Automatic test system and method for aviation fly-by-wire flight control equipment

Abstract

The invention belongs to the field of automatic testing, and particularly relates to an automatic testing system and method for aviation fly-by-wire flight control equipment, and the system comprises a system self-inspection unit, a system resource unit, a system interface adaption unit, and a system testing control unit. And the system self-checking unit controls the automatic test system to execute a self-checking function through operation software. The test efficiency and the test coverage rate can be remarkably improved, the problem of function test omission can be effectively solved, the fault of the tested airborne avionics equipment is analyzed by adding the YMECA fault analysis module and combining the definition event and the structure function of the fault tree, qualitative analysis is carried out on the fault, a professional basis is provided for fault diagnosis, the maintenance difficulty is reduced, and the test efficiency is improved. The aircraft maintenance guarantee efficiency is improved, and joint test of a plurality of airborne avionics devices and parallel test of a plurality of airborne avionics devices of the same model in a fly-by-wire flight control system of a certain type of fighter can be realized.

Description

Technical Field

[0001] This application belongs to the field of automated testing, and specifically relates to an automatic testing system and method for aviation fly-by-wire flight control equipment. Background Technology

[0002] Automated testing systems in engineering are often designed for specific application areas and test objects, and are often named after the application object. Therefore, depending on the application area and test object, there are automatic testing systems for aircraft, automatic testing systems for radar, etc.

[0003] Each automated test system comprises hardware and software components. The hardware component includes at least one central processing unit (CPU) and at least one input / output (I / O) unit, through which the automated test system connects to the avionics equipment under test, computer networks, etc.

[0004] Currently, in base-level fighter jet maintenance depots, the testing methods for automatic testing systems of airborne electronic equipment in the fly-by-wire flight control system may encounter problems such as cumbersome configuration, complex data processing, and numerous wiring changes. Complex automatic testing systems generally require individual testing of multiple test items, and complex testing procedures require operators of the automatic testing system to perform a series of test operations. Complex operating procedures may lead to repeated testing of the same function or missed functional tests.

[0005] Existing automated testing systems generally only provide anomaly detection results, and depending on the maintenance capabilities of the airborne equipment, they can only replace faulty LRUs (Line Replaceable Units) and SRUs (Shop Replaceable Units), lacking qualitative analysis tools.

[0006] Existing automatic testing systems for airborne electronic equipment in fly-by-wire flight control systems typically can only test one type of airborne electronic equipment, resulting in low testing efficiency. Therefore, how to improve automation, shorten testing time, and increase testing efficiency by conducting joint and parallel testing of multiple airborne electronic equipment and by combining hardware and software is an urgent problem to be solved. Summary of the Invention

[0007] The purpose of this application is to provide an automatic testing system and method for aviation fly-by-wire flight control equipment, in order to solve the problem of low testing efficiency in existing automatic testing systems.

[0008] The technical solution of this application is: an automatic testing method for aviation fly-by-wire flight control equipment, comprising:

[0009] Connect multiple airborne avionics devices under test to the various matrix interfaces of the automatic test system, and turn on the corresponding matrix interfaces;

[0010] The human-machine interaction module and the test control module collect data from each matrix interface. The system test control unit calls the data collected by the human-machine interaction module and the test control module to identify the airborne avionics equipment under test corresponding to each matrix interface and obtain the status information of the airborne avionics equipment under test.

[0011] The human-computer interaction module is connected to the user terminal and the test control module. The system test control unit sends the status information of the airborne avionics equipment under test to the user terminal through the human-computer interaction module. Then, the user selects the test items to be tested as needed, and then returns the selected test data to the test control module through the human-computer interaction module.

[0012] The system test control unit controls the signal resource management module to call the signal resources in the system resource unit, store them in the signal resource management module, and send them to the test control module; then, the signal resources and test data of the test control module are matched to obtain the priority order of the device under test, and the test is performed according to the priority order of the device under test;

[0013] Call signal resources and test each device under test in sequence according to priority, and collect test data from each device until all test programs are completed;

[0014] After all the test items for all the devices under test are completed, the test data are analyzed by the YMECA fault analysis module to obtain fault diagnosis results.

[0015] After all test procedures are completed, the results management display module will provide and print the test results and fault diagnosis results.

[0016] Preferably, the system test control unit calls the signal resources of the signal resource management module according to the signal matching settings of the human-machine interaction module, runs the software program according to the results in the test control module matching the test items, tests the test items of the device under test according to the priority order, and collects test data. When the test items of the device under test with high priority are completed, a reset operation is performed to release the signal resources. The signal resource management module re-matches the signal requirements according to the priority order, and repeats the above operation until all test programs are completed.

[0017] Preferably, the system interface adapter unit of the device under test is connected to the automatic test system. The interface adapter unit is equipped with multiple matrix interfaces, each device under test corresponds to one matrix interface, and the system interface adapter unit corresponding to each test airborne avionics device has a fixed priority matrix interface.

[0018] Preferably, the system resource unit includes excitation signal resources, measurement signal resources, bus signal resources, and switch signal resources, and each of the excitation signal resources, measurement signal resources, bus signal resources, and switch signal resources can be adapted to different models of the device under test.

[0019] Preferably, the YMECA fault analysis module is equipped with test standard values ​​for different models of the tested equipment. After the test data of the corresponding tested equipment is collected, the test standard value is compared with the test data. If the test data exceeds the corresponding test standard value, a fault is determined and the corresponding fault data is recorded. After all the test data is compared, the fault analysis of the tested airborne avionics equipment that has a fault is performed to obtain the fault diagnosis result.

[0020] Preferably, the process by which the YMECA fault analysis module performs fault analysis on the tested airborne avionics equipment that has malfunctioned to obtain fault diagnosis results includes:

[0021] Based on fuzzy hierarchical analysis, the fault problems of the tested airborne avionics equipment are classified into layers, including the equipment fault severity layer, the influencing factor layer and the fault mode layer. The influencing factor layer includes fault probability, severity, detection difficulty and maintenance difficulty. The influencing factors in the influencing factor layer are classified into levels to obtain the evaluation level matrix.

[0022] The fault tree is used to decompose the faults of the airborne avionics equipment under test and determine the fault modes that cause the faults of the airborne avionics equipment under test.

[0023] Calculate the overall hazard level of each fault mode for the fault of the tested airborne avionics equipment, determine the fault mode most likely to cause the fault of the tested airborne avionics equipment based on the overall hazard level, and obtain the fault diagnosis result.

[0024] Preferably, the process of calculating the comprehensive hazard level of each fault mode for the fault of the tested airborne avionics equipment, determining the fault mode most likely to cause the fault of the tested airborne avionics equipment based on the comprehensive hazard level, and obtaining the fault diagnosis result includes:

[0025] For each failure mode, the influencing factors are compared pairwise to obtain the influencing factor judgment matrix, and the weight matrix is ​​obtained based on the influencing factor judgment matrix.

[0026] Obtain the fuzzy evaluation matrix for each fault mode, and then obtain the fuzzy evaluation matrix for the fault mode based on the fuzzy evaluation matrix and the weight matrix.

[0027] The comprehensive hazard level of each fault mode is obtained based on the fuzzy evaluation matrix and evaluation level matrix of each fault mode. The fault modes are sorted according to the value of the comprehensive hazard level. The larger the value of the comprehensive hazard level, the more likely the corresponding fault mode is to cause failure of avionics equipment.

[0028] On the other hand, this application provides an automatic testing system for airborne fly-by-wire flight control equipment, including a system self-test unit, a system resource unit, a system interface adapter unit, and a system test control unit. The system self-test unit controls the automatic testing system to perform self-test functions through operating software. The system resource unit is used to provide various excitation signals required by the airborne avionics equipment under test and to complete the on / off switching of all signal channels. The system interface adapter unit is used to connect the interfaces of each device under test. The system test control unit is used to perform testing and data acquisition of each device under test.

[0029] Preferably, the system test control unit includes a signal resource management module, a human-computer interaction module, a test control module, a YMECA fault analysis module, and a result management and display module;

[0030] The signal resource management module provides a matching algorithm for the airborne avionics equipment under test to meet the power supply requirements of the equipment under test and the loading, data processing and matching requirements of the signals under test.

[0031] The human-computer interaction module has a human-computer interaction interface for realizing human-computer interaction functions;

[0032] The test control module has a signal conditioning circuit and a signal isolation circuit, which are used to complete the testing of various functions of the device under test;

[0033] The YMECA fault analysis module performs fault analysis based on the collected test data to obtain the test structure;

[0034] The results management and display module is used to manage and display the fault analysis results.

[0035] The automated testing system and method for airborne fly-by-wire flight control equipment disclosed in this application can significantly improve testing efficiency and coverage, effectively addressing the problem of missed functional tests. Through the YMECA fault analysis module, combined with fault tree definition events and structure functions, it analyzes the faults of the airborne avionics equipment under test, performs qualitative analysis of the faults, provides professional basis for fault diagnosis, reduces maintenance difficulty, and improves aircraft maintenance efficiency. It can realize the joint testing of multiple airborne avionics equipment in the aircraft fly-by-wire flight control system and the parallel testing of multiple airborne avionics equipment of the same model. Furthermore, by combining hardware and software, it improves the degree of automation, shortens testing time, increases testing efficiency, and effectively solves the problem of missed functional tests. Attached Figure Description

[0036] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0037] Figure 1 This is a schematic diagram of an automatic testing system for aero-fly-by-wire flight control equipment according to an embodiment of this application.

[0038] Figure 2 This is a schematic diagram of the automatic testing method for aero-fly-by-wire flight control equipment according to an embodiment of this application.

[0039] Figure 3 This is a schematic diagram illustrating the fault layering of integrated aviation signal lights according to an embodiment of this application.

[0040] Figure 4 This is a schematic diagram of a fault tree model for the failure of integrated aviation signal lights in an embodiment of this application.

[0041] Figure label:

[0042] 1-System self-test unit;

[0043] 2-System resource unit;

[0044] 21-Excitation signal resources;

[0045] 22-Measurement signal resources;

[0046] 23-Bus signal resources;

[0047] 24-Switch signal resources;

[0048] 3-System Interface Adaptor Unit;

[0049] 31-Matrix Interface;

[0050] 32 - Adapter and test cable;

[0051] 4-System test and control unit;

[0052] 41-Signal Resource Management Module;

[0053] 42-Human-computer interaction module;

[0054] 43-Test Control Module;

[0055] 44-YMECA Fault Analysis Module;

[0056] 45 - Results Management and Display Module. Detailed Implementation

[0057] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0058] like Figure 1 The image shows an automatic test system for aerospace fly-by-wire flight control equipment provided in this application. The automatic test system includes a system self-test unit 1, a system resource unit 2, a system interface adaptation unit 3, and a system test control unit 4.

[0059] The system self-test unit 1 is used to control the automatic test system to perform self-test functions through operating software, so as to avoid damage to the airborne avionics equipment under test or the automatic test system during subsequent testing.

[0060] System resource unit 2 is used to provide various excitation signals required by the airborne avionics equipment under test, and to complete the on / off switching of all signal channels. System resource unit 2 includes excitation signal resource 21, measurement signal resource 22, bus signal resource 23, and switch signal resource 24.

[0061] The system interface adapter unit 3 is used to connect the interfaces of various airborne avionics devices under test. The system interface adapter unit 3 includes an interface matrix 31, an adapter, and a test cable 32.

[0062] The system test control unit 4 is used for testing and data acquisition of various airborne avionics devices under test. The system test control unit 4 includes a signal resource management module 41, a human-machine interface module 42, a test control module 43, a YMECA fault analysis module 44, and a result management and display module 45. The signal resource management module 41 provides matching algorithms for the airborne avionics devices under test to meet their power supply requirements and the loading, data processing, and matching requirements of the tested signals. The human-machine interface module 42 has human-machine interaction functions and a user interface for comprehensive configuration of test data information. The test control module 43 is used to complete the testing of various functions of the airborne avionics devices under test and includes signal conditioning circuits and signal isolation circuits. The YMECA fault analysis module 44 performs fault analysis based on the acquired data. The result management and display module 45 manages and displays the fault analysis results. The tested functions include relevant functions in the fly-by-wire flight control system, and provide management functions during the test process, including starting the test software program, scheduling excitation signals and test signals, and debugging the automatic test system; the result management display module 45 is used to display the system's own status information, the test results and fault diagnosis results of the tested airborne avionics equipment, and the YMECA fault analysis module 44 performs fault analysis based on the fault tree of Failure Mode, Effects and Criticality Analysis (FMECA).

[0063] Among them, the signal isolation circuit and the signal conditioning circuit are used to isolate the signal between the test object and the automatic test system, and to perform voltage conversion according to the relevant parameters of the airborne avionics equipment under test and the automatic test system.

[0064] The system interface adapter unit 3 contains adapters, which are categorized according to the model of the airborne avionics equipment under test. Connecting an adapter is determined by its identification resistor. Different airborne avionics equipment under test are equipped with different models of adapters and test cables 32. The connection status and model information of the airborne avionics equipment under test are determined based on the identification resistors of the adapters and test cables 32. The system interface adapter unit 3 is equipped with multiple matrix interfaces 31, with one matrix interface 31 corresponding to each device under test. The on / off state and switching of the matrix interfaces 31 are controlled by the operating software. Without manual configuration, the system interface adapter unit 3 has a fixed priority matrix interface 31.

[0065] like Figure 2 The automatic testing method for fly-by-wire flight control equipment provided in this embodiment of the application, based on the above system, includes the following steps:

[0066] Step S100: Connect the airborne avionics equipment under test.

[0067] Connect multiple airborne avionics devices under test to the respective matrix interfaces 31 of the automatic test system, and turn on the corresponding matrix interfaces 31.

[0068] Preferably, the system interface adapter unit 3 of the automatic test system is used to connect the airborne avionics device under test to the system interface adapter unit 3 to ensure the correct connection of the adapter and the test cable 32. The system interface adapter unit 3 is equipped with multiple matrix interfaces 31, with one matrix interface 31 corresponding to each airborne avionics device under test. The on / off state and switching of the matrix interfaces 31 are controlled by the operating software and obtained through the operating software.

[0069] Without manual configuration, each system interface adapter unit 3 corresponding to the tested airborne avionics equipment has a fixed priority matrix interface 31.

[0070] Step S200, Identify information:

[0071] The human-machine interaction module 42 and the test control module 43 collect data from each matrix interface 31. The system test control unit 4 calls the data collected by the human-machine interaction module 42 and the test control module 43 to identify the airborne avionics equipment under test corresponding to each matrix interface 31 and obtain the status information of the airborne avionics equipment under test.

[0072] If the fixed priority matrix interface 31 is not used, it can be manually configured through the human-computer interaction module 42.

[0073] Step S300, determine the test items:

[0074] The human-machine interaction module 42 is connected to the user terminal and the test control module 43. The system test control unit 4 sends the status information of the airborne avionics equipment under test to the user terminal through the human-machine interaction module 42. Then, the user selects the test items to be tested as needed, and then returns the selected test item data to the test control module 43 through the human-machine interaction module 42.

[0075] Step S400, Signal Matching:

[0076] The system test control unit 4 controls the signal resource management module 41 to call the signal resources in the system resource unit 2, store them in the signal resource management module 41, and send them to the test control module 43; then the signal resources of the test control module 43 are matched with the test item data to obtain the priority order of the airborne avionics equipment under test, and then the test is carried out according to the priority order of the airborne avionics equipment under test.

[0077] Preferably, the system resource unit 2 includes excitation signal resource 21, measurement signal resource 22, bus signal resource 23 and switch signal resource 24, and each of the excitation signal resource 21, measurement signal resource 22, bus signal resource 23 and switch signal resource 24 can be adapted to different models of the airborne avionics equipment under test.

[0078] Step S500, One-click test:

[0079] The system invokes signal resources and tests each airborne avionics device under test in sequence according to priority, and collects test data for each airborne avionics device under test until all test procedures are completed.

[0080] The system test control unit 4 calls the signal resources of the signal resource management module 41 according to the signal matching settings of the previous human-machine interaction module 42, runs the software program according to the results in the test control module 43 matching the test items, and tests the airborne avionics equipment under test and the test items according to the priority order, and collects test data. When the test item of the airborne avionics equipment under test with high priority is completed, a reset operation is performed to release the signal resources. The signal resource management module 41 rematches the signal requirements according to the priority, and repeats the above operation until all test programs are completed.

[0081] With the above design, all test items can be completed without human intervention during the testing process, thus achieving one-click testing.

[0082] Step S600, Fault Analysis:

[0083] After all the test items of the tested airborne avionics equipment are completed, the test data are analyzed by the YMECA fault analysis module 44 to obtain the fault diagnosis results.

[0084] Preferably, the YMECA fault analysis module 44 is equipped with test standard values ​​for different models of airborne avionics devices under test. After the test data of the corresponding airborne avionics device under test is collected, the test standard value is compared with the test data. If the test data exceeds the corresponding test standard value, a fault is determined and the corresponding fault data is recorded. After all the test data is compared, the fault analysis is performed on the airborne avionics device under test that has a fault to obtain the fault diagnosis result.

[0085] FMECA analysis belongs to equipment FMECA (Failure Mode, Effects and Criticality Analysis). It combines the definition of fault tree events and structure functions to analyze the actual faults that occur during product use, analyze the causes, effects and hazards of the faults, and provide a basis for testing, maintenance and fault diagnosis.

[0086] The YMECA fault analysis module 44 in this application diagnoses faults in the tested airborne avionics equipment based on fuzzy hierarchical analysis, thereby obtaining fault diagnosis results. The analysis process of the YMECA fault analysis module 44 is as follows:

[0087] Step S610: Based on fuzzy hierarchical analysis, the fault problems of the airborne avionics equipment under test are divided into layers. The layers include the equipment fault severity layer, the influencing factor layer, and the fault mode layer. The influencing factor layer includes fault probability, severity, detection difficulty, and maintenance difficulty. The influencing factors in the influencing factor layer are classified into levels to obtain the evaluation level matrix V.

[0088] like Figure 3 As shown, this embodiment takes the analysis of aviation integrated signal light failure based on fuzzy hierarchical analysis and fault tree as an example. The aviation integrated signal light failure constitutes the top layer of equipment failure severity level, the failure probability level, severity level, detection difficulty level and maintenance difficulty level constitute the middle layer of influencing factors, and the various failure modes that cause the aviation integrated signal light failure constitute the bottom layer of failure mode.

[0089] The evaluation level matrix V is obtained by classifying each influencing factor in the influencing factor layer into four levels, namely V = {1, 2, 3, 4}. Table 1 shows the four-level classification of each influencing factor in this embodiment.

[0090] Table 1

[0091]

[0092] S620 decomposes the faults of the outgoing lines of the airborne avionics equipment under test based on the fault tree and determines the fault modes that cause the faults of the airborne avionics equipment under test.

[0093] like Figure 4 The diagram shows the fault tree model for the failure of integrated aviation signal lights in this embodiment. According to this model, the top-level integrated aviation signal light function failure event is composed of multiple independent minimum failure events, each of which represents a failure mode. Table 2 shows a schematic table of failure modes corresponding to the minimum failure events of integrated aviation signal lights in this embodiment.

[0094] Table 2

[0095] State variables definition State variables definition Failure Mode 1 LM139 chip failure Failure Mode 6 resistor fault Failure Mode 2 Positive control signal light malfunction Failure Mode 7 Self-test function chip malfunction Failure Mode 3 LM139 chip failure Failure Mode 8 5V power supply has no output Failure Mode 4 Negative control signal light malfunction Failure Mode 9 28V power supply has no output Failure Mode 5 Relay fault

[0096] Step S630: Calculate the overall hazard level of each fault mode for the fault of the tested airborne avionics equipment, determine the fault mode most likely to cause the fault of the tested airborne avionics equipment based on the overall hazard level, and then obtain the fault diagnosis result.

[0097] Specifically, step S630 of this application includes the following steps:

[0098] Step S631: Perform pairwise comparisons of the influencing factors for each failure mode to obtain an influencing factor judgment matrix, and obtain a weight matrix based on the influencing factor judgment matrix.

[0099] This embodiment takes fault mode 1 as an example. Based on the pairwise comparison of four indicators—fault probability, severity, detection difficulty, and maintenance difficulty—for fault mode 1, the influence judgment matrix of fault mode 1 can be obtained. Among them, the influence judgment matrix A 1 Each element a ij (i,j are the number of rows and columns of the matrix) are taken using the 0.1 to 0.9 scale method in Table 3.

[0100] Table 3

[0101] Scale definition illustrate 0.5 Equally important Both factors are equally important. 0.6 Slightly important Between the two factors, one factor is slightly more important than the other. 0.7 Obviously important Between two factors, one factor is significantly more important than the other. 0.8 More important Between two factors, one factor is much more important than the other. 0.9 Extremely important Between two factors, one factor is extremely more important than the other. 0.1,0.2,0.3,0.4 Inverse comparison <![CDATA[If the factor is compared to obtain element a ij , then element a ji = 1 - a ij >

[0102] In this application, the weight matrix

[0103] After obtaining the weight matrix, a consistency test of the compatibility index is required. The test method is as follows:

[0104]

[0105] I(A,W) is the compatibility index of the influence judgment matrix. When the compatibility index I(A,W) ≤ ​​α, the consistency of the influence judgment matrix meets the requirements. The smaller the threshold α, the higher the consistency requirement; typically, the threshold α = 0.1. Let W be the weighted term of the influencing factors of failure mode k. i k Then, the weight matrix of the influencing factors of failure mode k 0 < W i k <1 and satisfies the normalization condition:

[0106] In this embodiment, the weight matrix W after normalization for fault mode 1 can be obtained based on the above formula. 1 = [0.29167, 0.2500, 0.24167, 0.21667], and the compatibility index I(A,W) = 0.0712 ≤ 0.1, thus passing the consistency test.

[0107] S632, obtain the fuzzy evaluation matrix for each fault mode, and obtain the fuzzy evaluation matrix of the fault mode based on the fuzzy evaluation matrix and the weight matrix.

[0108] In this embodiment, the fuzzy set of failure probabilities for failure mode 1 can be obtained by using an expert panel evaluation method. Severity fuzzy set Detection difficulty level of fuzzy sets and fuzzy sets of maintenance difficulty Therefore, the fuzzy evaluation matrix R for fault mode 1 can be obtained. 1 :

[0109]

[0110] The fuzzy evaluation matrix of the fault modes can be obtained by using the formula B = RW.

[0111] In this embodiment, the fuzzy evaluation matrix B for fault mode 1 1 =R 1 W 1 =[0.382504,0.512505,0.532505,0.607506].

[0112] Step S633: Based on the fuzzy evaluation matrix and evaluation level matrix of each fault mode, obtain the comprehensive hazard level of each fault mode, and sort them according to the value of the comprehensive hazard level. The larger the value of the comprehensive hazard level, the more likely the corresponding fault mode is to cause the fault of the tested airborne avionics equipment.

[0113] In this application, the overall hazard level of the failure mode is C = BV. T .

[0114] In this embodiment, the overall hazard level C of fault mode 1 is... 1 =B 1 V T =5.435053. Repeating the above process yields the comprehensive hazard level C for the other eight failure modes. 2 ~C 9 The expression is {5.1964, 5.0235, 4.8582, 4.6.5201, 4.1724, 4.0103, 3.8562, 3.45621}.

[0115] By ranking the comprehensive hazard level C of each failure mode 1 ~C 9The values ​​show that fault mode 1 has the highest overall hazard level, and therefore, fault mode 1 is the most likely fault mode to cause the tested airborne avionics equipment to malfunction. When outputting the fault diagnosis results, the fault modes are sorted from highest to lowest overall hazard level to obtain the final fault diagnosis results.

[0116] Step S700, test complete:

[0117] After all test procedures are completed, the results management display module 45 will display and print the test results and fault diagnosis results.

[0118] The method and system of this application can significantly improve testing efficiency and coverage, effectively solving the problem of missing functional tests. By adding the YMECA fault analysis module 44, combined with the definition of fault tree events and structure functions, the faults of the tested airborne avionics equipment are analyzed, and qualitative analysis of the faults is performed, providing professional basis for fault diagnosis, reducing maintenance difficulty, and improving aircraft maintenance efficiency. It can realize the joint testing of multiple airborne avionics equipment in the fly-by-wire flight control system of a certain type of fighter jet and the parallel testing of multiple airborne avionics equipment of the same model. Furthermore, by combining hardware and software, the degree of automation is improved, the testing time is shortened, the testing efficiency is increased, and the problem of missing functional tests is effectively solved.

[0119] It should be noted that the accompanying drawings of the embodiments disclosed in this application only involve the structures involved in the embodiments disclosed in this application. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of the present invention can be combined with each other.

[0120] In conclusion, the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. An automatic testing method for aviation fly-by-wire flight control equipment, characterized in that, include: Connect multiple airborne avionics devices under test to the various matrix interfaces (31) of the automatic test system, and turn on the corresponding matrix interfaces (31); The human-computer interaction module (42) and the test control module (43) collect data from each matrix interface (31). The system test control unit (4) calls the data collected by the human-computer interaction module (42) and the test control module (43) to identify the airborne avionics equipment under test corresponding to each matrix interface (31) and obtain the status information of the airborne avionics equipment under test. The human-computer interaction module (42) is connected to the user terminal and the test control module (43). The system test control unit (4) sends the status information of the airborne avionics equipment under test to the user terminal through the human-computer interaction module (42), obtains the test items selected by the user, and returns the selected test data to the test control module (43) through the human-computer interaction module (42). The system test control unit (4) controls the signal resource management module (41) to call the signal resources in the system resource unit (2), store them in the signal resource management module (41), and send the signal resources to the test control module (43); then the signal resources and test data of the test control module (43) are matched to obtain the priority order of the airborne avionics equipment under test, and the test is carried out according to the priority order of the airborne avionics equipment under test. The system calls upon signal resources and tests each airborne avionics device under test in sequence according to priority, and collects test data for each airborne avionics device under test until all test procedures are completed. After all the test items of the tested airborne avionics equipment are completed, the test data are analyzed by the YMECA fault analysis module (44) to obtain the fault diagnosis results; After all test items are completed, the results management display module (45) will provide and print the test results and fault diagnosis results.

2. The automatic testing method for aviation fly-by-wire flight control equipment as described in claim 1, characterized in that, The system test control unit (4) calls the signal resources of the signal resource management module (41) according to the signal matching settings of the human-machine interaction module (42), runs the software program according to the results in the test control module (43) matching the test items, tests the test items of the airborne avionics equipment under test according to the priority order, and collects test data. When the test items of the airborne avionics equipment under test with high priority are completed, a reset operation is performed to release the signal resources. The signal resource management module (41) re-matches the signal requirements according to the priority order and repeats the above operation until all test programs are completed.

3. The automatic testing method for aviation fly-by-wire flight control equipment as described in claim 1, characterized in that, The system interface adapter unit (3) connects the airborne avionics equipment under test to the automatic test system. The interface adapter unit (3) has multiple matrix interfaces (31). Each airborne avionics equipment under test corresponds to one matrix interface (31). The system interface adapter unit (3) corresponding to each airborne avionics equipment under test has a fixed priority matrix interface (31).

4. The automatic testing method for aviation fly-by-wire flight control equipment as described in claim 1, characterized in that, The system resource unit (2) includes excitation signal resources (21), measurement signal resources (22), bus signal resources (23) and switch signal resources (24). Each of the excitation signal resources (21), measurement signal resources (22), bus signal resources (23) and switch signal resources (24) can be adapted to different models of the airborne avionics equipment under test.

5. The automatic testing method for aviation fly-by-wire flight control equipment as described in claim 1, characterized in that, The YMECA fault analysis module (44) is equipped with test standard values ​​for different models of airborne avionics devices under test. After collecting the test data of the corresponding airborne avionics device under test, the test standard value is compared with the test data. If the test standard value is exceeded, a fault is determined and the corresponding fault data is recorded. After all the test data is compared, the fault analysis is performed on the airborne avionics device under test that has a fault to obtain the fault diagnosis result.

6. The automatic testing method for aviation fly-by-wire flight control equipment as described in claim 5, characterized in that, The process by which the YMECA fault analysis module (44) performs fault analysis on the tested airborne avionics equipment that has malfunctioned and obtains fault diagnosis results includes: Based on fuzzy hierarchical analysis, the fault problems of the tested airborne avionics equipment are classified into layers, including the equipment fault severity layer, the influencing factor layer and the fault mode layer. The influencing factor layer includes fault probability, severity, detection difficulty and maintenance difficulty. The influencing factors in the influencing factor layer are classified into levels to obtain the evaluation level matrix. The fault tree is used to decompose the faults of the airborne avionics equipment under test and determine the fault modes that cause the faults of the airborne avionics equipment under test. Calculate the overall hazard level of each fault mode for the fault of the tested airborne avionics equipment, determine the fault mode most likely to cause the fault of the tested airborne avionics equipment based on the overall hazard level, and obtain the fault diagnosis result.

7. The automatic testing method for aviation fly-by-wire flight control equipment as described in claim 6, characterized in that, The process of calculating the overall hazard level of each failure mode for the tested airborne avionics equipment failure, determining the most likely failure mode to cause the failure based on the overall hazard level, and obtaining the failure diagnosis result includes: For each failure mode, the influencing factors are compared pairwise to obtain the influencing factor judgment matrix, and the weight matrix is ​​obtained based on the influencing factor judgment matrix. Obtain the fuzzy evaluation matrix for each fault mode, and then obtain the fuzzy evaluation matrix for the fault mode based on the fuzzy evaluation matrix and the weight matrix. The comprehensive hazard level of each fault mode is obtained based on the fuzzy evaluation matrix and evaluation level matrix of each fault mode. The fault modes are sorted according to the value of the comprehensive hazard level. The larger the value of the comprehensive hazard level, the more likely the fault mode is to cause the test airborne avionics equipment to fail.

8. An automatic testing system for aviation fly-by-wire flight control equipment, used to implement the automatic testing method for aviation fly-by-wire flight control equipment as described in any one of claims 1-7, characterized in that, It includes a system self-test unit (1), a system resource unit (2), a system interface adaptation unit (3), and a system test control unit (4); The system self-test unit (1) controls the automatic test system to perform self-test functions through the operating software; The system resource unit (2) is used to provide various excitation signals required by the airborne avionics equipment under test, and to complete the switching and connection of all signal channels; The system interface adapter unit (3) is used to connect the interfaces of each tested airborne avionics device. The system test control unit (4) is used to perform tests and data acquisition on each of the airborne avionics devices under test.

9. The automatic testing system for fly-by-wire flight control equipment as described in claim 8, characterized in that, The system test control unit (4) includes a signal resource management module (41), a human-computer interaction module (42), a test control module (43), a YMECA fault analysis module (44), and a result management and display module (45); The signal resource management module (41) provides a matching algorithm for the airborne avionics equipment under test to meet the power supply requirements of the airborne avionics equipment under test and the loading, data processing and matching requirements of the signal under test. The human-computer interaction module (42) has a human-computer interaction interface for implementing human-computer interaction functions; The test control module (43) has a signal conditioning circuit and a signal isolation circuit, which are used to complete the testing of various functions of the airborne avionics equipment under test; The YMECA fault analysis module (44) performs fault analysis based on the collected test data to obtain test results; The result management and display module (45) is used to manage and display the fault analysis results.

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