Aircraft power supply system detection method, detection equipment and storage medium

Abstract

The invention is suitable for the technical field of avionics equipment, and provides an aircraft power supply system detection method, detection equipment and a storage medium. The method comprises the following steps: acquiring an aircraft power supply system detection instruction, wherein the aircraft power supply system detection instruction is used for indicating a to-be-detected aircraft power supply system and a target test item; based on the aircraft power supply system detection instruction, a target test case file is called, and the target test case file comprises a test step and a qualification criterion corresponding to the target test item; automatically detecting the to-be-detected aircraft power supply system based on the test steps, and acquiring test data including AC voltage, frequency, DC voltage and output current respectively corresponding to the to-be-detected aircraft power supply system in a steady state and a transient state; and determining a detection result of the to-be-detected aircraft power supply system based on the test data and a qualification criterion. According to the technical scheme provided by the invention, the automation degree of aircraft power supply system detection is improved, and the detection efficiency of the aircraft power supply system is improved.

Description

Technical Field

[0001] The present application belongs to the technical field of avionics equipment, and in particular, relates to a detection method, detection equipment and storage medium for an aircraft power supply system. Background Art

[0002] Aircraft power supply system test equipment is a ground power supply test equipment used to verify the correctness of functions and performances such as AC and DC grid power supply, logic control, protection and voltage regulation during the aircraft assembly stage.

[0003] The testing content of aircraft power supply system testing equipment mainly includes the testing and verification of key components such as power supply, power equipment, power lines and batteries in the aircraft power supply system. The purpose of the test is to ensure that the aircraft power supply system can work normally under various working conditions, meet the power demand of the aircraft, and ensure flight safety. However, the existing aircraft power supply system testing equipment is not automated enough, and usually requires operators to perform testing operations manually, resulting in low testing efficiency.

[0004] Therefore, how to improve the detection efficiency of aircraft power supply systems has become an urgent problem to be solved. Summary of the invention

[0005] The embodiments of the present application provide an aircraft power supply system detection method, detection equipment and storage medium, aiming to improve the detection efficiency of the aircraft power supply system.

[0006] In a first aspect, an embodiment of the present application provides an aircraft power supply system detection method, which is applied to an aircraft power supply system detection device, the method comprising: obtaining an aircraft power supply system detection instruction, the aircraft power supply system detection instruction being used to indicate an aircraft power supply system to be detected and a target test item; based on the aircraft power supply system detection instruction, calling a target test case file, the target test case file comprising test steps and qualification criteria corresponding to the target test items; based on the test steps, automatically detecting the aircraft power supply system to be detected, and obtaining test data, the test data comprising the AC voltage, frequency, DC voltage and output current corresponding to the aircraft power supply system to be detected in steady state and transient state, respectively; based on the test data and the qualification criteria, determining the detection result of the aircraft power supply system to be detected.

[0007] In a possible implementation, the automatic detection of the power supply system of the aircraft to be detected based on the test steps and the acquisition of test data include: determining the complexity of the target test item based on the target test item and a first preset mapping relationship, the first preset mapping relationship representing the mapping relationship between the test item and the complexity of the test item; determining target test setting information based on the complexity of the target test item and a second preset mapping relationship, the second preset mapping relationship representing the mapping relationship between the complexity of the test item and the test setting information, the test setting information including test speed and test accuracy; automatically detecting the power supply system of the aircraft to be detected based on the test steps and the target test setting information, and acquiring the test data.

[0008] In a possible implementation, the automatic detection of the power supply system of the aircraft to be detected based on the test steps and the acquisition of test data include: based on the test steps, acquiring test step selection information, the test step selection information including one or more steps in the test steps; based on the test step selection information, the automatic detection of the power supply system of the aircraft to be detected and the acquisition of the test data.

[0009] In a possible implementation, the target test case file also includes a target test channel; before automatically testing the power supply system of the aircraft to be tested based on the test steps and obtaining test data, the method also includes: inputting an excitation signal to the power supply system of the aircraft to be tested through the target test channel; obtaining a feedback voltage value of the power supply system of the aircraft to be tested based on the excitation signal through the target test channel; and determining a self-test result of the target test channel based on the feedback voltage value.

[0010] In one possible implementation, the target test case file also includes a standard voltage value corresponding to the target test channel; after determining the self-test result of the target test channel based on the feedback voltage value, the method also includes: when the self-test result of the target test channel is passed, calibrating the target test channel based on the feedback voltage value and the standard voltage value using a least squares method and a Levenberg-Marquardt method.

[0011] In a possible implementation, the target test case file also includes a detection method, and the detection method includes automatic detection; before automatically detecting the power supply system of the aircraft to be detected based on the test steps and obtaining test data, the method also includes: obtaining a detection method selection instruction, and the detection method selection instruction is used to indicate the detection method of each test step; based on the detection method selection instruction, determining whether the test step is automatic detection; when the detection method corresponding to the test step is automatic detection, executing the step of automatically detecting the power supply system of the aircraft to be detected based on the test steps and obtaining test data.

[0012] In a possible implementation, before obtaining the aircraft power supply system detection instruction, the method further includes: obtaining an interface configuration file, the interface configuration file including interface configuration information of the aircraft power supply system to be detected; and performing interface configuration of the aircraft power supply system to be detected based on the interface configuration file.

[0013] In a possible implementation, after determining the test result of the power supply system of the aircraft to be tested based on the test data and the qualification criterion, the method further includes: automatically generating a test report based on the test data and the test result.

[0014] In a second aspect, an embodiment of the present application provides an aircraft power supply system detection device, the device comprising:

[0015] A main control computer is used to obtain an aircraft power supply system detection instruction, wherein the aircraft power supply system detection instruction is used to indicate the aircraft power supply system to be detected and a target test item; based on the aircraft power supply system detection instruction, call a target test case file, wherein the target test case file includes test steps and qualification criteria corresponding to the target test item; and automatically detect the aircraft power supply system to be detected based on the test steps;

[0016] A data acquisition device, used to acquire test data, wherein the test data includes the AC voltage, frequency, DC voltage and output current corresponding to the power supply system of the aircraft to be tested in steady state and transient state respectively;

[0017] The main control computer is also used to determine the test result of the power supply system of the aircraft to be tested based on the test data and the qualification criterion.

[0018] In a third aspect, an embodiment of the present application provides a computer-readable storage medium, wherein the computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the method described in the first aspect or any one of the implementation methods thereof is implemented.

[0019] In a fourth aspect, an embodiment of the present application provides a computer program product, which includes a computer program, and when the computer program is executed by a processor, it implements the steps of the method described in the first aspect or any one of the implementation methods thereof.

[0020] Compared with the prior art, the embodiments of the present application have the following beneficial effects: by obtaining an aircraft power supply system detection instruction for indicating the aircraft power supply system to be detected and the target test item, a target test case file containing test steps and qualification criteria corresponding to the target test item is directly called, and the aircraft power supply system to be detected is automatically detected based on the test steps and test data is obtained, and then based on the test data and the qualification criteria, the detection result of the aircraft power supply system to be detected is determined, without the need for an operator to manually perform a test operation, thereby improving the degree of automation of the aircraft power supply system detection and at the same time improving the detection efficiency of the aircraft power supply system. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0022] Figure 1 A schematic diagram of the architecture of an aircraft power supply system detection device provided in one embodiment of the present application;

[0023] Figure 2 A schematic diagram of a connection method between an aircraft power supply system detection device and an aircraft power supply device provided in an embodiment of the present application;

[0024] Figure 3 A schematic diagram of the architecture of a test management software system provided in one embodiment of the present application;

[0025] Figure 4 A schematic diagram of the interaction between various modules of a test management software system provided in one embodiment of the present application;

[0026] Figure 5 A schematic diagram of a flow chart of a method for detecting an aircraft power supply system provided in one embodiment of the present application;

[0027] Figure 6 A flowchart of another aircraft power supply system detection method provided in an embodiment of the present application. DETAILED DESCRIPTION

[0028] In the following description, specific details such as specific system structures, technologies, etc. are provided for the purpose of illustration rather than limitation, so as to provide a thorough understanding of the embodiments of the present application. However, it should be clear to those skilled in the art that the present application may also be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to prevent unnecessary details from obstructing the description of the present application.

[0029] It should be understood that when used in the present specification and the appended claims, the term "comprising" indicates the presence of described features, wholes, steps, operations, elements and / or components, but does not exclude the presence or addition of one or more other features, wholes, steps, operations, elements, components and / or combinations thereof.

[0030] It should also be understood that the term “and / or” used in the specification and appended claims refers to any and all possible combinations of one or more of the associated listed items, and includes these combinations.

[0031] As used in the specification and appended claims of this application, the term "if" can be interpreted as "when" or "uponce" or "in response to determining" or "in response to detecting", depending on the context. Similarly, the phrase "if it is determined" or "if [described condition or event] is detected" can be interpreted as meaning "uponce it is determined" or "in response to determining" or "uponce [described condition or event] is detected" or "in response to detecting [described condition or event]", depending on the context.

[0032] In addition, in the description of the present application specification and the appended claims, the terms "first", "second", "third", etc. are only used to distinguish the descriptions and cannot be understood as indicating or implying relative importance.

[0033] References to "one embodiment" or "some embodiments" etc. described in the specification of this application mean that one or more embodiments of the present application include specific features, structures or characteristics described in conjunction with the embodiment. Therefore, the statements "in one embodiment", "in some embodiments", "in some other embodiments", "in some other embodiments", etc. that appear in different places in this specification do not necessarily refer to the same embodiment, but mean "one or more but not all embodiments", unless otherwise specifically emphasized in other ways. The terms "including", "comprising", "having" and their variations all mean "including but not limited to", unless otherwise specifically emphasized in other ways.

[0034] Aircraft power supply system test equipment is a ground power supply test equipment used to verify the correctness of functions and performances such as AC and DC grid power supply, logic control, protection and voltage regulation during the aircraft assembly stage.

[0035] The inspection content of the aircraft power supply system inspection equipment mainly includes the testing and verification of key components such as the power supply, power equipment, power lines and batteries in the aircraft power supply system. The purpose of the inspection is to ensure that the aircraft power supply system can work normally under various working conditions, meet the power demand of the aircraft, and ensure flight safety. However, the existing aircraft power supply system inspection equipment has insufficient automation, and usually requires operators to perform manual testing operations, including connecting test cables, installing test tools, manually recording data, and manually analyzing results. The degree of automation of the inspection equipment directly affects the inspection efficiency and the accuracy of the inspection results. If the degree of automation of the inspection equipment is insufficient, it may lead to problems such as cumbersome inspection process, low inspection efficiency or inaccurate inspection results. If there are omissions or misjudgments in the inspection process, potential problems in the aircraft power supply system cannot be discovered and handled in a timely manner, posing a major safety hazard.

[0036] In addition, aircraft power supply system testing equipment usually needs to have a high degree of integration, and needs to be designed and implemented by comprehensively considering multiple factors (such as test parameters, test accuracy, test speed, test type, etc.). If the testing equipment is not designed and implemented properly, it may lead to problems such as imperfect testing functions or insufficient testing accuracy, resulting in low accuracy of the test results.

[0037] In order to solve the above-mentioned technical problems, the present application provides an aircraft power supply system detection method, which is applied to an aircraft power supply system detection device to obtain an aircraft power supply system detection instruction, the aircraft power supply system detection instruction is used to indicate the aircraft power supply system to be detected and the target test item; based on the aircraft power supply system detection instruction, the target test case file is called, the target test case file includes test steps and qualification criteria corresponding to the target test items; based on the test steps, the aircraft power supply system to be detected is automatically detected, and test data is obtained, the test data includes the AC voltage, frequency, DC voltage and output current corresponding to the aircraft power supply system to be detected in steady state and transient state respectively; based on the test data and qualification criteria, the detection result of the aircraft power supply system to be detected is determined, thereby improving the detection efficiency of the aircraft power supply system.

[0038] For ease of understanding, the technical solution of the present application will be described in detail below with reference to the accompanying drawings.

[0039] Figure 1 This is a schematic diagram of the architecture of an aircraft power supply system detection device provided in one embodiment of the present application. Figure 1As shown, the aircraft power supply system detection device 10 includes a main control computer 11 and a data acquisition device 12, and the main control computer 11 and the data acquisition device 12 are connected via a cable.

[0040] Specifically, the main control computer 11 is the core controller in the aircraft power supply system detection device 10, which is responsible for the control of the overall detection process and data processing; the data acquisition device 12 is used for data acquisition; the aircraft power supply system detection device 10 is equipped with a test management software system for implementing the following Figure 5 and Figure 6 The aircraft power supply system detection method is shown.

[0041] As an example, the main control computer 11 is used to obtain an aircraft power supply system detection instruction, which is used to indicate the aircraft power supply system to be detected and the target test items; based on the aircraft power supply system detection instruction, the target test case file is called, and the target test case file includes test steps and qualification criteria corresponding to the target test items; based on the test steps, the aircraft power supply system to be detected is automatically detected.

[0042] As an example, the data acquisition device 12 is used to collect test data, including the AC voltage, frequency, DC voltage, and output current of the power supply system of the aircraft to be tested in steady state and transient state. The data acquisition device 12 includes a high-speed acquisition card, a current sensor, a current clamp, and the like.

[0043] As an example, the main control computer 11 is also used to determine the test result of the power supply system of the aircraft to be tested based on the test data and the qualification criteria.

[0044] In one embodiment, the aircraft power supply system detection device 10 further includes a signal conditioning disconnect box, which is connected to the data acquisition device 12 via a cable and is connected to the aircraft to be detected via a cable. The signal conditioning disconnect box is composed of a signal conditioning disconnect box device, a power supply device, a current sensor, and a current clamp, and is used to transfer, condition, and disconnect the analog active signal obtained from the power supply system of the aircraft to be detected.

[0045] In one embodiment, the aircraft power supply system detection device 10 further includes a linear power supply (not shown in the figure), which is used to supply power to the signal conditioning disconnect box, the current sensor and the current clamp.

[0046] In one embodiment, the aircraft power supply system detection device 10 is connected to the aircraft to be detected via a cable, and the cable is mainly used to realize the signal transmission and control connection functions between the aircraft power supply system detection device 10 and the aircraft power supply system to be detected.

[0047] Specifically, the cable includes a T-cable, and the T-cable includes a switching cable, a test cable, a switching socket, and a switching plug.

[0048] In the specific implementation, Figure 2 As shown, the adapter cable is connected to the adapter socket and adapter plug at both ends to achieve the connection between the onboard plug and the aircraft power supply equipment. The test cable is tapped from the adapter plug and welded to connect the test cable to the rear panel connector of the signal conditioning disconnect box in the aircraft power supply system detection equipment 10.

[0049] Understandably, Figure 1 The schematic diagram of the structure shown is only an example of the aircraft power supply system detection device 10 provided by the present application. In other embodiments of the present application, the aircraft power supply system detection device 10 may include more or fewer components than shown in the figure, or combine some components, or split some components, or arrange the components differently. For example, the aircraft power supply system detection device 10 may also include a relay box. The components shown in the figure may be implemented in hardware, software, or a combination of software and hardware, and the present application does not limit this.

[0050] Figure 3 The present invention provides a schematic diagram of the architecture of a test management software system provided in one embodiment of the present invention. The test management software is based on LabView as a development platform, which can drive the corresponding interface board to generate an excitation signal, provide an excitation input for the power supply system of the aircraft to be tested, and collect, transmit and process the working parameters generated by the power supply system of the aircraft to be tested based on the excitation input, complete the status display and control of the power supply system of the aircraft to be tested, and is used for functional testing and product performance testing.

[0051] Specifically, Figure 3 As shown, the test management software system includes a user interaction layer, a functional logic layer and an interface driver layer. The user interaction layer includes a software user interface; the functional logic layer includes an automatic test module, a data management module, a report generation module, an ICD management module, a resource management module and a user management module; and the interface driver layer includes an interface driver module.

[0052] As an example, the software user interface is a graphical human-computer interaction interface that can simulate the system display interface and provide human-computer interaction operations. The software user interface can be customized and developed according to actual needs, and the software user interface is designed based on the principles of user habits, arrangement, security, flexibility, and humanization.

[0053] Exemplarily, the software user interface can display test items, test results, step prompts, and test data such as ground power supply voltage and battery voltage; it provides control buttons such as start test, pause test, save progress, stop test, system self-check, calibration, and cable detection, and the corresponding functions can be achieved by clicking the buttons; the top of the interface provides buttons such as test, topology map, voltage detection, bus detection, and data management, and by clicking the buttons, you can jump to the corresponding interface.

[0054] As an example, the automatic testing module imports and reads editable test case files, checks the corresponding test content for automatic testing, and can identify the complexity of the test items corresponding to different test cases. According to the complexity, the test speed and test accuracy of the hardware boards in the aircraft power supply system detection equipment are automatically set to complete routine tests and high-precision complex tests (such as distortion spectrum tests) to ensure the accuracy of the test results.

[0055] Exemplarily, the test case file is in EXCEL format, and the test case can be customized according to the EXCEL file template to meet different test requirements. The test case file includes test steps, operation and prompt information, detection method, detection content, qualified judgment criteria, and parameter source, etc. For example, by reading the parameter source in the test case file, different subroutines are run to perform corresponding types of tests.

[0056] As an example, the data management module is used to manage and store the test data collected during the detection process, and can read the saved files for playback to perform data analysis.

[0057] Exemplarily, the test data collected during the detection process include the AC voltage value, frequency value, DC voltage value, and output current value of the power supply system of the aircraft to be tested in steady state and transient state.

[0058] As an example, the report generation module has a report generation toolkit that can customize the creation of test reports and automatically generate test reports after the test is completed.

[0059] Exemplarily, the test report is output in WORD format, and the test report includes information such as a voltage waveform diagram, test results, and test data.

[0060] As an example, the ICD management module is used to configure the interface control document (ICD) of the power supply system of the aircraft to be tested. The interface control document includes the interface configuration of the input / output signals / messages in the power supply system of the aircraft to be tested (including the name, type, identification, length, data type, encoding method, parsing or conversion method and other attributes of each message / signal). With the help of the ICD configuration information, the real-time parsing of the received data / signal and the automatic generation and output of the output data / signal can be dynamically completed, thereby realizing the bus function of the simulated aircraft management system.

[0061] As an example, the resource management module is used to test the management software for self-test, metering and channel calibration.

[0062] Exemplarily, the standard value of the channel to be detected is input through the jumper of the signal conditioning disconnect box, and the detection value of the channel to be detected is obtained. Through the standard value and the detection value, the generalized least squares method and the Levenberg-Marquardt method are cyclically called to realize the calibration of the channel to be detected. In addition, the test values ​​of all displayed test channels can be synchronously refreshed on the calibration interface to realize one-key calibration of multiple channels.

[0063] Exemplarily, an excitation signal is input into the power supply system of the aircraft to be detected through the channel to be detected, and a feedback voltage value of the power supply system of the aircraft to be detected based on the excitation signal is obtained through the channel to be detected; based on the feedback voltage value, it is determined whether the channel to be detected is functioning normally to determine the self-test result of the channel to be detected.

[0064] As an example, the user management module includes a user interface and user authority management functions, and the administrator can assign user authorities on the user interface according to the responsibilities of the testers.

[0065] As an example, the interface driver module is used to call the relevant hardware boards in the aircraft power supply system detection equipment used in the detection process to generate excitation or perform data collection.

[0066] Exemplarily, the relevant hardware boards and cards in the aircraft power supply system detection equipment used in the detection process include the 1394 board, data acquisition card, serial port board and relay board in the main control computer; the high-voltage acquisition and conditioning board, low-voltage acquisition and conditioning board, ground / open signal acquisition and conditioning board and current signal conditioning board in the signal conditioning disconnect box.

[0067] In the specific implementation, Figure 4As shown, the tester inputs the operation instructions through the software user interface, the ICD management module realizes the import of the interface configuration file through the software user interface, the automatic test module imports the test case file according to the operation instructions input by the user, and inputs the stimulus data to the power supply system of the aircraft to be tested and collects the test data through the interface driver module, processes the test data, and displays the test results and test data and other information in the software user interface. The data management module stores the test data and test results and other information, and sends the data used to generate the test report to the report generation module, and the report generation module generates the test report.

[0068] Understandably, Figure 3 The architecture diagram shown is only an example of the test management software provided by the present application. In other embodiments of the present application, the test management software may include more or fewer components than shown in the diagram, or combine certain components, or split certain components, or arrange the components differently, for example. The components shown in the diagram may be implemented in hardware, software, or a combination of software and hardware, and the present application does not limit this.

[0069] Figure 5 This is a flow chart of a method for detecting an aircraft power supply system provided in an embodiment of the present application. For the sake of convenience, only the part related to the present embodiment is shown. The method provided in the present embodiment is applied to Figure 1 The aircraft power supply system detection device 10 shown in the figure, the method provided in this embodiment includes the following steps:

[0070] S501, obtaining an aircraft power supply system detection instruction, where the aircraft power supply system detection instruction is used to indicate an aircraft power supply system to be detected and a target test item.

[0071] Specifically, the aircraft power supply system to be tested is the power supply system used in the aircraft to be tested; the target test item is the item that the aircraft power supply system to be tested needs to be tested in this test; the aircraft power supply system test instruction includes the identification information of the aircraft power supply system to be tested and the identification information of the target test item, the identification information of the aircraft power supply system to be tested may include the name or number of the aircraft power supply system to be tested, and the identification information of the target test item may include the name or number of the target test item. For example, the target test item is the Expression for Load Management Center (ELMC) enable / disable status check test.

[0072] In a specific implementation, the operator inputs an aircraft power supply system detection instruction in the human-computer interaction interface provided by the main control computer, and determines the aircraft power supply system to be detected and the target test item for this test based on the identification information of the aircraft power supply system to be detected and the identification information of the target test item carried in the aircraft power supply system detection instruction.

[0073] S502, based on the aircraft power supply system detection instruction, calling the target test case file, the target test case file includes test steps and qualification criteria corresponding to the target test items.

[0074] Specifically, the test case file is based on EXCEL, and the test case can be customized according to the EXCEL file template to meet different test requirements. Test case files for different test items of different aircraft power supply systems are pre-set and stored in the main control computer.

[0075] In a specific implementation, after receiving the aircraft power supply system detection instruction, based on the identification information of the aircraft power supply system to be detected in the aircraft power supply system detection instruction, the target test case file corresponding to it is called, and the target test case file includes the test steps and qualified criteria corresponding to the target test items. In addition, according to actual needs, the content of the target test case file can be customized and modified, which improves the flexibility of aircraft power supply system detection.

[0076] S503, automatically testing the power supply system of the aircraft to be tested based on the test steps, and acquiring test data, the test data including the AC voltage, frequency, DC voltage and output current corresponding to the power supply system of the aircraft to be tested in steady state and transient state respectively.

[0077] In the specific implementation, after reading the target test case file, the relevant hardware boards used in this test are called according to the test steps in the target test case file. Through these hardware boards, excitation signals are input into the power supply system of the aircraft to be tested, and the signals generated by each component in the power supply system of the aircraft to be tested based on the excitation signals, that is, test data, are obtained.

[0078] S504, based on the test data and the qualification criteria, determining the test result of the power supply system of the aircraft to be tested.

[0079] Specifically, the qualified criterion includes the qualified value range corresponding to each test data, and the test results include pass and fail.

[0080] In a specific implementation, when the acquired test data is within the corresponding qualified value range, it is determined that the component in the power supply system of the aircraft to be inspected corresponding to the test data has passed the test; when the acquired test data is not within the corresponding qualified value range, it is determined that the component in the power supply system of the aircraft to be inspected corresponding to the test data has failed the test.

[0081] The technical solution provided by the present application directly calls the target test case file containing the test steps and qualification criteria corresponding to the target test items by obtaining the aircraft power supply system detection instructions for indicating the aircraft power supply system to be detected and the target test items, automatically detects the aircraft power supply system to be detected based on the test steps and obtains the test data, and then determines the detection result of the aircraft power supply system to be detected based on the test data and the qualification criteria, without the need for operators to manually perform test operations, thereby improving the degree of automation of aircraft power supply system detection and at the same time improving the detection efficiency of the aircraft power supply system.

[0082] On the basis of the above-mentioned embodiment, this embodiment further illustrates and optimizes the technical solution. Specifically, in this embodiment, the power supply system of the aircraft to be tested is automatically tested based on the test steps, and the test data is obtained, including:

[0083] Determine the complexity of the target test item based on the target test item and a first preset mapping relationship, wherein the first preset mapping relationship represents a mapping relationship between the test item and the complexity of the test item;

[0084] Determine target test setting information based on the complexity of the target test item and a second preset mapping relationship, the second preset mapping relationship represents a mapping relationship between the complexity of the test item and the test setting information, the test setting information includes a test speed and a test accuracy;

[0085] Based on the test steps and target test setting information, the power supply system of the aircraft to be tested is automatically tested and the test data is obtained.

[0086] In the specific implementation, the complexity of the target test item is first determined based on the target test item and the first preset mapping relationship, and then the test speed and test accuracy for the target test item are determined based on the complexity of the target test item and the second preset mapping relationship, that is, the test speed and test accuracy of the hardware board used to complete the target test item; according to different test speeds and test accuracy, the target test items can be divided into conventional test items and high-precision complex test items (such as distortion spectrum testing); for high-precision complex test items, higher test speeds and test accuracy are required for automatic detection to ensure the accuracy of the detection results.

[0087] It can be seen that the technical solution provided in this embodiment adopts different test speeds and test accuracies for test items of different complexity, thereby improving the accuracy and efficiency of aircraft power supply system detection.

[0088] On the basis of the above-mentioned embodiment, this embodiment further illustrates and optimizes the technical solution. Specifically, in this embodiment, the power supply system of the aircraft to be tested is automatically tested based on the test steps, and the test data is obtained, including:

[0089] Based on the test steps, obtaining test step selection information, the test step selection information including one or more steps in the test steps;

[0090] Based on the test step selection information, the power supply system of the aircraft to be tested is automatically tested and the test data is obtained.

[0091] In a specific implementation, after reading the target test case file, the tester can select the required test steps from the test steps provided in the target test case file in the human-computer interaction interface and check them according to actual needs. The main control computer obtains the test step selection information according to the tester's checking operation, and further automatically detects the power supply system of the aircraft to be tested according to the test steps selected in the test step selection information, and obtains the test data.

[0092] It can be seen that the technical solution provided in this embodiment can select test steps according to actual needs, thereby improving the flexibility of aircraft power supply system detection and at the same time improving the detection efficiency of the aircraft power supply system.

[0093] Based on the above embodiment, this embodiment further illustrates and optimizes the technical solution. Specifically, in this embodiment, the target test case file also includes a target test channel; before automatically testing the power supply system of the aircraft to be tested based on the test steps and obtaining the test data, the method also includes:

[0094] Input an excitation signal to the power supply system of the aircraft to be tested through the target test channel;

[0095] Obtaining the feedback voltage value of the power supply system of the aircraft to be tested based on the excitation signal through the target test channel;

[0096] Based on the feedback voltage value, a self-test result of the target test channel is determined.

[0097] Specifically, the target test case file also includes a target test channel. Before automatically testing the power supply system of the aircraft to be tested, it is necessary to first perform a self-test on the target test channel to ensure that the target test channel can transmit signals normally.

[0098] In a specific implementation, an excitation signal is first input into the power supply system of the aircraft to be tested through the target test channel; then, a feedback voltage value of the power supply system of the aircraft to be tested based on the excitation signal is obtained through the target test channel. If the received feedback voltage value is within the qualified criterion range, the self-test result of the target test channel is determined to be passed.

[0099] It can be seen that the technical solution provided in this embodiment performs a self-check on the test channel before testing to ensure that the test channel can transmit signals, thereby improving the accuracy of the aircraft power supply system detection.

[0100] On the basis of the above embodiment, this embodiment further illustrates and optimizes the technical solution. Specifically, in this embodiment, the target test case file also includes a standard voltage value corresponding to the target test channel; after determining the self-test result of the target test channel based on the feedback voltage value, the method also includes:

[0101] When the self-test result of the target test channel is passed, the target test channel is calibrated based on the feedback voltage value and the standard voltage value by using the least square method and the Levenberg-Marquardt method.

[0102] Specifically, when the self-test result of the target test channel is passed, the target test channel needs to be further calibrated to ensure the accuracy of the signal transmitted by the target test channel.

[0103] In a specific implementation, the feedback voltage value and the standard voltage value are fitted by cyclically calling the generalized least squares method and the Levenberg-Marquardt method, thereby reducing the uncertainty and error of the transmission signal to achieve the calibration of the target test channel.

[0104] As an example, the feedback voltage value and the standard voltage value are fitted to the generalized straight line equation represented by the following equation by cyclically calling the generalized least square method and the Levenberg-Marquardt method:

[0105] f=ax+b

[0106] Where x is the input sequence, a is the slope, and b is the intercept. We need to get the best fitting a and b values ​​for the observation point (X, Y).

[0107] The following equation is used to describe the linear curve obtained by the linear fitting algorithm:

[0108] y[i]=ax[i]+b

[0109] If the noise of Y is Gaussian, the least squares method is used. When using the least squares method, the slope and intercept of the linear model can be obtained by minimizing the residual according to the following equation:

[0110]

[0111] Where N is the length of Y, w i is the weight of the i-th element, fi is the i-th element of the best linear fit, and yi is the i-th element of Y.

[0112] It can be seen that by calibrating the target test channel, the accuracy of the signal transmitted by the target test channel is improved, and the accuracy of the aircraft power supply system detection is also improved.

[0113] Based on the above embodiment, this embodiment further illustrates and optimizes the technical solution. Specifically, in this embodiment, the target test case file also includes a detection method, and the detection method includes automatic detection; before automatically detecting the power supply system of the aircraft to be detected based on the test steps and obtaining the test data, the method also includes:

[0114] Obtaining a detection mode selection instruction, where the detection mode selection instruction is used to indicate the detection mode of each test step;

[0115] Based on the detection mode selection instruction, determine whether the test step is automatic detection;

[0116] When the detection mode corresponding to the test step is automatic detection, the steps of automatically detecting the power supply system of the aircraft to be detected based on the test step and obtaining the test data are executed.

[0117] In a specific implementation, the target test case file also includes a detection method, which includes automatic detection and manual detection. Before automatically detecting the power supply system of the aircraft to be detected according to the test steps, first determine whether the test step is automatic detection or manual detection according to the detection method in the target test case file. If it is automatic detection, compare and judge the test data collected by the interface driver module according to the test steps and the corresponding qualified criteria. If it is manual detection, the operator performs manual operation according to the test steps.

[0118] It can be seen that the technical solution provided in this embodiment determines whether the test step is automatic detection or manual detection through the detection method in the target test case file, thereby improving the flexibility of aircraft power supply system detection.

[0119] Based on the above embodiment, this embodiment further illustrates and optimizes the technical solution. Specifically, in this embodiment, before obtaining the aircraft power supply system detection instruction, the method further includes:

[0120] Obtain an interface configuration file, where the interface configuration file includes interface configuration information of a power supply system of the aircraft to be detected;

[0121] Based on the interface configuration file, configure the interface of the power supply system of the aircraft to be tested.

[0122] In a specific implementation, before testing the power supply system of the aircraft to be tested, the operator inputs or modifies the interface configuration information through the human-machine interface, and after the main control computer obtains the interface configuration file through the human-machine interface, the interface configuration of the power supply system of the aircraft to be tested is performed according to the interface configuration file. With the help of the interface configuration information, the real-time analysis of the received data / signal and the automatic generation and output of the output data / signal can be dynamically completed, realizing the bus function of the simulated aircraft management system.

[0123] The technical solution provided in this embodiment can realize automatic configuration of the interface and improve the detection efficiency of the aircraft power supply system.

[0124] On the basis of the above-mentioned embodiment, this embodiment further illustrates and optimizes the technical solution. Specifically, in this embodiment, after determining the test result of the power supply system of the aircraft to be tested based on the test data and the qualified criterion, the method further includes:

[0125] Automatically generate test reports based on test data and test results.

[0126] In a specific implementation, after the test result of the power supply system of the aircraft to be tested is determined, a test report is automatically generated according to the test data and the test result.

[0127] As an example, the test report is output in a word format, and the test report includes test data, test results, waveform diagrams and other contents.

[0128] It should be noted that the content included in the test report can be customized according to actual needs, and this application does not limit this.

[0129] The technical solution provided in this embodiment automatically generates a test report through test data and test results, so that users can clearly understand the test process and improve user experience.

[0130] Figure 6 A flowchart of another aircraft power supply system detection method provided in one embodiment of the present application. Figure 6 As shown, based on the above embodiment, this embodiment further illustrates and optimizes the technical solution. Specifically, the method provided in this embodiment includes four stages, namely, detection preparation, system self-check, detection process and detection end;

[0131] In the test preparation stage, the operator makes settings in the human-machine interface, such as setting the interface configuration file;

[0132] During the system self-test phase, the operator inputs a control command, which includes identification information of the aircraft power supply system to be tested and identification information of the target item, etc.; performs a system self-test, including self-test and calibration of the target test channel, etc.;

[0133] In the test process stage, the test case file is read, and the test step is determined to be automatic detection or manual detection according to the detection method in the test case file. When the test step is automatic detection, automatic detection is performed according to the test content and test steps set in the test case file. When all the test steps in the test case file with automatic detection method are executed, the following stage is performed; when the test step is manual detection, the operator enters instructions in the human-computer interaction interface for manual detection, and the operator determines whether the manual detection is completed;

[0134] At the end of the test, the product under test is reset, that is, the power supply system of the aircraft under test is reset; the system is reset; and the test report is obtained.

[0135] In summary, the technical method provided by this application has the following technical effects:

[0136] Comprehensive functions: It can simulate the bus data of the aircraft management system, simulate the output signal of the aircraft power supply system, and detect the various parameters and power supply characteristics of the aircraft electrical equipment and the aircraft power supply system, meeting the needs of comprehensive detection of the aircraft power supply system.

[0137] High precision: It adopts a high-precision data acquisition system, which can monitor various parameters of the aircraft power supply system in real time. It also has self-test, metering and channel calibration functions to ensure the accuracy of the test results.

[0138] Easy operation: By providing a graphical test interface, users can easily import and check the test cases that need to be tested, realize automatic detection, and automatically generate test reports, saving detection time and quickly analyzing test results.

[0139] Strong practicability: This application can be widely used in the detection of power supply systems of various types of aircraft and has high practical value.

[0140] The embodiment of the present application further provides a computer-readable storage medium, which stores a computer program. When the computer program is executed by a processor, the steps in the above-mentioned method embodiments can be implemented.

[0141] If the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the present application implements all or part of the processes in the above-mentioned embodiment method, which can be completed by instructing the relevant hardware through a computer program, and the computer program can be stored in a computer-readable storage medium, and the computer program can implement the steps of the above-mentioned various method embodiments when executed by the processor. Among them, the computer program includes computer program code, and the computer program code can be in source code form, object code form, executable file or some intermediate form. The computer-readable medium may include at least: any entity or device capable of carrying the computer program code to an electronic device, a recording medium, a computer memory, a read-only memory (ROM, Read-Only Memory), a random access memory (RAM, Random Access Memory), an electric carrier signal, a telecommunication signal, and a software distribution medium. For example, a USB flash drive, a mobile hard disk, a disk or an optical disk.

[0142] A computer-readable storage medium provided in an embodiment of the present application has the same beneficial effects as the above-mentioned aircraft power supply system detection method.

[0143] An embodiment of the present application provides a computer program product, which includes a computer program. When the computer program is executed by a processor, the steps in the above-mentioned method embodiments can be implemented.

[0144] A computer program product provided in an embodiment of the present application has the same beneficial effects as the above-mentioned aircraft power supply system detection method.

[0145] In the above embodiments, the description of each embodiment has its own emphasis. For parts that are not described or recorded in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0146] Those of ordinary skill in the art will appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of this application.

[0147] In the embodiments provided in the present application, it should be understood that the disclosed devices / electronic devices and methods can be implemented in other ways. For example, the device / electronic device embodiments described above are merely schematic. For example, the division of the modules or units is only a logical function division. There may be other division methods in actual implementation, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of devices or units, which can be electrical, mechanical or other forms.

[0148] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0149] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present application, and should all be included in the protection scope of the present application.

Claims

1. A method for detecting an aircraft power supply system, characterized in that: Applied to aircraft power supply system detection equipment, the method comprises: Acquire an aircraft power supply system detection instruction, where the aircraft power supply system detection instruction is used to indicate an aircraft power supply system to be detected and a target test item; Based on the aircraft power supply system detection instruction, calling a target test case file, wherein the target test case file includes test steps and qualification criteria corresponding to the target test items; Automatically testing the power supply system of the aircraft to be tested based on the test steps, and acquiring test data, wherein the test data includes the AC voltage, frequency, DC voltage and output current corresponding to the power supply system of the aircraft to be tested in steady state and transient state respectively; Based on the test data and the qualification criteria, a test result of the power supply system of the aircraft to be tested is determined.

2. The method according to claim 1, characterized in that The automatic detection of the power supply system of the aircraft to be detected based on the test steps and obtaining test data includes: Determining the complexity of the target test item based on the target test item and a first preset mapping relationship, wherein the first preset mapping relationship represents a mapping relationship between a test item and the complexity of the test item; Determine target test setting information based on the complexity of the target test item and a second preset mapping relationship, wherein the second preset mapping relationship represents a mapping relationship between the complexity of the test item and the test setting information, wherein the test setting information includes a test speed and a test accuracy; Based on the test steps and the target test setting information, the power supply system of the aircraft to be tested is automatically tested, and the test data is obtained.

3. The method according to claim 1 or 2, characterized in that: The automatic detection of the power supply system of the aircraft to be detected based on the test steps and obtaining test data includes: Based on the test steps, acquiring test step selection information, wherein the test step selection information includes one or more steps in the test steps; Based on the test step selection information, the power supply system of the aircraft to be tested is automatically tested, and the test data is obtained.

4. The method according to claim 1, characterized in that: The target test case file also includes a target test channel; Before automatically testing the power supply system of the aircraft to be tested based on the testing steps and obtaining test data, the method further includes: Inputting an excitation signal to the power supply system of the aircraft to be tested through the target test channel; Acquiring, through the target test channel, a feedback voltage value of the power supply system of the aircraft to be tested based on the excitation signal; Based on the feedback voltage value, a self-test result of the target test channel is determined.

5. The method according to claim 4, characterized in that The target test case file also includes a standard voltage value corresponding to the target test channel; After determining the self-test result of the target test channel based on the feedback voltage value, the method further includes: When the self-test result of the target test channel is passed, the target test channel is calibrated based on the feedback voltage value and the standard voltage value by using the least square method and the Levenberg-Marquardt method.

6. The method according to claim 1, characterized in that The target test case file also includes a detection method, and the detection method includes automatic detection; Before automatically testing the power supply system of the aircraft to be tested based on the testing steps and obtaining test data, the method further includes: Obtaining a detection mode selection instruction, wherein the detection mode selection instruction is used to indicate a detection mode for each of the test steps; Based on the detection mode selection instruction, determining whether the test step is automatic detection; When the detection method corresponding to the test step is automatic detection, the step of automatically detecting the power supply system of the aircraft to be detected based on the test step and acquiring test data is executed.

7. The method according to claim 1, characterized in that Before obtaining the aircraft power supply system detection instruction, the method further includes: Acquire an interface configuration file, wherein the interface configuration file includes interface configuration information of the power supply system of the aircraft to be detected; Based on the interface configuration file, interface configuration is performed on the power supply system of the aircraft to be tested.

8. The method according to claim 1, characterized in that After determining the test result of the power supply system of the aircraft to be tested based on the test data and the qualification criterion, the method further includes: Based on the test data and the test results, a test report is automatically generated.

9. An aircraft power supply system detection device, characterized in that: The device comprises: A main control computer is used to obtain an aircraft power supply system detection instruction, wherein the aircraft power supply system detection instruction is used to indicate the aircraft power supply system to be detected and a target test item; based on the aircraft power supply system detection instruction, call a target test case file, wherein the target test case file includes test steps and qualification criteria corresponding to the target test item; and automatically detect the aircraft power supply system to be detected based on the test steps; A data acquisition device, used to acquire test data, wherein the test data includes the AC voltage, frequency, DC voltage and output current corresponding to the power supply system of the aircraft to be tested in steady state and transient state respectively; The main control computer is also used to determine the test result of the power supply system of the aircraft to be tested based on the test data and the qualification criterion.

10. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the method according to any one of claims 1 to 8 is implemented.

Images