terms of performance indicators are mainly reflected in accurately quantifying load performance, improving the comprehensiveness and accuracy of evaluation, optimizing load test processes, reducing test costs, guiding system design and optimization, improving flight safety, and enhancing system reliability. These technical effects help to comprehensively evaluate the performance of the target aviation power supply system and provide strong support for system optimization and improvement. At the same time, the technical solution determines whether the system meets the load test performance requirements by comprehensively analyzing the test data values ​​in terms of working principle. In terms of technical effects, it improves the accuracy of evaluation, optimizes system design, reduces test costs, improves test efficiency, and ensures flight safety.

[0168] The embodiment of the present invention provides a load test system for an aviation power supply system, such as Figure 2 As shown, the load test system of the aviation power supply system includes:

[0169] A first test data value acquisition module is used to test the target aviation power supply system to be tested according to the initial load amount, and obtain the test data value of the target aviation power supply system;

[0170] A gradient value acquisition module, used to acquire a gradient value of load increase according to a test data value corresponding to an initial load quantity test of the target aviation power supply system;

[0171] A second test data value acquisition module is used to gradually increase the load according to the gradient value of the load increase, and obtain the test data value of the target aviation power supply system corresponding to each load increase;

[0172] The performance determination module is used to determine whether the operation of the target aviation power supply system meets the load test performance requirements according to the test data value of the target aviation power supply system corresponding to each load increase.

[0173] The working principle of the above technical solution is as follows: First, a reasonable initial load is selected, which should be able to represent the basic load demand of the aviation power supply system under normal flight conditions. Then, the target aviation power supply system is tested under this load condition, and the key test data values ​​of the system, such as voltage, current, frequency, power factor and temperature, are recorded and obtained. Based on the results of the initial load test, combined with the design specifications and performance requirements of the aviation power supply system, the gradient value of the load increase is calculated and determined. This gradient value represents the amount of each load increase, which is intended to ensure that the test process can fully cover possible load changes without causing system damage or data distortion due to excessive load changes. According to the determined load increase gradient, the load of the system is gradually increased. After each load increase, the target aviation power supply system needs to be retested and the corresponding test data values ​​are recorded. This process is intended to simulate the gradual change of load in actual flight to observe the response and performance of the system under different load conditions. According to the test data values ​​obtained after each load increase, combined with the performance requirements and standards of the aviation power supply system, the operating status of the system is judged. This includes evaluating the system's voltage stability, current output capability, frequency retention capability, and thermal management capability. If the system remains stable and meets the performance requirements under all test load conditions, the target aviation power supply system is considered to have passed the load test.

[0174] The effect of the above technical solution is: through the strategy of gradually increasing the load, this method can simulate the dynamic changes of the load in actual flight, so as to more accurately evaluate the changing performance and excessive stability of the aviation power supply system under different load conditions, thereby avoiding system damage or data distortion caused by excessive load. Compared with the traditional static load test method, this method simulates actual flight conditions by gradually increasing the load, thereby reducing the testing cost. The detailed test data and analysis results provided by this method can provide strong data support for the design and optimization of aviation power supply systems. Designers can adjust system parameters and structures based on the test results to improve the performance and stability of the system. By comprehensively evaluating the performance of the aviation power supply system under various load conditions, this method helps to ensure that the system can operate stably in actual flight, thereby reducing the risk of flight accidents caused by power failures.

[0175] In one embodiment of the present invention, the first test data value acquisition module includes:

[0176] An initial load quantity retrieving module is used to retrieve the initial load quantity from a database, wherein the unit is kw;

[0177] The initial test module is used to test the target aviation power supply system to be tested according to the initial load, and obtain the test data values ​​of the target aviation power supply system, wherein the test data values ​​include voltage, current, frequency and power factor.

[0178] The working principle of the above technical solution is as follows: This step first involves a pre-established database, which stores the initial load data under different test scenarios. These data are in kilowatts (kw) and are intended to simulate various load conditions that the aviation power supply system may encounter in actual flight. Before the test begins, the system will retrieve a suitable initial load from the database. The selection of this initial load is usually based on the design specifications, performance requirements and test purposes of the aviation power supply system. After obtaining the initial load, the system will apply this load to the target aviation power supply system to be tested. Subsequently, the system will begin to monitor and record the key test data values ​​of the target aviation power supply system under the initial load, including voltage, current, frequency and power factor. These parameters are important indicators for evaluating the performance and stability of the aviation power supply system.

[0179] The effect of the above technical solution is: by retrieving the initial load from the database, it can be ensured that the same load conditions are used for each test, thereby improving the accuracy and repeatability of the test. At the same time, the load data in the database can be updated and expanded as needed to adapt to different test scenarios and changes in the aviation power supply system. This technical solution can comprehensively evaluate the performance and stability of the system by monitoring and recording key test data values ​​such as voltage, current, frequency and power factor of the target aviation power supply system under the initial load. These data can provide strong data support for the design and optimization of the aviation power supply system, and help improve the overall performance and reliability of the system. Through automated testing and database calls, this technical solution can significantly reduce testing costs and time. Compared with traditional manual testing methods, this technical solution is more efficient and convenient, and can greatly improve testing efficiency. By comprehensively evaluating the performance of the aviation power supply system under various load conditions, this technical solution helps to ensure that the system can operate stably in actual flight. This is of great significance for improving flight safety and reducing the risk of flight accidents.

[0180] In summary, this technical solution achieves a comprehensive evaluation and optimization of the performance of the aviation power supply system through core links such as database call, load test and data collection. This can not only improve the accuracy and repeatability of the test, but also reduce the test cost and time, while improving flight safety.

[0181] In one embodiment of the present invention, the gradient value acquisition module includes:

[0182] A test data value retrieving module, used to retrieve the test data value corresponding to the initial load capacity test of the target aviation power supply system;

[0183] A standard data value retrieving module is used to retrieve the standard data value corresponding to the initial load test;

[0184] A gradient adjustment coefficient acquisition module, used to obtain the gradient adjustment coefficient by using the difference between the test data value and the standard data value corresponding to the initial load test of the target aviation power supply system;

[0185] The gradient adjustment coefficient is obtained by the following formula:

[0186]

[0187] Where Q represents the gradient adjustment coefficient; n represents the number of types contained in the test data value, that is, n = 4; X i represents the value corresponding to the i-th test data value; X zi represents the standard data value corresponding to the i-th test data value; L0 represents the value of the initial load of the target aviation power supply system; L mIndicates the maximum value of the test load corresponding to the load test;

[0188] An initial gradient amount retrieving module is used to retrieve the initial gradient amount from the database;

[0189] A gradient value calculation module, used to obtain a gradient value of a load increase by using the gradient adjustment coefficient in combination with an initial gradient value;

[0190] The load increase gradient value is obtained by the following formula:

[0191]

[0192] Among them, L t Indicates the gradient value of load increase; L c represents the initial gradient; Q represents the gradient adjustment coefficient; L0 represents the value of the initial load of the target aviation power supply system.

[0193] The working principle of the above technical solution is: retrieve the test data values ​​of the target aviation power supply system under the initial load from the test record, and these data values ​​include key parameters such as voltage, current, frequency and power factor. At the same time, retrieve the standard data values ​​corresponding to the initial load test, which are determined based on the design specifications, performance requirements and past test experience of the aviation power supply system. The gradient adjustment coefficient Q is calculated using the difference between the test data value and the standard data value. This coefficient reflects the degree of deviation between the performance of the target aviation power supply system under the initial load and the standard performance. The n in the calculation formula represents the number of types of test data values ​​(i.e., the four parameters of voltage, current, frequency and power factor), and Xi and Xzi represent the i-th test data value and its corresponding standard data value respectively. L0 and Lm represent the initial load value of the target aviation power supply system and the maximum test load value corresponding to the load test respectively. This formula comprehensively considers the deviation between the test data value and the standard data value and the proportional relationship between the initial load and the maximum test load, thereby deriving a gradient adjustment coefficient that can reflect the degree of deviation of system performance. The initial gradient Lc is retrieved from a pre-established database. This initial gradient is determined based on system performance requirements, test objectives, and past test experience, and is used to guide the gradual increase in load. The gradient value Lt of the load increase is calculated using the gradient adjustment coefficient Q and the initial gradient value Lc, combined with the initial load value L0. This value determines the specific amount of load increase each time in subsequent load tests. The calculation formula combines the gradient adjustment coefficient Q, the initial gradient value Lc, and the initial load value L0, and derives the gradient value Lt of the load increase through a certain mathematical relationship to ensure that the load test can gradually and reasonably increase the load, thereby comprehensively evaluating the performance of the target aviation power supply system.

[0194] The effect of the above technical solution is: by introducing the gradient adjustment coefficient Q, the deviation between the test data value and the standard data value and the proportional relationship between the initial load and the maximum test load are comprehensively considered, so that the gradient value of the load increase is more consistent with the actual change of the system performance. This method can more accurately reflect the performance of the target aviation power supply system under different load conditions and improve the accuracy and scientificity of the test. By pre-establishing a database and retrieving the initial gradient value Lc, the cumbersome process of re-determining the gradient value before each test is avoided. The calculation process of the gradient adjustment coefficient Q and the gradient value Lt of the load increase can be automated, thereby improving the efficiency and automation of the test process. By gradually increasing the load and monitoring the changes in system performance, potential performance problems can be discovered and solved in a timely manner. This method helps to optimize the design parameters and structural layout of the aviation power supply system, thereby improving the overall performance and reliability of the system. Compared with the traditional load testing method, the technical solution can more quickly determine the gradient value of the load increase and carry out testing. This helps to reduce the cost and time investment of testing and improve the economy and efficiency of testing work.

[0195] On the other hand, by calculating the gradient adjustment coefficient Q, the deviations of various test data values ​​(voltage, current, frequency, power factor) from the standard data values, as well as the proportional relationship between the initial load and the maximum test load, are comprehensively considered, so that the gradient value of the load increase can be determined more accurately. This helps to improve the accuracy and reliability of the test. The method adopts the method of gradually increasing the load, which can more carefully observe and analyze the performance changes of the target aviation power supply system under different load conditions, so as to more accurately evaluate its performance and reliability. By gradually increasing the load and monitoring the changes in system performance, potential performance problems such as voltage instability, excessive current, frequency fluctuation, etc. can be discovered and solved in time. This helps to optimize the design parameters and structural layout of the aviation power supply system and improve the overall performance of the system. The method can simulate the dynamic changes of the load in actual flight, so as to evaluate the stability and reliability of the target aviation power supply system under different load conditions. By optimizing the design and adjusting the parameters, the reliability of the system can be further improved to ensure its stable operation in various complex environments. The calculation process of the gradient adjustment coefficient Q and the gradient value Lt of the load increase can be realized automatically, which reduces the time and error of manual calculation and improves the test efficiency. By pre-establishing a database and retrieving the initial gradient value Lc, the cumbersome process of redetermining the gradient value before each test is avoided, reducing the number and time of repeated tests. This method can determine the gradient value of the load increase more quickly and carry out testing work, which helps to reduce the cost and time investment of testing and improve the economy and efficiency of testing work. During the test process, the data values ​​of each test can be recorded and data analysis can be performed. This helps to trace and verify the test results later to ensure the accuracy and reliability of the test results. Since this method uses standardized test procedures and data processing methods, the test results have good repeatability. This helps to repeat the test at different times and locations to verify the stability and consistency of system performance.

[0196] In summary, the technical effects of the above technical solutions in terms of performance indicators are mainly reflected in improving the accuracy and reliability of the test, optimizing the system design and performance, reducing the test cost and time, and improving the traceability and repeatability of the test. These technical effects help to improve the overall performance and reliability of the aviation power supply system and provide a strong guarantee for flight safety. At the same time, the technical solution realizes the reasonable determination of the gradient value of the load increase and the test process of gradually increasing the load by comprehensively considering the deviation between the test data value and the standard data value, the proportional relationship between the initial load and the maximum test load, and the pre-established database information. This method can more accurately evaluate the performance of the target aviation power supply system and optimize the system design parameters and structural layout.

[0197] In one embodiment of the present invention, the second test data value acquisition module includes:

[0198] A load adjustment module, used for adjusting the initial load to a first load, a second load and a third load respectively after the initial load test is completed; wherein the first load is L0+Lt, the second load is L0+2.5Lt, and the third load is L0+5Lt; wherein L0 represents the initial load; and Lt represents the gradient value of the load increase;

[0199] A first test data value acquisition module is used to adjust the load of the target aviation power supply system from an initial load to a first load, and maintain the first load for 30 minutes to 40 minutes to obtain a first test data value; wherein the first test data value includes a test data fluctuation rate corresponding to the test data at the moment of load increase and a test data value after stabilization;

[0200] A first test data fluctuation rate value acquisition module is used to adjust the load of the target aviation power supply system to the initial load instantly after the first test data value is recorded, obtain instantaneous fluctuation data of the test data value, and record it as the first test data fluctuation rate value;

[0201] A second test data value acquisition module is used to adjust the load of the target aviation power supply system from the initial load to the second load, and maintain the second load for 20 minutes to 30 minutes to obtain a second test data value; wherein the second test data value includes the test data fluctuation rate corresponding to the test data at the moment of load increase and the test data value after stabilization;

[0202] A second test data fluctuation rate value acquisition module is used to adjust the load of the target aviation power supply system to the initial load instantly after the second test data value is recorded, obtain instantaneous fluctuation data of the test data value, and record it as the second test data fluctuation rate value;

[0203] A third test data value acquisition module is used to adjust the load of the target aviation power supply system from the initial load to the third load, and continue the third load for 15 minutes to 25 minutes to obtain a third test data value; wherein the third test data value includes the test data fluctuation rate corresponding to the test data at the moment of load increase and the test data value after stabilization;

[0204] The third test data fluctuation rate value acquisition module is used to instantly adjust the load of the target aviation power supply system to the initial load after the third test data value is recorded, obtain the instantaneous fluctuation data of the test data value, and record it as the third test data fluctuation rate value.

[0205] The working principle of the above technical solution is: after the initial load test is completed, the first load (L0+Lt), the second load (L0+2.5Lt) and the third load (L0+5Lt) are set according to the load increase gradient value Lt. These load settings are intended to simulate different load conditions that the aviation power supply system may encounter in actual flight, so as to comprehensively evaluate its performance.

[0206] For each set load (first, second, and third load), adjust the load of the target aviation power supply system from the initial load to the load and keep it for a period of time (30min-40min, 20min-30min, and 15min-25min, respectively). At the moment of load increase, record the volatility of the test data to evaluate the system's ability to respond to load changes. After the load stabilizes, record the test data value to evaluate the system's performance under the load. After the test is completed, instantly adjust the load back to the initial load, and record the instantaneous fluctuation data of the test data value, that is, the test data volatility value, to evaluate the system's load recovery capability.

[0207] The effect of the above technical solution is: by gradually increasing the load and testing at each load for a period of time, the performance of the target aviation power supply system under different load conditions can be comprehensively evaluated. This helps to discover potential problems of the system under different loads, such as voltage instability, excessive current, frequency fluctuations, etc., so as to optimize and improve them in time. By recording the test data at the moment of load increase and after the load is stable, the system's responsiveness to load changes and performance stability can be more accurately evaluated. At the same time, by recording the test data volatility value, the system load recovery capability can be further evaluated to improve the accuracy and reliability of the test. According to the test results, the design of the target aviation power supply system can be optimized, such as adjusting the circuit structure, improving the heat dissipation method, etc., to improve the system performance and reliability. This helps to reduce the failure rate of the system in actual flight and improve flight safety. By gradually increasing the load for testing, the risk of damage to the system due to excessive load applied at one time can be avoided, thereby reducing the test cost. At the same time, since the test process is carried out in stages, the test plan can be adjusted in time according to the test results to reduce unnecessary test time and waste of resources.

[0208] On the other hand, by gradually increasing the load and recording the test data fluctuation rate at the moment of load increase, the response speed and stability of the target aviation power supply system to load changes can be accurately evaluated. This helps to understand whether the system can quickly adjust and maintain stable output when facing a sudden increase in load. By testing for a period of time at each set load and recording the test data value after stabilization, the stability and reliability of the target aviation power supply system under different load conditions can be verified. This helps to ensure that the system can continuously and stably supply power in actual flight to meet flight requirements. By recording the instantaneous fluctuation data of the test data value (i.e., the test data fluctuation rate value), the recovery ability of the target aviation power supply system after load changes can be quantitatively evaluated. This helps to understand whether the system can quickly return to a stable state after a sudden decrease in load, thereby ensuring flight safety. Based on the above test results, the design of the target aviation power supply system can be optimized, such as adjusting the circuit structure, improving the heat dissipation method, optimizing the control strategy, etc., to improve system performance and reliability. This helps to reduce the failure rate of the system in actual flight and improve flight safety and economy. By gradually increasing the load for testing, the risk of damage to the system caused by applying too large a load at one time can be avoided, thereby reducing the test cost. At the same time, since the test process is carried out in stages, the test plan can be adjusted in time according to the test results, reducing unnecessary test time and resource waste. This technical solution can more accurately evaluate the performance of the target aviation power supply system by testing in stages and recording detailed data. At the same time, since the test process has clear steps and indicators, it can improve test efficiency and ensure the accuracy and reliability of test results.

[0209] In summary, the technical effects of the above-mentioned technical solutions in terms of performance indicators are mainly reflected in accurately evaluating load response capabilities, verifying system stability and reliability, quantitatively evaluating load recovery capabilities, optimizing system design and performance improvement, reducing test costs and time, and improving test efficiency and accuracy. These technical effects help to comprehensively evaluate the performance of the target aviation power supply system and provide strong protection for flight safety. At the same time, the technical solution comprehensively evaluates the performance of the target aviation power supply system under different load conditions by gradually increasing the load and recording test data. This helps to improve the accuracy and reliability of the test, optimize the system design, and reduce test costs and time.

[0210] In one embodiment of the present invention, the performance determination module includes:

[0211] A test data value retrieving module, used to retrieve a first test data value, a second test data value and a third test data value;

[0212] A first load evaluation coefficient acquisition module, used to acquire a first load evaluation coefficient using the first test data value, the second test data value and the third test data value;

[0213] The first load evaluation coefficient is obtained by the following formula:

[0214]

[0215] Among them, S 01 represents the first load evaluation coefficient; e represents the number of load tests, and e=3; L i represents the load corresponding to the i-th load test; L0 represents the value of the initial load of the target aviation power supply system; R b represents the standard deviation of the data coefficients corresponding to the three load tests; R i represents the data coefficient corresponding to the i-th test data value generated by the i-th load test, and the data coefficient corresponding to the i-th test data value is obtained by the following formula:

[0216]

[0217] Among them, R represents the data coefficient corresponding to the test data value generated by each load test; n represents the number of types contained in the test data value; X fi represents the data volatility corresponding to the i-th test data value; T fi represents the fluctuation duration corresponding to the fluctuation period of the i-th test data value; X zi represents the standard data value corresponding to the i-th test data value; X bi represents the standard deviation of the data value of the i-th test data value during the load test process; X wi represents the final stable setting of the i-th test data value during the load test;

[0218] A test data volatility value retrieving module, used to retrieve a first test data volatility value, a second test data volatility value and a third test data volatility value;

[0219] A second load evaluation coefficient acquisition module, used to acquire a second load evaluation coefficient by using the first test data volatility value, the second test data volatility value and the third test data volatility value;

[0220] The second load evaluation coefficient is obtained by the following formula:

[0221]

[0222] Among them, S 02 represents the second load evaluation coefficient; n represents the number of types contained in the test data value; X fjirepresents the data volatility corresponding to the i-th test data in the j-th instantaneous fluctuation data; X zji represents the standard data value corresponding to the i-th test data in the j-th instantaneous fluctuation data; T fji represents the fluctuation duration corresponding to the i-th test data in the j-th instantaneous fluctuation data; T ci represents the preset reference value of the fluctuation duration corresponding to the i-th test data; X maxji represents the peak value corresponding to the fluctuation process of the i-th test data in the j-th instantaneous fluctuation data; X minji Indicates the trough value corresponding to the fluctuation process of the i-th test data in the j-th instantaneous fluctuation data;

[0223] A comprehensive load evaluation coefficient acquisition module, used to obtain a comprehensive load evaluation coefficient using the first load evaluation coefficient and the second load evaluation coefficient;

[0224] The comprehensive load evaluation coefficient is obtained by the following formula:

[0225]

[0226] Where S represents the comprehensive load evaluation coefficient; S 01 Represents the first load evaluation coefficient; S 02 represents the second load evaluation coefficient;

[0227] An evaluation coefficient comparison module, used for comparing the comprehensive load evaluation coefficient with a preset load evaluation coefficient threshold;

[0228] The load performance determination module is used to determine that the load measurement performance requirement is not met when the comprehensive load evaluation coefficient is lower than a preset load evaluation coefficient threshold.

[0229] The working principle of the above technical solution is: retrieve the first test data value, the second test data value and the third test data value, which are obtained when testing the target aviation power supply system under different loads. At the same time, retrieve the test data volatility value corresponding to each test to evaluate the system's response speed and stability to load changes. Calculate the first load evaluation coefficient using the test data value (including data volatility, fluctuation duration, standard data value, data value standard deviation and final stable setting, etc.). This coefficient comprehensively considers factors such as the number of load tests, load, data coefficient standard deviation, etc., to evaluate the overall performance of the system during load changes. Calculate the second load evaluation coefficient using the test data volatility value (including data volatility, standard data value, fluctuation duration, peak value and trough value in instantaneous fluctuation data, etc.). This coefficient mainly evaluates the response speed and stability of the system at the moment of load change, as well as the characteristics of the fluctuation process. Combine the first load evaluation coefficient and the second load evaluation coefficient to calculate the comprehensive load evaluation coefficient. This coefficient is a comprehensive evaluation of the system load performance, taking into account the overall performance and instantaneous response capability during load changes. Compare the comprehensive load evaluation coefficient with the preset load evaluation coefficient threshold. If the comprehensive load evaluation coefficient is lower than the threshold, it is determined that the target aviation power supply system does not meet the load measurement performance requirements.

[0230] The effect of the above technical solution is: this technical solution can comprehensively evaluate the performance of the target aviation power supply system during load changes by comprehensively considering various data indicators (such as data volatility, fluctuation duration, standard data value, etc.) during the load test process. By introducing the first load evaluation coefficient and the second load evaluation coefficient, and combining the comprehensive load evaluation coefficient for judgment, the accuracy of the evaluation of the system load performance is improved. Based on the evaluation results, the design of the target aviation power supply system can be optimized to improve its load performance and stability. This technical solution avoids unnecessary repeated testing and reduces testing costs by testing in stages and recording detailed data. The test process has clear steps and indicators, which can quickly complete the test and obtain evaluation results, thereby improving test efficiency. By accurately evaluating the load performance of the target aviation power supply system, potential problems can be discovered and optimized in a timely manner to ensure flight safety.

[0231] On the other hand, by introducing the first load evaluation coefficient and the second load evaluation coefficient, the technical solution can accurately quantify the performance of the target aviation power supply system during load changes. These two coefficients comprehensively consider a variety of test data values, such as data volatility, fluctuation duration, standard data value, etc., so as to more accurately reflect the load performance of the system. The technical solution not only considers the overall performance during the load test (through the first load evaluation coefficient), but also considers the transient response capability (through the second load evaluation coefficient). This comprehensive evaluation method improves the comprehensiveness and accuracy of the system load performance and helps to discover potential performance bottlenecks or problems. By testing in stages and recording detailed data, the technical solution optimizes the load testing process. The test process has clear steps and indicators, and can quickly complete the test and obtain the evaluation results, thereby improving the test efficiency. Since the test process is carried out in stages and analyzed based on detailed test data, unnecessary repeated tests can be avoided. This helps to reduce the test cost while ensuring the accuracy and reliability of the test results. Based on the evaluation results, the design of the target aviation power supply system can be optimized. For example, according to the load performance evaluation results, the circuit structure can be adjusted, the heat dissipation method can be improved, or the control strategy can be optimized to improve the load performance and stability of the system. By accurately evaluating the load performance of the target aviation power supply system, potential problems can be discovered and optimized in a timely manner. This helps ensure that the system can continuously and stably supply power during flight, thereby improving flight safety. This technical solution helps to discover unstable factors in the system during load changes by comprehensively evaluating the system's load performance. By optimizing the design and improving measures, the reliability of the system can be enhanced and the failure rate can be reduced.

[0232] In summary, the technical effects of the above technical solutions in terms of performance indicators are mainly reflected in accurately quantifying load performance, improving the comprehensiveness and accuracy of evaluation, optimizing load test processes, reducing test costs, guiding system design and optimization, improving flight safety, and enhancing system reliability. These technical effects help to comprehensively evaluate the performance of the target aviation power supply system and provide strong support for system optimization and improvement. At the same time, the technical solution determines whether the system meets the load test performance requirements by comprehensively analyzing the test data values ​​in terms of working principle. In terms of technical effects, it improves the accuracy of evaluation, optimizes system design, reduces test costs, improves test efficiency, and ensures flight safety.

[0233] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. A load testing method for an aviation power supply system, characterized in that: The load testing method of the aviation power supply system comprises: Testing the target aviation power supply system to be tested according to the initial load, and obtaining test data values ​​of the target aviation power supply system; Obtaining a gradient value of load increase according to a test data value corresponding to an initial load test of the target aviation power supply system; The load is gradually increased according to the gradient value of the load increase, and a test data value of the target aviation power supply system corresponding to each load increase is obtained; Whether the operation of the target aviation power supply system meets the load test performance requirements is determined based on the test data value of the target aviation power supply system corresponding to each load increase.

2. The load testing method for the aviation power supply system according to claim 1, characterized in that: The target aviation power supply system to be tested is tested according to the initial load, and the test data values ​​of the target aviation power supply system are obtained, including: Retrieve the initial load from the database; The target aviation power supply system to be tested is tested according to the initial load, and test data values ​​of the target aviation power supply system are obtained, wherein the test data values ​​include voltage, current, frequency and power factor.

3. The load testing method for the aviation power supply system according to claim 1, characterized in that: Obtaining a load increase gradient value according to a test data value corresponding to an initial load test of the target aviation power supply system includes: Retrieve the test data value corresponding to the initial load test of the target aviation power supply system; Retrieve the standard data value corresponding to the initial load test; Obtaining a gradient adjustment coefficient using a difference between a test data value and a standard data value corresponding to an initial load test of the target aviation power supply system; Retrieve the initial gradient from the database; The gradient value of the load increase is obtained by combining the gradient adjustment coefficient with the initial gradient value.

4. The load testing method for the aviation power supply system according to claim 1, characterized in that: The load is gradually increased according to the gradient value of the load increase, and the test data value of the target aviation power supply system corresponding to each load increase is obtained, including: After the initial load test is completed, the initial load is adjusted to the first load, the second load and the third load respectively; wherein the first load is L0+Lt, the second load is L0+2.5Lt, and the third load is L0+5Lt; wherein L0 represents the initial load; Lt represents the gradient value of the load increase; The load of the target aviation power supply system is adjusted from the initial load to the first load, and the first load is maintained for 30 minutes to 40 minutes to obtain a first test data value; wherein the first test data value includes the test data fluctuation rate corresponding to the test data at the moment of load increase and the test data value after stabilization; After the first test data value is recorded, the load of the target aviation power supply system is instantly adjusted to the initial load, and the instantaneous fluctuation data of the test data value is obtained and recorded as the first test data fluctuation rate value; The load of the target aviation power supply system is adjusted from the initial load to the second load, and the second load is maintained for 20 minutes to 30 minutes to obtain a second test data value; wherein the second test data value includes the test data fluctuation rate corresponding to the test data at the moment of load increase and the test data value after stabilization; After the second test data value is recorded, the load of the target aviation power supply system is instantly adjusted to the initial load, and the instantaneous fluctuation data of the test data value is obtained and recorded as the second test data fluctuation rate value; The load of the target aviation power supply system is adjusted from the initial load to the third load, and the third load is maintained for 15 minutes to 25 minutes to obtain a third test data value; wherein the third test data value includes the test data fluctuation rate corresponding to the test data at the moment of load increase and the test data value after stabilization; After the third test data value is recorded, the load of the target aviation power supply system is instantly adjusted to the initial load, and the instantaneous fluctuation data of the test data value is obtained and recorded as the third test data fluctuation rate value.

5. The load testing method for the aviation power supply system according to claim 1, characterized in that: According to the test data value of the target aviation power supply system corresponding to each load increase, it is determined whether the operation of the target aviation power supply system meets the load test performance requirements, including: Retrieving a first test data value, a second test data value, and a third test data value; Obtaining a first load evaluation coefficient using the first test data value, the second test data value, and the third test data value; Retrieving the first test data volatility value, the second test data volatility value and the third test data volatility value; Obtaining a second load evaluation coefficient using the first test data volatility value, the second test data volatility value, and the third test data volatility value; Obtaining a comprehensive load evaluation coefficient using the first load evaluation coefficient and the second load evaluation coefficient; Comparing the comprehensive load evaluation coefficient with a preset load evaluation coefficient threshold; When the comprehensive load evaluation coefficient is lower than a preset load evaluation coefficient threshold, it is determined that the load measurement performance requirement is not met.

6. A load test system for an aviation power supply system, characterized in that: The load test system of the aviation power supply system comprises: A first test data value acquisition module is used to test the target aviation power supply system to be tested according to the initial load amount, and obtain the test data value of the target aviation power supply system; A gradient value acquisition module, used to acquire a gradient value of load increase according to a test data value corresponding to an initial load quantity test of the target aviation power supply system; A second test data value acquisition module is used to gradually increase the load according to the gradient value of the load increase, and obtain the test data value of the target aviation power supply system corresponding to each load increase; The performance determination module is used to determine whether the operation of the target aviation power supply system meets the load test performance requirements according to the test data value of the target aviation power supply system corresponding to each load increase.

7. The load test system of the aviation power supply system according to claim 6, characterized in that: The first test data value acquisition module includes: An initial load volume retrieving module is used to retrieve the initial load volume from a database; The initial test module is used to test the target aviation power supply system to be tested according to the initial load, and obtain the test data values ​​of the target aviation power supply system, wherein the test data values ​​include voltage, current, frequency and power factor.

8. The load test system of the aviation power supply system according to claim 6, characterized in that: The gradient value acquisition module comprises: A test data value retrieving module, used to retrieve the test data value corresponding to the initial load capacity test of the target aviation power supply system; A standard data value retrieving module is used to retrieve the standard data value corresponding to the initial load test; A gradient adjustment coefficient acquisition module, used to obtain the gradient adjustment coefficient by using the difference between the test data value and the standard data value corresponding to the initial load test of the target aviation power supply system; An initial gradient amount retrieving module is used to retrieve the initial gradient amount from the database; The gradient value calculation module is used to obtain the gradient value of the load increase by using the gradient adjustment coefficient in combination with the initial gradient value.

9. The load test system of the aviation power supply system according to claim 6, characterized in that: The second test data value acquisition module includes: A load adjustment module, used for adjusting the initial load to a first load, a second load and a third load respectively after the initial load test is completed; wherein the first load is L0+Lt, the second load is L0+2.5Lt, and the third load is L0+5Lt; wherein L0 represents the initial load; and Lt represents the gradient value of the load increase; A first test data value acquisition module is used to adjust the load of the target aviation power supply system from an initial load to a first load, and maintain the first load for 30 minutes to 40 minutes to obtain a first test data value; wherein the first test data value includes a test data fluctuation rate corresponding to the test data at the moment of load increase and a test data value after stabilization; A first test data fluctuation rate value acquisition module is used to adjust the load of the target aviation power supply system to the initial load instantly after the first test data value is recorded, obtain instantaneous fluctuation data of the test data value, and record it as the first test data fluctuation rate value; A second test data value acquisition module is used to adjust the load of the target aviation power supply system from the initial load to the second load, and maintain the second load for 20 minutes to 30 minutes to obtain a second test data value; wherein the second test data value includes the test data fluctuation rate corresponding to the test data at the moment of load increase and the test data value after stabilization; A second test data fluctuation rate value acquisition module is used to adjust the load of the target aviation power supply system to the initial load instantly after the second test data value is recorded, obtain instantaneous fluctuation data of the test data value, and record it as the second test data fluctuation rate value; A third test data value acquisition module is used to adjust the load of the target aviation power supply system from the initial load to the third load, and continue the third load for 15 minutes to 25 minutes to obtain a third test data value; wherein the third test data value includes the test data fluctuation rate corresponding to the test data at the moment of load increase and the test data value after stabilization; The third test data fluctuation rate value acquisition module is used to instantly adjust the load of the target aviation power supply system to the initial load after the third test data value is recorded, obtain the instantaneous fluctuation data of the test data value, and record it as the third test data fluctuation rate value.

10. The load test system of the aviation power supply system according to claim 6, characterized in that: The performance determination module comprises: A test data value retrieving module, used to retrieve a first test data value, a second test data value and a third test data value; A first load evaluation coefficient acquisition module, used to acquire a first load evaluation coefficient using the first test data value, the second test data value and the third test data value; A test data volatility value retrieving module, used to retrieve a first test data volatility value, a second test data volatility value and a third test data volatility value; A second load evaluation coefficient acquisition module, used to acquire a second load evaluation coefficient by using the first test data volatility value, the second test data volatility value and the third test data volatility value; A comprehensive load evaluation coefficient acquisition module, used to obtain a comprehensive load evaluation coefficient using the first load evaluation coefficient and the second load evaluation coefficient; An evaluation coefficient comparison module, used for comparing the comprehensive load evaluation coefficient with a preset load evaluation coefficient threshold; The load performance determination module is used to determine that the load measurement performance requirement is not met when the comprehensive load evaluation coefficient is lower than a preset load evaluation coefficient threshold.

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