A load testing method and system for aviation power supply system

Abstract

The present invention proposes a load testing method and system for an aviation power supply system. The load testing method for an aviation power supply system includes: testing a target aviation power supply system to be tested according to an initial load, and obtaining a test data value of the target aviation power supply system; obtaining a load increase gradient value according to the test data value corresponding to the initial load test of the target aviation power supply system; gradually increasing the load according to the load increase gradient value, and obtaining a test data value of the target aviation power supply system corresponding to each load increase; and determining 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. The system includes modules corresponding to the steps of the method.

Description

Technical Field

[0001] The present 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, aviation power supply systems, as a crucial component of aircraft, have become increasingly important. Their stability and reliability are directly linked to flight safety and mission success. Aviation power supply systems must not only meet the aircraft's power requirements under normal flight conditions but also maintain power to critical equipment during emergencies or abnormal situations. Therefore, comprehensive and rigorous testing of aviation power supply systems to ensure their stable operation under various load conditions is an essential component of the aviation industry. Traditional testing methods for aviation power supply systems rely primarily on static load testing, which involves observing and recording system operating parameters such as voltage, current, frequency, and power factor under preset fixed load conditions to evaluate system performance. However, this method often fails to fully reflect the various dynamic load variations that the system may encounter during actual flight. In particular, sudden increases or decreases in load make it difficult to fully verify the system's responsiveness and stability. Furthermore, with the increasing number of avionics equipment and power demands, aviation power supply systems face increasingly complex load environments. Traditional static load testing methods are no longer sufficient to meet the performance testing requirements of modern aviation power supply systems. A testing method that can simulate the dynamic load variations experienced during actual flight and accurately evaluate system performance under various load conditions is urgently needed. 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 system simulates the dynamic changes of the load during actual flight, and acquires and analyzes the test data values ​​of the system in real time, thereby comprehensively evaluating 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, further improving 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. 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 load increase gradient value according to a test data value corresponding to an initial load test of the target aviation power supply system;

[0007] gradually increasing the load according to the gradient value of the load increase, and obtaining test data values ​​of the target aviation power supply system corresponding to each load increase;

[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] Furthermore, 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] Furthermore, obtaining a load increase gradient value 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 values ​​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] Among them, Q represents the gradient adjustment coefficient; n represents the number of types contained in the test data value, that is, n=4; X i Indicates 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] Obtaining a gradient value of load increase by using the gradient adjustment coefficient in combination with an 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] Furthermore, the load is gradually increased according to the gradient value of the load increase, and test data values ​​of the target aviation power supply system corresponding to each load increase are 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] Adjust the load of the target aviation power supply system from the initial load to a first load, and maintain the first load for 30 minutes to 40 minutes, and 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 instantaneous fluctuation data of the test data value is obtained and recorded as a first test data fluctuation rate value;

[0028] Adjust the load of the target aviation power supply system from the initial load to a second load, and maintain the second load for 20 minutes to 30 minutes, and 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 instantaneous fluctuation data of the test data value is obtained and recorded as the second test data fluctuation rate value;

[0030] 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, 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 instantaneous fluctuation data of the test data value is obtained and recorded as the third test data fluctuation rate value.

[0032] Furthermore, determining 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 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 Indicates 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 T represents the fluctuation duration corresponding to the i-th test data in the j-th instantaneous fluctuation data; ci represents the preset reference value of the fluctuation duration corresponding to the i-th test data; X maxji Indicates 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] Among them, S represents the comprehensive load evaluation coefficient; S 01 Indicates 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 configured to test a target aviation power supply system to be tested according to an initial load, and acquire a test data value of the target aviation power supply system;

[0053] a gradient value acquisition module, configured to acquire a gradient value of load increase based on a test data value corresponding to an initial load 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 a 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 based on 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 capacity retrieving module is used to retrieve the initial load capacity 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 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 is used to retrieve the test data value corresponding to the initial load 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, configured to obtain a gradient adjustment coefficient by 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;

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

[0064]

[0065] Among them, Q represents the gradient adjustment coefficient; n represents the number of types contained in the test data value, that is, n=4; X i Indicates 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 value retrieving module is used to retrieve the initial gradient value from the database;

[0067] A gradient value calculation module is 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 is configured to adjust 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 configured to adjust the load of the target aviation power supply system from an initial load to a first load, maintaining the first load for 30-40 minutes, and acquire 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 configured to, after the first test data value is recorded, instantly adjust the load of the target aviation power supply system to the initial load, obtain instantaneous fluctuation data of the test data value, and record the data as the first test data fluctuation rate value;

[0075] A second test data value acquisition module is configured to adjust the load of the target aviation power supply system from an initial load to a second load, maintaining the second load for 20 minutes to 30 minutes, and acquire a second test data value; wherein the second 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;

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

[0077] a third test data value acquisition module, configured to adjust the load of the target aviation power supply system from the initial load to a third load, maintaining the third load for 15-25 minutes, and acquire 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;

[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, configured 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, configured 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 Indicates 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 is 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, configured to acquire 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;

[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 T represents the fluctuation duration corresponding to the i-th test data in the j-th instantaneous fluctuation data; ci represents the preset reference value of the fluctuation duration corresponding to the i-th test data; X maxji Indicates 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, configured to acquire 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] Among them, S represents the comprehensive load evaluation coefficient; S 01 Indicates the first load evaluation coefficient; S 02 represents the second load evaluation coefficient;

[0096] An evaluation coefficient comparison module, configured to compare the comprehensive load evaluation coefficient with a preset load evaluation coefficient threshold;

[0097] The load performance determination module is configured to determine that the load 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, thereby more accurately evaluating 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 testing 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 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 A flow chart of the method of the present invention;

[0101] Figure 2 This is a system block diagram of the system of the present invention. DETAILED DESCRIPTION

[0102] The preferred embodiments of the present invention are described below with reference to 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 testing 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 test data values ​​of the target aviation power supply system;

[0105] S2. Obtaining a load increase gradient value based on 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 test data values ​​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 that represents the basic load requirements of the aviation power supply system under normal flight conditions. The target aviation power supply system is then tested under this load condition, and key test data such as voltage, current, frequency, power factor, and temperature are recorded and acquired. Based on the results of the initial load test and in conjunction with the design specifications and performance requirements of the aviation power supply system, a load increase gradient is calculated and determined. This gradient represents the amount of each load increase, ensuring that the test process fully covers possible load variations while preventing system damage or data distortion due to excessive load changes. The system load is gradually increased according to the determined load increase gradient. After each load increase, the target aviation power supply system is retested and the corresponding test data are recorded. This process simulates the gradual load changes experienced during actual flight to observe the system's response and performance under different load conditions. Based on the test data obtained after each load increase and in conjunction with the performance requirements and standards of the aviation power supply system, the system's operating status is assessed. This includes evaluating the system's voltage stability, current output capability, frequency retention, and thermal management capabilities. 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 test data values ​​of the target aviation power supply system are 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 objectives 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 above technical solution achieves the following benefits: by retrieving the initial load from a database, the same load conditions are used for each test, thereby improving test accuracy and repeatability. Furthermore, the load data in the database can be updated and expanded as needed to accommodate different test scenarios and changes in the aviation power supply system. By monitoring and recording key test data such as voltage, current, frequency, and power factor of the target aviation power supply system under the initial load, this technical solution comprehensively assesses the system's performance and stability. This data provides strong support for the design and optimization of the aviation power supply system, helping to improve its overall performance and reliability. Through automated testing and database access, this technical solution significantly reduces testing costs and time. Compared to traditional manual testing methods, this technical solution is more efficient and convenient, significantly improving testing efficiency. By comprehensively evaluating the performance of the aviation power supply system under various load conditions, this technical solution helps ensure the system's stable operation during 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 comprehensive performance evaluation and optimization of aviation power supply systems through core processes such as database access, load testing, and data collection. This not only improves test accuracy and repeatability, but also reduces testing costs and time, while enhancing flight safety.

[0116] In one embodiment of the present invention, 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:

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

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

[0119] S203, 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;

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

[0121]

[0122] Among them, Q represents the gradient adjustment coefficient; n represents the number of types contained in the test data value, that is, n=4; X i Indicates 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 as follows: test data values ​​of the target aviation power supply system under initial load are retrieved from test records. These data values ​​include key parameters such as voltage, current, frequency, and power factor. Standard data values ​​corresponding to the initial load test are also retrieved. These standard data values ​​are determined based on the design specifications, performance requirements, and past testing experience of the aviation power supply system. The difference between the test data values ​​and the standard data values ​​is used to calculate the gradient adjustment coefficient Q. This coefficient reflects the degree of deviation between the performance of the target aviation power supply system under initial load and the standard performance. In the calculation formula, n represents the number of test data value types (i.e., the four parameters of voltage, current, frequency, and power factor), 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 values ​​and the standard data values ​​and the ratio between the initial load and the maximum test load, thereby deriving a gradient adjustment coefficient that reflects the degree of deviation of system performance. The initial gradient value 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 adjustment coefficient Q and the initial gradient Lc, combined with the initial load L0, are used to calculate the load increase gradient value Lt. 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 Lc, and the initial load L0, and derives the load increase gradient value Lt 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 above technical solution achieves the following benefits: By introducing the gradient adjustment coefficient Q, the load increase gradient value is more accurately aligned with actual system performance changes, taking into account the deviation between the test data value and the standard data value, as well as the ratio between the initial load and the maximum test load. This method can more accurately reflect the performance of the target aviation power supply system under different load conditions, improving the accuracy and scientific nature of the test. By pre-establishing a database and retrieving the initial gradient value Lc, the tedious process of re-determining the gradient value before each test is avoided. The calculation of the gradient adjustment coefficient Q and the load increase gradient value Lt can be automated, thereby improving the efficiency and automation of the testing process. By gradually increasing the load and monitoring the changes in system performance, potential performance issues can be promptly identified and resolved. This method helps 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 traditional load testing methods, this technical solution can more quickly determine the load increase gradient value and conduct testing. This helps reduce testing costs and time, improving the cost-effectiveness and efficiency of testing.

[0130] Furthermore, by calculating the gradient adjustment coefficient Q, the deviations of various test data values ​​(voltage, current, frequency, and power factor) from the standard data values, as well as the ratio between the initial load and the maximum test load, are comprehensively considered. This allows for a more precise determination of the load increase gradient value. This helps improve test accuracy and reliability. This method, which employs a gradual load increase approach, allows for more detailed observation and analysis of the performance changes of the target aviation power supply system under different load conditions, leading to a more accurate assessment of its performance and reliability. By gradually increasing the load and monitoring the changes in system performance, potential performance issues such as voltage instability, excessive current, and frequency fluctuation can be promptly identified and addressed. This helps optimize the design parameters and structural layout of the aviation power supply system, improving overall system performance. This method can simulate the dynamic load changes experienced during actual flight, thereby assessing the stability and reliability of the target aviation power supply system under different load conditions. By optimizing the design and adjusting parameters, system reliability can be further improved, ensuring stable operation in various complex environments. The calculation of the gradient adjustment coefficient Q and the load increase gradient value Lt can be automated, reducing manual calculation time and errors and improving testing efficiency. By pre-establishing a database and retrieving the initial gradient value Lc, the tedious process of redetermining the gradient value before each test is avoided, reducing the number and time of repeated tests. This method can more quickly determine the gradient value of the load increase and carry out testing work, helping to reduce testing costs and time investment, and improve the economy and efficiency of testing work. During the test process, the data values ​​of each test can be recorded and analyzed. This facilitates subsequent traceability and verification of test results, ensuring the accuracy and reliability of the test results. Because this method uses standardized testing procedures and data processing methods, the test results have good repeatability. This facilitates repeated testing at different times and locations to verify the stability and consistency of system performance.

[0131] In summary, the technical benefits of the above-mentioned technical solution in terms of performance indicators are mainly reflected in improving test accuracy and reliability, optimizing system design and performance, reducing test costs and time, and enhancing test traceability and repeatability. These technical benefits help improve the overall performance and reliability of aviation power supply systems, providing a strong guarantee for flight safety. Furthermore, by comprehensively considering the deviation between test data values ​​and standard data values, the ratio between initial load and maximum test load, and pre-established database information, this technical solution achieves the rational determination of load increase gradient values ​​and the gradual increase of load test process. This approach can more accurately evaluate the performance of the target aviation power supply system and optimize 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 test data values ​​of the target aviation power supply system corresponding to each load increase are 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: Adjust the load of the target aviation power supply system from the initial load to a first load, and maintain the first load for 30-40 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;

[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 a first test data fluctuation rate value;

[0136] S304: Adjust the load of the target aviation power supply system from the initial load to a second load, maintaining the second load for 20 minutes to 30 minutes, and obtain a second test data value; wherein the second 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;

[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 a second test data fluctuation rate value.

[0138] S306: Adjust the load of the target aviation power supply system from the initial load to a third load, and maintain the third load for 15 minutes to 25 minutes, and 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;

[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 instantaneous fluctuation data of the test data value is obtained and recorded as a third test data fluctuation rate value.

[0140] The working principle of the above technical solution is as follows: After the initial load test is completed, the first load (L0+Lt), second load (L0+2.5Lt), and third load (L0+5Lt) are set according to the load increase gradient value Lt. These load settings are intended to simulate the 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), the load of the target aviation power supply system is adjusted from the initial load to the load and maintained for a period of time (30min-40min, 20min-30min, and 15min-25min, respectively). At the moment of load increase, the volatility of the test data is recorded to evaluate the system's response to load changes. After the load stabilizes, the test data value is recorded to evaluate the system's performance under the load. After the test is completed, the load is instantly adjusted back to the initial load, and the instantaneous fluctuation data of the test data value, that is, the test data volatility value, is recorded to evaluate the system's load recovery capability.

[0142] The above technical solution achieves this by gradually increasing the load and testing at each load for a period of time, enabling a comprehensive assessment of the performance of the target aviation power supply system under different load conditions. This helps identify potential system issues under different loads, such as voltage instability, excessive current, and frequency fluctuations, enabling timely optimization and improvement. Recording test data both immediately after the load increases and after the load stabilizes allows for a more accurate assessment of the system's responsiveness to load changes and performance stability. Furthermore, by recording the test data volatility, the system's load recovery capability can be further assessed, improving the accuracy and reliability of the test. Based on the test results, the design of the target aviation power supply system can be optimized, such as by adjusting the circuit structure and improving heat dissipation methods, to enhance system performance and reliability. This helps reduce the system's failure rate during actual flight and improve flight safety. By gradually increasing the load during testing, the risk of system damage caused by applying excessive load all at once is avoided, thereby reducing testing costs. Furthermore, because the testing process is conducted in stages, the test plan can be adjusted promptly based on the test results, reducing unnecessary testing time and resources.

[0143] On the other hand, by gradually increasing the load and recording the test data fluctuation rate at the instantaneous load increase, the target aviation power supply system's response speed and stability to load changes can be accurately assessed. This helps determine whether the system can quickly adjust and maintain stable output when faced with a sudden load increase. By testing at each set load for a period of time and recording the test data values ​​after stabilization, the stability and reliability of the target aviation power supply system under different load conditions can be verified. This helps ensure that the system can continuously and stably provide power and meet flight requirements during actual flight. By recording the instantaneous fluctuations in the test data values ​​(i.e., the test data fluctuation rate), the target aviation power supply system's recovery capability after load changes can be quantitatively assessed. This helps determine whether the system can quickly recover to a stable state after a sudden load decrease, thereby ensuring flight safety. Based on these test results, the design of the target aviation power supply system can be optimized, such as adjusting the circuit structure, improving heat dissipation methods, and optimizing the control strategy, to improve system performance and reliability. This helps reduce the system's failure rate during actual flight, improving flight safety and economic efficiency. By gradually increasing the load during testing, the risk of system damage caused by applying an excessive load at once can be avoided, thereby reducing testing costs. Furthermore, because the testing process is conducted in phases, the test plan can be adjusted promptly based on test results, reducing unnecessary testing time and resource waste. By conducting phased testing and recording detailed data, this technical solution allows for a more accurate assessment of the performance of the target aviation power supply system. Furthermore, because the testing process has clear steps and indicators, it improves testing efficiency and ensures the accuracy and reliability of test results.

[0144] In summary, the technical benefits of the above-mentioned technical solution in terms of performance indicators are primarily reflected in accurately assessing load responsiveness, verifying system stability and reliability, quantitatively assessing load recovery capabilities, optimizing system design and performance, reducing testing costs and time, and improving test efficiency and accuracy. These technical benefits help comprehensively evaluate the performance of the target aviation power supply system, providing a strong guarantee for flight safety. Furthermore, by gradually increasing the load and recording test data, the technical solution comprehensively evaluates the performance of the target aviation power supply system under different load conditions. This helps improve test accuracy and reliability, optimize system design, and reduce testing 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 based on 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 coefficient 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 Indicates 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 T represents the fluctuation duration corresponding to the i-th test data in the j-th instantaneous fluctuation data; ci represents the preset reference value of the fluctuation duration corresponding to the i-th test data; X maxji Indicates 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: Obtain 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] Among them, S represents the comprehensive load evaluation coefficient; S 01 Indicates 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 as follows: first, second, and third test data values ​​are retrieved. These data are obtained when testing the target aviation power supply system under different loads. Simultaneously, the test data fluctuation rate corresponding to each test is retrieved to evaluate the system's response speed and stability to load changes. The test data values ​​(including data fluctuation rate, fluctuation duration, standard data value, data value standard deviation, and final stable setting) are used to calculate a first load evaluation coefficient. This coefficient comprehensively considers factors such as the number of load tests, load, and data coefficient standard deviation to evaluate the system's overall performance during load changes. The second load evaluation coefficient is calculated using the test data fluctuation rate values ​​(including data fluctuation rate, standard data value, fluctuation duration, peak and trough values ​​in the instantaneous fluctuation data). This coefficient primarily evaluates the system's response speed and stability during load changes, as well as the characteristics of the fluctuation process. Combining the first and second load evaluation coefficients, a comprehensive load evaluation coefficient is calculated. This coefficient comprehensively evaluates the system's load performance, taking into account its overall performance and transient response capability during load changes. The comprehensive load evaluation coefficient is then compared with a 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 test 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 multiple 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, thereby ensuring flight safety.

[0166] Furthermore, by introducing a first and second load evaluation coefficient, this technical solution can accurately quantify the performance of the target aviation power supply system during load fluctuations. These two coefficients comprehensively consider various test data values, such as data volatility, fluctuation duration, and standard data values, thereby more accurately reflecting the system's load performance. This technical solution not only considers the overall performance during the load test (via the first load evaluation coefficient) but also the transient response capability (via the second load evaluation coefficient). This comprehensive evaluation approach improves the comprehensiveness and accuracy of the system's load performance, helping to identify potential performance bottlenecks or issues. By conducting tests in stages and recording detailed data, this technical solution optimizes the load testing process. The testing process has clear steps and indicators, enabling rapid completion and evaluation of results, thereby improving testing efficiency. Because the testing process is conducted in stages and analyzed based on detailed test data, unnecessary retesting can be avoided. This helps reduce testing costs while ensuring the accuracy and reliability of test results. Based on the evaluation results, the design of the target aviation power supply system can be optimized. For example, based on the load performance evaluation results, circuit structure adjustments, improved heat dissipation methods, or optimized control strategies can be used to improve the system's load performance and stability. By accurately assessing the load performance of the target aviation power supply system, potential issues can be promptly identified and optimized. This helps ensure continuous and stable power supply during flight, thereby improving flight safety. This technical solution, through comprehensive evaluation of the system's load performance, helps identify unstable factors during load fluctuations. Through optimized design and improvement measures, system reliability can be enhanced and failure rates reduced.

[0167] In summary, the technical benefits of the aforementioned technical solution in terms of performance indicators are primarily reflected in accurately quantifying load performance, improving the comprehensiveness and accuracy of assessments, optimizing the load testing process, reducing testing costs, guiding system design and optimization, improving flight safety, and enhancing system reliability. These technical benefits facilitate a comprehensive assessment of the performance of the target aviation power supply system and provide strong support for system optimization and improvement. Furthermore, the technical solution operates by comprehensively analyzing test data values ​​to determine whether the system meets load test performance requirements. This technical benefit improves assessment accuracy, optimizes system design, reduces testing 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. Figure 2 As shown, the load testing system of the aviation power supply system includes:

[0169] A first test data value acquisition module is configured to test a target aviation power supply system to be tested according to an initial load, and acquire a test data value of the target aviation power supply system;

[0170] a gradient value acquisition module, configured to acquire a gradient value of load increase based on a test data value corresponding to an initial load 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 a 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 based on 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 that represents the basic load requirements of the aviation power supply system under normal flight conditions. The target aviation power supply system is then tested under this load condition, and key test data such as voltage, current, frequency, power factor, and temperature are recorded and acquired. Based on the results of the initial load test and in conjunction with the design specifications and performance requirements of the aviation power supply system, a load increase gradient is calculated and determined. This gradient represents the amount of each load increase, ensuring that the test process fully covers possible load variations while preventing system damage or data distortion due to excessive load changes. The system load is gradually increased according to the determined load increase gradient. After each load increase, the target aviation power supply system is retested and the corresponding test data are recorded. This process simulates the gradual load changes experienced during actual flight to observe the system's response and performance under different load conditions. Based on the test data obtained after each load increase and in conjunction with the performance requirements and standards of the aviation power supply system, the system's operating status is assessed. This includes evaluating the system's voltage stability, current output capability, frequency retention, and thermal management capabilities. 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 capacity retrieving module is used to retrieve the initial load capacity 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 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 objectives 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 above technical solution achieves the following benefits: by retrieving the initial load from a database, the same load conditions are used for each test, thereby improving test accuracy and repeatability. Furthermore, the load data in the database can be updated and expanded as needed to accommodate different test scenarios and changes in the aviation power supply system. By monitoring and recording key test data such as voltage, current, frequency, and power factor of the target aviation power supply system under the initial load, this technical solution comprehensively assesses the system's performance and stability. This data provides strong support for the design and optimization of the aviation power supply system, helping to improve its overall performance and reliability. Through automated testing and database access, this technical solution significantly reduces testing costs and time. Compared to traditional manual testing methods, this technical solution is more efficient and convenient, significantly improving testing efficiency. By comprehensively evaluating the performance of the aviation power supply system under various load conditions, this technical solution helps ensure the system's stable operation during 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 comprehensive performance evaluation and optimization of aviation power supply systems through core processes such as database access, load testing, and data collection. This not only improves test accuracy and repeatability, but also reduces testing costs and time, while enhancing flight safety.

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

[0182] A test data value retrieving module is used to retrieve the test data value corresponding to the initial load 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, configured to obtain a gradient adjustment coefficient by 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;

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

[0186]

[0187] Among them, Q represents the gradient adjustment coefficient; n represents the number of types contained in the test data value, that is, n=4; X i Indicates 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 value retrieving module is used to retrieve the initial gradient value from the database;

[0189] A gradient value calculation module is 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 as follows: test data values ​​of the target aviation power supply system under initial load are retrieved from test records. These data values ​​include key parameters such as voltage, current, frequency, and power factor. Standard data values ​​corresponding to the initial load test are also retrieved. These standard data values ​​are determined based on the design specifications, performance requirements, and past testing experience of the aviation power supply system. The difference between the test data values ​​and the standard data values ​​is used to calculate the gradient adjustment coefficient Q. This coefficient reflects the degree of deviation between the performance of the target aviation power supply system under initial load and the standard performance. In the calculation formula, n represents the number of test data value types (i.e., the four parameters of voltage, current, frequency, and power factor), 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 values ​​and the standard data values ​​and the ratio between the initial load and the maximum test load, thereby deriving a gradient adjustment coefficient that reflects the degree of deviation of system performance. The initial gradient value 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 adjustment coefficient Q and the initial gradient Lc, combined with the initial load L0, are used to calculate the load increase gradient value Lt. 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 Lc, and the initial load L0, and derives the load increase gradient value Lt 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 above technical solution achieves the following benefits: By introducing the gradient adjustment coefficient Q, the load increase gradient value is more accurately aligned with actual system performance changes, taking into account the deviation between the test data value and the standard data value, as well as the ratio between the initial load and the maximum test load. This method can more accurately reflect the performance of the target aviation power supply system under different load conditions, improving the accuracy and scientific nature of the test. By pre-establishing a database and retrieving the initial gradient value Lc, the tedious process of re-determining the gradient value before each test is avoided. The calculation of the gradient adjustment coefficient Q and the load increase gradient value Lt can be automated, thereby improving the efficiency and automation of the testing process. By gradually increasing the load and monitoring the changes in system performance, potential performance issues can be promptly identified and resolved. This method helps 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 traditional load testing methods, this technical solution can more quickly determine the load increase gradient value and conduct testing. This helps reduce testing costs and time, improving the cost-effectiveness and efficiency of testing.

[0195] Furthermore, by calculating the gradient adjustment coefficient Q, the deviations of various test data values ​​(voltage, current, frequency, and power factor) from the standard data values, as well as the ratio between the initial load and the maximum test load, are comprehensively considered. This allows for a more precise determination of the load increase gradient value. This helps improve test accuracy and reliability. This method, which employs a gradual load increase approach, allows for more detailed observation and analysis of the performance changes of the target aviation power supply system under different load conditions, leading to a more accurate assessment of its performance and reliability. By gradually increasing the load and monitoring the changes in system performance, potential performance issues such as voltage instability, excessive current, and frequency fluctuation can be promptly identified and addressed. This helps optimize the design parameters and structural layout of the aviation power supply system, improving overall system performance. This method can simulate the dynamic load changes experienced during actual flight, thereby assessing the stability and reliability of the target aviation power supply system under different load conditions. By optimizing the design and adjusting parameters, system reliability can be further improved, ensuring stable operation in various complex environments. The calculation of the gradient adjustment coefficient Q and the load increase gradient value Lt can be automated, reducing manual calculation time and errors and improving testing efficiency. By pre-establishing a database and retrieving the initial gradient value Lc, the tedious process of redetermining the gradient value before each test is avoided, reducing the number and time of repeated tests. This method can more quickly determine the gradient value of the load increase and carry out testing work, helping to reduce testing costs and time investment, and improve the economy and efficiency of testing work. During the test process, the data values ​​of each test can be recorded and analyzed. This facilitates subsequent traceability and verification of test results, ensuring the accuracy and reliability of the test results. Because this method uses standardized testing procedures and data processing methods, the test results have good repeatability. This facilitates repeated testing at different times and locations to verify the stability and consistency of system performance.

[0196] In summary, the technical benefits of the above-mentioned technical solution in terms of performance indicators are mainly reflected in improving test accuracy and reliability, optimizing system design and performance, reducing test costs and time, and enhancing test traceability and repeatability. These technical benefits help improve the overall performance and reliability of aviation power supply systems, providing a strong guarantee for flight safety. Furthermore, by comprehensively considering the deviation between test data values ​​and standard data values, the ratio between initial load and maximum test load, and pre-established database information, this technical solution achieves the rational determination of load increase gradient values ​​and the gradual increase of load test process. This approach can more accurately evaluate the performance of the target aviation power supply system and optimize 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 is configured to adjust 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 configured to adjust the load of the target aviation power supply system from an initial load to a first load, maintaining the first load for 30-40 minutes, and acquire 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 configured to, after the first test data value is recorded, instantly adjust the load of the target aviation power supply system to the initial load, obtain instantaneous fluctuation data of the test data value, and record the data as the first test data fluctuation rate value;

[0201] A second test data value acquisition module is configured to adjust the load of the target aviation power supply system from an initial load to a second load, maintaining the second load for 20 minutes to 30 minutes, and acquire a second test data value; wherein the second 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;

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

[0203] a third test data value acquisition module, configured to adjust the load of the target aviation power supply system from the initial load to a third load, maintaining the third load for 15-25 minutes, and acquire 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;

[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 as follows: After the initial load test is completed, the first load (L0+Lt), second load (L0+2.5Lt), and third load (L0+5Lt) are set according to the load increase gradient value Lt. These load settings are intended to simulate the 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), the load of the target aviation power supply system is adjusted from the initial load to the load and maintained for a period of time (30min-40min, 20min-30min, and 15min-25min, respectively). At the moment of load increase, the volatility of the test data is recorded to evaluate the system's response to load changes. After the load stabilizes, the test data value is recorded to evaluate the system's performance under the load. After the test is completed, the load is instantly adjusted back to the initial load, and the instantaneous fluctuation data of the test data value, that is, the test data volatility value, is recorded to evaluate the system's load recovery capability.

[0207] The above technical solution achieves this by gradually increasing the load and testing at each load for a period of time, enabling a comprehensive assessment of the performance of the target aviation power supply system under different load conditions. This helps identify potential system issues under different loads, such as voltage instability, excessive current, and frequency fluctuations, enabling timely optimization and improvement. Recording test data both immediately after the load increases and after the load stabilizes allows for a more accurate assessment of the system's responsiveness to load changes and performance stability. Furthermore, by recording the test data volatility, the system's load recovery capability can be further assessed, improving the accuracy and reliability of the test. Based on the test results, the design of the target aviation power supply system can be optimized, such as by adjusting the circuit structure and improving heat dissipation methods, to enhance system performance and reliability. This helps reduce the system's failure rate during actual flight and improve flight safety. By gradually increasing the load during testing, the risk of system damage caused by applying excessive load all at once is avoided, thereby reducing testing costs. Furthermore, because the testing process is conducted in stages, the test plan can be adjusted promptly based on the test results, reducing unnecessary testing time and resources.

[0208] On the other hand, by gradually increasing the load and recording the test data fluctuation rate at the instantaneous load increase, the target aviation power supply system's response speed and stability to load changes can be accurately assessed. This helps determine whether the system can quickly adjust and maintain stable output when faced with a sudden load increase. By testing at each set load for a period of time and recording the test data values ​​after stabilization, the stability and reliability of the target aviation power supply system under different load conditions can be verified. This helps ensure that the system can continuously and stably provide power and meet flight requirements during actual flight. By recording the instantaneous fluctuations in the test data values ​​(i.e., the test data fluctuation rate), the target aviation power supply system's recovery capability after load changes can be quantitatively assessed. This helps determine whether the system can quickly recover to a stable state after a sudden load decrease, thereby ensuring flight safety. Based on these test results, the design of the target aviation power supply system can be optimized, such as adjusting the circuit structure, improving heat dissipation methods, and optimizing the control strategy, to improve system performance and reliability. This helps reduce the system's failure rate during actual flight, improving flight safety and economic efficiency. By gradually increasing the load during testing, the risk of system damage caused by applying an excessive load at once can be avoided, thereby reducing testing costs. Furthermore, because the testing process is conducted in phases, the test plan can be adjusted promptly based on test results, reducing unnecessary testing time and resource waste. By conducting phased testing and recording detailed data, this technical solution allows for a more accurate assessment of the performance of the target aviation power supply system. Furthermore, because the testing process has clear steps and indicators, it improves testing efficiency and ensures the accuracy and reliability of test results.

[0209] In summary, the technical benefits of the above-mentioned technical solution in terms of performance indicators are primarily reflected in accurately assessing load responsiveness, verifying system stability and reliability, quantitatively assessing load recovery capabilities, optimizing system design and performance, reducing testing costs and time, and improving test efficiency and accuracy. These technical benefits help comprehensively evaluate the performance of the target aviation power supply system, providing a strong guarantee for flight safety. Furthermore, by gradually increasing the load and recording test data, the technical solution comprehensively evaluates the performance of the target aviation power supply system under different load conditions. This helps improve test accuracy and reliability, optimize system design, and reduce testing costs and time.

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

[0211] A test data value retrieving module, configured 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, configured 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 coefficient 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 Indicates 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 is 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, configured to acquire 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;

[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 T represents the fluctuation duration corresponding to the i-th test data in the j-th instantaneous fluctuation data; ci represents the preset reference value of the fluctuation duration corresponding to the i-th test data; X maxji Indicates 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, configured to acquire 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] Among them, S represents the comprehensive load evaluation coefficient; S 01 Indicates the first load evaluation coefficient; S 02 represents the second load evaluation coefficient;

[0227] An evaluation coefficient comparison module, configured to compare the comprehensive load evaluation coefficient with a preset load evaluation coefficient threshold;

[0228] The load performance determination module is configured to determine that the load 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 as follows: first, second, and third test data values ​​are retrieved. These data are obtained when testing the target aviation power supply system under different loads. Simultaneously, the test data fluctuation rate corresponding to each test is retrieved to evaluate the system's response speed and stability to load changes. The test data values ​​(including data fluctuation rate, fluctuation duration, standard data value, data value standard deviation, and final stable setting) are used to calculate a first load evaluation coefficient. This coefficient comprehensively considers factors such as the number of load tests, load, and data coefficient standard deviation to evaluate the system's overall performance during load changes. The second load evaluation coefficient is calculated using the test data fluctuation rate values ​​(including data fluctuation rate, standard data value, fluctuation duration, peak and trough values ​​in the instantaneous fluctuation data). This coefficient primarily evaluates the system's response speed and stability during load changes, as well as the characteristics of the fluctuation process. Combining the first and second load evaluation coefficients, a comprehensive load evaluation coefficient is calculated. This coefficient comprehensively evaluates the system's load performance, taking into account its overall performance and transient response capability during load changes. The comprehensive load evaluation coefficient is then compared with a 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 test 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 multiple 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, thereby ensuring flight safety.

[0231] Furthermore, by introducing a first and second load evaluation coefficient, this technical solution can accurately quantify the performance of the target aviation power supply system during load fluctuations. These two coefficients comprehensively consider various test data values, such as data volatility, fluctuation duration, and standard data values, thereby more accurately reflecting the system's load performance. This technical solution not only considers the overall performance during the load test (via the first load evaluation coefficient) but also the transient response capability (via the second load evaluation coefficient). This comprehensive evaluation approach improves the comprehensiveness and accuracy of the system's load performance, helping to identify potential performance bottlenecks or issues. By conducting tests in stages and recording detailed data, this technical solution optimizes the load testing process. The testing process has clear steps and indicators, enabling rapid completion and evaluation of results, thereby improving testing efficiency. Because the testing process is conducted in stages and analyzed based on detailed test data, unnecessary retesting can be avoided. This helps reduce testing costs while ensuring the accuracy and reliability of test results. Based on the evaluation results, the design of the target aviation power supply system can be optimized. For example, based on the load performance evaluation results, circuit structure adjustments, improved heat dissipation methods, or optimized control strategies can be used to improve the system's load performance and stability. By accurately assessing the load performance of the target aviation power supply system, potential issues can be promptly identified and optimized. This helps ensure continuous and stable power supply during flight, thereby improving flight safety. This technical solution, through comprehensive evaluation of the system's load performance, helps identify unstable factors during load fluctuations. Through optimized design and improvement measures, system reliability can be enhanced and failure rates reduced.

[0232] In summary, the technical benefits of the aforementioned technical solution in terms of performance indicators are primarily reflected in accurately quantifying load performance, improving the comprehensiveness and accuracy of assessments, optimizing the load testing process, reducing testing costs, guiding system design and optimization, improving flight safety, and enhancing system reliability. These technical benefits facilitate a comprehensive assessment of the performance of the target aviation power supply system and provide strong support for system optimization and improvement. Furthermore, the technical solution operates by comprehensively analyzing test data values ​​to determine whether the system meets load test performance requirements. This technical benefit improves assessment accuracy, optimizes system design, reduces testing costs, improves test efficiency, and ensures flight safety.

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

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 includes: 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 load increase gradient value according to a test data value corresponding to an initial load test of the target aviation power supply system; gradually increasing the load according to the gradient value of the load increase, and obtaining test data values ​​of the target aviation power supply system corresponding to each load increase; 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; The obtaining of 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: S201, retrieve test data values ​​corresponding to the initial load test of the target aviation power supply system; S202, retrieve the standard data value corresponding to the initial load test; S203, 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; The gradient adjustment coefficient is obtained by the following formula: Among them, Q represents the gradient adjustment coefficient; n represents the number of types contained in the test data value, that is, n=4; X i Indicates 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; S204, retrieving the initial gradient value from the database; S205. Utilize the gradient adjustment coefficient in combination with the initial gradient value to obtain a gradient value of the load increase; wherein the gradient value of the load increase is obtained by the following formula: 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.

2. The load testing method for an aviation power supply system according to claim 1, characterized in that: Test the target aviation power supply system according to the initial load and obtain test data values ​​of the target aviation power supply system, 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 an 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; Adjust the load of the target aviation power supply system from the initial load to a first load, and maintain the first load for 30 minutes to 40 minutes, and 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 instantaneous fluctuation data of the test data value is obtained and recorded as a first test data fluctuation rate value; Adjust the load of the target aviation power supply system from the initial load to a second load, and maintain the second load for 20 minutes to 30 minutes, and 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 instantaneous fluctuation data of the test data value is obtained and recorded as the second test data fluctuation rate value; 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, 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 instantaneous fluctuation data of the test data value is obtained and recorded as the third test data fluctuation rate value.

4. The load testing method for an aviation power supply system according to claim 1, characterized in that: 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, 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.

5. A load test system for an aviation power supply system, characterized in that: The load testing system of the aviation power supply system includes: A first test data value acquisition module is configured to test a target aviation power supply system to be tested according to an initial load, and acquire a test data value of the target aviation power supply system; a gradient value acquisition module, configured to acquire a gradient value of load increase based on a test data value corresponding to an initial load 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 a test data value of the target aviation power supply system corresponding to each load increase; A performance determination module is used to 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; The gradient value acquisition module includes: A test data value retrieving module is used to retrieve the test data value corresponding to the initial load 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; The gradient adjustment coefficient acquisition module is 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; wherein the gradient adjustment coefficient is obtained by the following formula: Among them, Q represents the gradient adjustment coefficient; n represents the number of types contained in the test data value, that is, n=4; X i Indicates 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; An initial gradient value retrieving module is used to retrieve the initial gradient value 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; wherein the gradient value of the load increase is obtained by the following formula: 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.

6. The load testing system for the aviation power supply system according to claim 5, characterized in that: The first test data value acquisition module includes: An initial load amount retrieving module is used to retrieve the initial load amount from the 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 test data values ​​of the target aviation power supply system, wherein the test data values ​​include voltage, current, frequency and power factor.

7. The load testing system for the aviation power supply system according to claim 5, characterized in that: The second test data value acquisition module includes: A load adjustment module is configured to adjust 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 configured to adjust the load of the target aviation power supply system from an initial load to a first load, maintaining the first load for 30-40 minutes, and acquire 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 configured to, after the first test data value is recorded, instantly adjust the load of the target aviation power supply system to the initial load, obtain instantaneous fluctuation data of the test data value, and record the data as the first test data fluctuation rate value; A second test data value acquisition module is configured to adjust the load of the target aviation power supply system from an initial load to a second load, maintaining the second load for 20 minutes to 30 minutes, and acquire a second test data value; wherein the second 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 second test data fluctuation rate value acquisition module is configured to, after the second test data value is recorded, instantly adjust the load of the target aviation power supply system to the initial load, obtain instantaneous fluctuation data of the test data value, and record the data as the second test data fluctuation rate value; a third test data value acquisition module, configured to adjust the load of the target aviation power supply system from the initial load to a third load, maintaining the third load for 15-25 minutes, and acquire 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; 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.

8. The load testing system for the aviation power supply system according to claim 5, characterized in that: The performance determination module includes: A test data value retrieving module, configured 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, configured 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 is 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, configured to acquire 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; a comprehensive load evaluation coefficient acquisition module, configured to acquire a comprehensive load evaluation coefficient using the first load evaluation coefficient and the second load evaluation coefficient; An evaluation coefficient comparison module, configured to compare the comprehensive load evaluation coefficient with a preset load evaluation coefficient threshold; The load performance determination module is configured to determine that the load performance requirement is not met when the comprehensive load evaluation coefficient is lower than a preset load evaluation coefficient threshold.

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