A testing method and system for aircraft entertainment display system

Abstract

The present invention relates to the field of aircraft system testing technology, and in particular to a testing method and system for an aircraft entertainment display system. The method comprises: connecting to an aircraft entertainment display system to be monitored; capturing the running code of the aircraft entertainment display system to be monitored when it is powered on; inputting an extraction instruction to obtain multiple groups of test codes from the running code; obtaining the value of each group of test codes through debugging and forming corresponding test instructions; encapsulating the test instructions to form an interactive operation interface; calling at least one standby test instruction through the interactive operation interface; obtaining the test code and value corresponding to the standby test instruction, and transmitting them to the aircraft entertainment display system to be tested for testing; receiving the test results of the standby test instruction and displaying the test results on the interactive operation interface. Utilizing the present invention, an aircraft entertainment display system can be repaired after a fault occurs in an original industrial computer, ensuring safe operation during this period.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft system testing, and in particular to a testing method and system for an aircraft entertainment display system. Background Art

[0002] Under existing technology, when testing an aircraft entertainment and display system (such as one manufactured by Thales), functional testing must be performed using the original manufacturer's industrial control computer and its accompanying automated testing software; otherwise, testing is impossible. However, the original manufacturer's industrial control computer may sometimes malfunction, making it impossible to test the aircraft's entertainment and display system. Furthermore, after a malfunction, the original manufacturer's industrial control computer must be sent back to the manufacturer for repair, which can take months. During this time, the aircraft's entertainment and display system cannot be tested, posing a safety hazard. Therefore, how to repair the aircraft's entertainment and display system even after a malfunction of the original manufacturer's industrial control computer, to ensure its safe operation during this period, is an urgent problem that needs to be addressed. Summary of the Invention

[0003] To solve one of the above-mentioned problems in the prior art, the present invention provides a testing method for an aircraft entertainment display system, comprising: connecting to an aircraft entertainment display system to be monitored; capturing the running code of the aircraft entertainment display system to be monitored when it is turned on; inputting an extraction instruction to obtain multiple groups of test codes from the running code; obtaining the assignment of each group of the test codes through debugging, and forming corresponding test instructions according to the test codes and the assignments of the test codes; encapsulating the test instructions according to their functions to form an interactive operation interface, wherein the interactive operation interface includes at least one calling option, each of the calling options being used to call one or more of the test instructions; connecting to the aircraft entertainment display system to be tested; calling at least one test instruction to be used by interacting with the calling option of the interactive operation interface; obtaining the test code and assignment corresponding to the test instruction to be used, and transmitting them to the aircraft entertainment display system to be tested for testing; receiving the test results of the execution of the test instructions to be used, and displaying the test results on the interactive operation interface.

[0004] Another aspect of the present invention provides a test system for an aircraft entertainment display system, comprising:

[0005] The first interface is used to connect to the aircraft entertainment display system to be monitored;

[0006] A code capture module, used to capture the running code of the aircraft entertainment display system to be monitored when it is turned on;

[0007] A code extraction module, configured to input an extraction instruction to obtain multiple groups of test codes from the running code;

[0008] A test instruction generation module is used to obtain the assignment of each group of test codes through debugging, and form corresponding test instructions according to the test codes and the assignment of the test codes;

[0009] A test instruction encapsulation and interactive operation module, configured to encapsulate the test instructions according to their functions to form an interactive operation interface, wherein the interactive operation interface includes at least one call option, each of which is used to call one or more test instructions;

[0010] The second interface is used to connect to the aircraft entertainment display system under test;

[0011] A calling test module, configured to call at least one test instruction to be used by interacting with the calling option of the interactive operation interface;

[0012] a test code acquisition and value assignment module, configured to acquire the test code and value assignment corresponding to the test instruction to be used, and transmit the acquired test code and value assignment to the aircraft entertainment display system to be tested via the second interface for testing;

[0013] The test result display module is used to receive the test result of the test instruction to be used and display the test result on the interactive operation interface.

[0014] The beneficial effects of the present invention are reflected in the fact that the method and system for testing an aircraft entertainment display system provided by the present invention can directly obtain the underlying code of the aircraft entertainment display system, parse the code into test instructions, encapsulate the test instructions in a visual and interactive operation interface, and use this operation interface to test the aircraft entertainment display system. The method and system for testing an aircraft entertainment display system provided by the present invention can also repair the aircraft entertainment display system even after a failure of the original industrial computer, thereby ensuring the safe operation of the aircraft entertainment display system during this period. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a flow chart of a testing method for an aircraft entertainment display system provided in Example 1 of the present invention;

[0016] Figure 2 This is an example diagram of the underlying running code when the aircraft entertainment display system provided by Example 1 of the present invention is turned on;

[0017] Figure 3 This is an example diagram of the software interface design of the interactive operation interface provided in Example 1 of the present invention;

[0018] Figure 4This is an example diagram of a sub-option interface of the interactive operation interface provided in Example 1 of the present invention;

[0019] Figure 5 This is a flow chart of determining repair reports based on fault levels and new and old levels, as provided in Example 1 of the present invention;

[0020] Figure 6 This is a schematic diagram of the structure of a test system for an aircraft entertainment display system provided in Example 1 of the present invention;

[0021] Figure 7 This is a structural diagram of the repair determination system provided in Example 1 of the present invention. DETAILED DESCRIPTION

[0022] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0023] Example 1

[0024] This embodiment provides a test method for an aircraft entertainment display system. The test method of this embodiment mainly includes a debugging part and a testing part. The debugging part is mainly implemented through steps S101 to S105, and the testing part is mainly implemented through steps S106 to S109. Figure 1 As shown, the test method for the aircraft entertainment display system of this embodiment specifically includes the following steps:

[0025] Step S101: Connecting to the aircraft entertainment display system to be monitored. Specifically, during the debugging phase, a functioning aircraft entertainment display system can be used as the aircraft entertainment display system to be monitored, so as to obtain a complete data stream and, therefore, the correct operating code. In a specific implementation, the aircraft entertainment display system to be monitored can be connected via a serial bus. For example, universal RS232 serial port software can be installed on the test user's computer port. The test user then uses an RS232 serial cable and a network cable to connect the aircraft entertainment display system (hereinafter referred to as the display) to the test user's computer.

[0026] Step S102, capturing the running code of the aircraft entertainment display system to be monitored when it is turned on; specifically, the aircraft entertainment display system to be monitored is turned on and the test user computer reads the underlying running code of the aircraft entertainment display system when it is turned on through the RS232 serial port line. Figure 2The figure shows an example of the underlying running code when the aircraft entertainment display system is turned on. In an optional embodiment, step S102 can be specifically implemented by the following steps:

[0027] Step 1021, using the serial bus to obtain the data stream of the aircraft entertainment display system to be monitored when it is turned on; specifically, a serial debugging tool can be used to intercept the data, and when intercepting the data, it may also be necessary to perform timing synchronization and other processing on the data to ensure the accuracy of the data.

[0028] Step 1022: Parse the data stream to obtain the execution code. Specifically, the captured data stream may be binary or encoded and needs to be parsed into a readable format. Reverse engineering may also be required to analyze the protocol structure (e.g., including message headers, checksums, data fields, etc.). For example, deep packet parsing algorithms and CRC checksums can be used to reverse-engineer the data stream to obtain the execution code. Parsing the data stream ensures the accuracy of the obtained execution code.

[0029] In step S103, an extraction command is input to retrieve multiple sets of test code from the running code. Specifically, the extraction command is used to identify and extract test code from the numerous running codes. For example, for the Thales aircraft entertainment display system, the extraction command can be the atp_svdu4 command. atp_svdu4 is a low-level debugging command used to enter the engineering test mode of the THALES aircraft entertainment display system. After inputting this command, the system will return multiple sets of test code (such as test code for touch screen testing and image testing).

[0030] In a specific implementation example, you can enter the extraction instruction statement root@android: / # atp_svdu4_ in the running code page. This instruction is used to obtain the test code of the aircraft entertainment display system. The obtained part of the test code can be shown as follows:

[0031] rooteandroid: / # atp_svdu4_

[0032] atp_svdu4_atpusb_test.sh

[0033] atp_svdu4_audio_io_test.sh

[0034] atp_svdu4_audio_setup.sh

[0035] atp_svdu4_audiocontrol.sh

[0036] atp_svdu4_audioplayer.sh

[0037] atp_svdu4_button_test.sh

[0038] atp_svdu4_ccr_test.sh

[0039] atp_svdu4_disableidle_scrn.sh

[0040] atp_svdu4_display_hone_scrn.sh

[0041] atp_svdu4_eth_txrx_test.sh

[0042] atp_svdu4_ext_video_test.sh

[0043] atp_svdu4_ext_video_test2.sh

[0044] atp_svdu4_getpartnum.sh

[0045] atp_svdu4_hdmipip_test.sh

[0046] atp_svdu4_hdmipip_test2.sh

[0047] Step S104: The values ​​assigned to each set of test code are obtained through debugging, and corresponding test instructions are generated based on the test code and its values. Specifically, after obtaining the test code, the code parameter assignment rules need to be determined through debugging to ultimately form a complete set of test instructions. Only after the test code is correctly assigned can a complete test instruction set be generated.

[0048] In step S105, the test instructions are packaged according to their functions to form an interactive interface. The interactive interface includes at least one call option, each of which is used to call one or more test instructions. Specifically, the test instructions are packaged according to their functional classification (e.g., image test, audio test, etc.), resulting in a corresponding visual, interactive test interface. The interactive interface can be implemented as a visual, interactive software product. The interactive interface can integrate multiple test options, and testing can be completed by interacting with these test options. For example, the interactive interface can include a "Touch Screen Test" option. When this option is selected, the corresponding test instruction is called, and the code contained in the instruction is then transmitted via a serial port to the aircraft's entertainment and display system, thereby testing the aircraft's entertainment and display system.

[0049] In an optional embodiment, the call option further includes: a call sub-option, wherein the call sub-option is used to call a test instruction. By setting the sub-options, the test of the aircraft entertainment display system can be completed in a more refined manner.

[0050] In a specific embodiment, the interactive operation interface can be as follows Figure 3 、 4 shown. Figure 3 The software interface is designed to be an interactive operation interface, which can include various test options for the THALES aircraft entertainment display system to be implemented in this embodiment. Figure 4 This is an example of a sub-option interface. Figure 4 The sub-option interface under the "memory card test" call option is shown. The operation interface and operation program of the present invention can be designed based on C++ language, which is convenient for users to operate.

[0051] It should be noted that Figure 3 and Figure 4 The interactive operation interface displayed is only an example of the present invention, so as to better understand the present invention, but the present invention is not limited thereto, as long as the interactive operation interface of the present invention can be implemented.

[0052] Through the above steps S101 to S105, a visual interactive operation interface for testing is constructed, which can be used to test the corresponding system in the future. After debugging is completed and the interactive operation interface is constructed, the interactive operation interface can be used to test the specific aircraft entertainment display system that needs to be tested.

[0053] Step S106 , connecting the aircraft entertainment display system to be tested; specifically, a system that has failed or is not operating smoothly may be selected as the aircraft entertainment display system to be tested.

[0054] In a specific embodiment, the test user can use an RS232 serial cable and a network cable to connect the computer to the aircraft entertainment display system to be tested, start the software and log in to the software main interface (such as Figure 3 The software's main interface allows you to confirm and enter basic information about the aircraft entertainment display system to be tested for subsequent use. It also allows you to check whether the RS232 port and network port IP address have been automatically identified by the software.

[0055] Step S107 involves interacting with the call options on the interactive operation interface to call at least one test instruction to be used. Specifically, a test function (call option) can be clicked on the interactive operation interface to call the desired test instruction from the aforementioned packaged test instruction set. The interactive operation interface can automatically complete all test options one by one, or it can execute test options based on user input.

[0056] In one optional embodiment, invoking at least one test command in use by interacting with a call option on the interactive operation interface specifically includes: selecting a call sub-option by interacting with the call option on the interactive operation interface; and invoking a test command in use based on the selected call sub-option. By setting sub-options to conduct tests, more refined testing of the aircraft entertainment display system can be achieved.

[0057] In a specific embodiment, the test can be started after preparation in step S106. According to the system settings or the test user's input, the test items are selected one by one, or the secondary test interface (such as Figure 4 The secondary test interface displays the sub-test items of the current test item. Upon receiving a test start input (e.g., a system-defined start command or a click on a corresponding test option button), the automatic test begins.

[0058] Step S108, obtaining the test code and value corresponding to the test instruction to be used, and transmitting them to the aircraft entertainment display system to be tested for testing; specifically, after the test instruction to be used is determined, the test code and value corresponding to the test instruction are automatically input to the entertainment display system to be tested through the serial port to start the test.

[0059] Step S109: Receive the test result of the test command to be used and display the test result on the interactive operation interface. Specifically, after the aircraft entertainment display system has completely executed the test code, it transmits the test result (which can be a specific test result, such as the number of pixel errors, etc.; or a result representing whether the test is passed, such as "pass") back to the computer port of the test user through the serial port. The specific test result will be displayed on the computer interface. Figure 4 The status display is displayed in real time in the "Status Display" column, or the "pass" is displayed through the interactive operation interface. In addition, after completing all test items according to the above steps, the software can also automatically generate a test report for the test user to print.

[0060] The test method for an aircraft entertainment display system provided in this embodiment directly accesses the underlying code of the aircraft entertainment display system, parses the code into test instructions, and encapsulates the test instructions in a visual, interactive user interface. This user interface is then used to test the aircraft entertainment display system. This test method for an aircraft entertainment display system in this embodiment enables the aircraft entertainment display system to be repaired even after a malfunction of the original industrial computer, ensuring the safe operation of the aircraft entertainment display system during this period.

[0061] In addition, since the entertainment display system being tested is installed on an aircraft, and the service time of the aircraft is usually dozens or hundreds of years, some aircraft entertainment display systems may be old products, and it may be difficult to find replacement parts for the components of the aircraft entertainment display system, resulting in the dilemma of not being able to report for repair even if a failure occurs. Therefore, after detecting that the aircraft entertainment display system has a failure, it is also necessary to make a comprehensive judgment based on the above actual situation whether the aircraft entertainment display system needs to be repaired. Therefore, in an optional embodiment, the test method for the aircraft entertainment display system of this embodiment also includes the following steps for judging whether to report for repair based on the fault level and the new and old levels, such as Figure 5 As shown:

[0062] Step S110, establishing an impact factor weight table, wherein the impact factors include a first impact factor and a second impact factor, the first impact factor being the fault level, and the second impact factor being the old and new level. The impact factor weight table includes weight values ​​corresponding to different impact factor levels. Specifically, both the fault level and the old and new level will affect the decision on whether the aircraft entertainment display system needs to be repaired, so both are used as impact factors for calculation to comprehensively consider whether the aircraft entertainment display system needs to be repaired.

[0063] In a specific embodiment, the fault level can be set to 4 levels, with levels 1 to 4 representing: irreversible fault, serious fault, moderate fault, and minor fault, respectively. Weight values ​​can be assigned to fault levels 1 to 4, for example, the weight values ​​can be 100, 10, 5, and 1, respectively. Among them, the weight value of irreversible fault is set to be particularly high, which can ensure that once an irreversible fault occurs, it can be reported for repair regardless of the impact of the newness. The newness level is set to 4 levels, with levels 1 to 4 representing: very new, semi-new, relatively old, and very old, respectively. Weight values ​​can be assigned to fault levels 1 to 4, for example, the weight values ​​can be 20, 10, 5, and 1, respectively.

[0064] Step S111 , determining the fault level corresponding to the aircraft entertainment display system under test based on the test results and the fault judgment threshold table, and determining the weight value of the first influencing factor based on the fault level and influencing factor weight table; specifically, the fault level can be determined by comparing the test results.

[0065] In one optional embodiment, a fault determination threshold table includes thresholds corresponding to each fault level. Determining the fault level of the aircraft entertainment display system under test based on the test results and the fault determination threshold table specifically includes comparing the test results with the thresholds corresponding to each fault level, and determining the fault level corresponding to the test results based on the comparison results. Specifically, the test results may include detailed fault information. For example, in the case of a touch screen test, the test results may include the error status of specific pixels (e.g., the number of pixels with errors). The fault determination threshold table is configured for each test. For example, in the case of a touch screen test, the table may include thresholds for the number of pixel errors corresponding to different fault levels. For example, fewer than 10 pixels (or 0.1% of pixels) with errors may be considered a minor fault; more than 2,000 pixels (or 20% of pixels) with errors may be considered an irreversible fault. Furthermore, the distribution and concentration of the error pixels may be considered when comprehensively determining the fault level.

[0066] Step S112 , determining the model and service life of the aircraft entertainment display system to be tested; specifically, the model and service life of the aircraft entertainment display system to be tested may be obtained based on the aforementioned basic information of the aircraft entertainment display system to be tested.

[0067] Step S113 , determining the age level of the aircraft entertainment display system under test based on the model and service life of the aircraft entertainment display system under test, and determining the weight value of the second influencing factor based on the age level and the influencing factor weight table; specifically, by comprehensively considering the model and service life of the aircraft entertainment display system under test, the age level of the aircraft entertainment display system under test can be more reasonably evaluated.

[0068] In step S114, a determination is made as to whether the aircraft entertainment display system under test requires repair based on the weighted values ​​of the first and second influencing factors. Specifically, based on the aforementioned weighted values, the weighted values ​​of the first and second influencing factors may be added or multiplied together, and the result of this addition or multiplication may be compared with a preset repair threshold. If the preset repair threshold is reached, repair processing is indicated.

[0069] Based on the above steps, during automated testing, the fault level is first determined based on the test results returned. The aircraft's age (model, age, etc.) is then used to determine whether the test passed and whether repairs are necessary. Minor faults in older systems may not require a repair report. Irreversible faults, regardless of age, require a repair report.

[0070] Let's take a specific test example to illustrate: when testing the touch screen, the repair threshold is set to 10, and the weight value of the first influencing factor and the weight value of the second influencing factor are processed by multiplication. If the test result returned is: 10 pixels are displayed incorrectly, and the pixel positions of these 10 pixels are relatively far apart, then the fault level will be marked as level 4. If the aircraft model is very old at this time, the weight values ​​of the fault level and the new and old levels are both 1. At this time, the result of the comprehensive calculation of the first influencing factor and the second influencing factor is 1, which does not meet the preset repair threshold of 10, so the test result is fed back as passed. The reason for this judgment is that some aircraft models are very old and may not have replaceable parts, or the replacement cost of replaceable parts is very high. Therefore, even if some errors are detected, but these errors do not affect the overall availability, no repair processing will be performed. If the fault level is marked as Level 4, but the aircraft is very new, the fault level weight is 1, but the weight of the oldness level is 20. At this time, the result of the comprehensive calculation of the first and second impact factors is 20, which has reached the preset repair threshold of 10. In this case, the test fails and a repair is required. However, if the fault level is Level 1, the fault level weight is 100. Regardless of the condition of the aircraft, the result of the comprehensive calculation of the first and second impact factors exceeds the preset repair threshold of 10. Therefore, the test fails and a repair is required.

[0071] This embodiment also provides a test system 20 for an aircraft entertainment display system, which is used to execute the aforementioned test method for an aircraft entertainment display system. The contents already explained in detail in the aforementioned test method will not be repeated here. Please refer to the description in the aforementioned test method. Figure 6 As shown, the test system 20 includes:

[0072] First interface 201 is used to connect to the aircraft entertainment and display system to be monitored. Specifically, first interface 201 and subsequent second interface 206 can be the same serial bus interface or different serial bus interfaces. For example, universal RS232 serial port software can be installed on the test user's computer port, and the test user can connect the aircraft entertainment and display system to the test user's computer using an RS232 serial port cable and an Ethernet cable.

[0073] The code capture module 202 is used to capture the running code of the aircraft entertainment display system to be monitored when it is turned on. Specifically, the aircraft entertainment display system to be monitored is turned on and the test user computer reads the underlying running code of the aircraft entertainment display system when it is turned on through the RS232 serial port line.

[0074] In an optional embodiment, the code capture module 202 captures the running code of the aircraft entertainment display system to be monitored during startup, specifically including: receiving a data stream of the aircraft entertainment display system to be monitored, obtained via a serial bus; and parsing the data stream to obtain the running code. Specifically, data can be intercepted using a serial debugging tool via the serial bus of the first interface 201. During data interception, the data may need to be processed, such as by timing synchronization, to ensure data accuracy. The captured data stream may be binary or encoded, requiring parsing into a readable format. Reverse engineering may also be required to analyze the protocol structure (e.g., including message headers, checksums, data fields, etc.). For example, a deep packet parsing algorithm and CRC checksums can be used to reversely parse the data stream to obtain the running code. Parsing the data stream ensures the accuracy of the acquired running code.

[0075] The code extraction module 203 is used to input an extraction instruction to retrieve multiple sets of test code from the running code. Specifically, the extraction instruction is used to identify and extract test code from the numerous running codes. For example, for the Thales aircraft entertainment display system, the extraction instruction can be the atp_svdu4 instruction. atp_svdu4 is a low-level debugging instruction used to enter the engineering test mode of the THALES aircraft entertainment display system. After inputting this instruction, the system will return multiple sets of test code (such as test code for touch screen testing and image testing).

[0076] The test instruction generation module 204 is used to obtain the assignments for each set of test code through debugging, and then generate corresponding test instructions based on the test code and its assignments. Specifically, after obtaining the test code, it is necessary to determine the assignment rules for the code parameters through debugging to ultimately generate a complete set of test instructions. Only after the test code is correctly assigned can a complete test instruction set be generated.

[0077] The test instruction encapsulation and interactive operation module 205 is configured to encapsulate test instructions according to their functions, forming an interactive operation interface. The interactive operation interface includes at least one call option, each of which is used to call one or more test instructions. Specifically, each test instruction is encapsulated according to its functional classification (e.g., image test, audio test, etc.), resulting in a corresponding visual, interactive test interface. The interactive operation interface can be implemented as a visual, interactive software product. The interactive operation interface can integrate multiple test options, and testing can be completed by interacting with these test options. For example, the interactive operation interface can include a "Touch Screen Test" option. Selecting this option invokes the corresponding test instruction, and the code contained in the instruction is then transmitted via a serial port to the aircraft's entertainment and display system, thereby testing the aircraft's entertainment and display system.

[0078] In an optional embodiment, the call option further includes: a call sub-option, wherein the call sub-option is used to call a test instruction. By setting the sub-options, the test of the aircraft entertainment display system can be completed in a more refined manner.

[0079] The second interface 206 is used to connect to the aircraft entertainment display system to be tested. Specifically, a system that has a fault or is not running smoothly can be selected as the aircraft entertainment display system to be tested.

[0080] The test call module 207 is configured to call at least one test instruction to be used by interacting with a call option on the interactive operation interface. Specifically, a test function (call option) can be clicked on the interactive operation interface to call the desired test instruction from the packaged test instruction set. The interactive operation interface can automatically complete all test options one by one, or it can execute test options based on input selected by the test user.

[0081] In an optional embodiment, the test calling module 207 calls at least one test instruction in use by interacting with a call option on the interactive operation interface. Specifically, the method includes: selecting a call sub-option by interacting with the call option on the interactive operation interface; and calling a test instruction in use based on the selected call sub-option. By setting sub-options to perform tests, the aircraft entertainment display system can be tested in a more refined manner.

[0082] The test code acquisition and value assignment module 208 is used to acquire the test code and value assignment corresponding to the test instruction to be used, and transmit it to the aircraft entertainment display system to be tested through the second interface for testing; specifically, after the test instruction to be used is determined, the test code and value assignment corresponding to the test instruction are automatically input to the entertainment display system to be tested through the serial port to start testing.

[0083] The test result display module 209 is used to receive the test results of the test instructions to be used and display the test results on the interactive operation interface. Specifically, after the aircraft entertainment display system has completely executed the test code, it transmits the test results (which can be specific test results, such as the number of pixel errors, etc.; or a result indicating whether the test passed, such as "pass") back to the computer port of the test user through the serial port. The specific test results will be displayed on the computer interface. Figure 4 The status display is displayed in real time in the "Status Display" column, or the "pass" is displayed through the interactive operation interface. In addition, after completing all test items according to the above steps, the software can also automatically generate a test report for the test user to print.

[0084] The test system for an aircraft entertainment display system provided in this embodiment can directly access the underlying code of the aircraft entertainment display system, parse the code into test instructions, and encapsulate the test instructions in a visual and interactive operation interface, which can be used to test the aircraft entertainment display system. This test system for an aircraft entertainment display system in this embodiment can also repair the aircraft entertainment display system even if the original industrial computer fails, ensuring the safe operation of the aircraft entertainment display system during this period.

[0085] In addition, since the entertainment display system being tested is installed on an aircraft, and the service time of the aircraft is usually dozens or hundreds of years, some aircraft entertainment display systems may be old products, and it may be difficult to find replacement parts for the components of the aircraft entertainment display system, resulting in the dilemma of not being able to report for repair even if a failure occurs. Therefore, after detecting that the aircraft entertainment display system has a failure, it is also necessary to make a comprehensive judgment based on the above actual situation whether the aircraft entertainment display system needs to be repaired. In an optional embodiment, the test system 20 of this embodiment may also include a repair determination system 30 that determines whether repair is needed based on the fault level and the age, such as Figure 7 As shown, the repair determination system 30 specifically includes:

[0086] The weight table module 301 is used to establish an impact factor weight table, wherein the impact factors include a first impact factor and a second impact factor, the first impact factor is the fault level, and the second impact factor is the old and new level. The impact factor weight table includes weight values ​​corresponding to different impact factor levels. Specifically, the fault level and the old and new level will affect the decision on whether the aircraft entertainment display system needs to be repaired. Therefore, both are used as impact factors for calculation to comprehensively consider whether the aircraft entertainment display system needs to be repaired.

[0087] Fault determination module 302 is configured to determine the fault level corresponding to the aircraft entertainment display system under test based on the test results and the fault determination threshold table, and to determine the weight value of the first influencing factor based on the fault level and influencing factor weight table. Specifically, the fault level can be determined by comparing the test results.

[0088] In one optional embodiment, a fault determination threshold table includes thresholds corresponding to each fault level. The fault determination module 302 determines the fault level of the aircraft entertainment display system under test based on the test results and the fault determination threshold table. This specifically includes comparing the test results with the thresholds corresponding to each fault level and determining the fault level corresponding to the test results based on the comparison results. Specifically, the test results may include detailed fault information. For example, in the case of a touch screen test, the test results may include the error status of specific pixels (e.g., the number of pixels with errors). The fault determination threshold table is configured for each test. For example, in the case of a touch screen test, the table may include thresholds for the number of pixel errors corresponding to different fault levels. For example, fewer than 10 pixels (or 0.1% of pixels) with errors may be considered a minor fault; more than 2,000 pixels (or 20% of pixels) with errors may be considered an irreversible fault. Furthermore, during fault determination, the distribution and concentration of the error pixels may be considered to comprehensively determine the fault level.

[0089] The age determination module 303 is configured to determine the model and service age of the aircraft entertainment display system under test, determine the age level of the aircraft entertainment display system under test based on the model and service age of the aircraft entertainment display system under test, and determine the weight value of the second influencing factor based on the age level and the influencing factor weight table. Specifically, the model and service age of the aircraft entertainment display system under test can be obtained based on the aforementioned basic information of the aircraft entertainment display system under test. By comprehensively considering the model and service age, the age level of the aircraft entertainment display system under test can be more reasonably evaluated.

[0090] Repair determination module 304 is configured to determine whether the aircraft entertainment display system under test requires repair based on the weighted values ​​of the first and second influencing factors. Specifically, based on the aforementioned weighted values, the weighted values ​​of the first and second influencing factors may be added or multiplied together, and the result of this addition or multiplication may be compared with a preset repair threshold. If the preset repair threshold is reached, a repair request is indicated.

[0091] During automated testing, the repair determination system 30 first determines the fault level based on the returned test results. The system then considers the aircraft's age (model, age, etc.) to determine whether the test has passed and whether repairs are necessary. Minor faults involving older systems may not require a repair report. Irreversible faults, regardless of age, require a repair report.

[0092] In the description of the embodiments of the present invention, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "center", "top", "bottom", "top", "bottom", "inside", "outside", "inner side", "outer side" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. Among them, "inside" refers to an internal or enclosed area or space. "Periphery" refers to the area surrounding a specific component or specific area.

[0093] In the description of the embodiments of the present invention, the terms "first," "second," "third," and "fourth" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly specifying the number of the technical features indicated. Therefore, a feature specified as "first," "second," "third," or "fourth" may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "plurality" means two or more.

[0094] In the description of the embodiments of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "connected," "connected," and "assembled" should be understood in a broad sense. For example, they may refer to fixed connections, detachable connections, or integral connections; they may refer to direct connections, indirect connections through an intermediate medium, or internal connections between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention in specific circumstances.

[0095] In the description of the embodiments of the present invention, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0096] In describing the embodiments of the present invention, it should be understood that "-" and "~" represent a range between two values, and the range includes the endpoints. For example, "AB" represents a range greater than or equal to A and less than or equal to B. "A~B" represents a range greater than or equal to A and less than or equal to B.

[0097] In describing the embodiments of the present invention, the term "and / or" is used herein to describe a relationship between associated objects, indicating that three possible relationships exist. For example, "A and / or B" can represent three situations: A exists alone, A and B exist simultaneously, and B exists alone. Furthermore, the character " / " is generally used herein to indicate that the associated objects are in an "or" relationship.

[0098] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A test method for an aircraft entertainment display system, characterized in that: include: Connect to the aircraft entertainment display system to be monitored via the serial bus; Capturing the running code of the aircraft entertainment display system to be monitored when it is powered on, wherein capturing the running code of the aircraft entertainment display system to be monitored when it is powered on specifically comprises: using the serial port bus to obtain a data stream of the aircraft entertainment display system to be monitored when it is powered on, and parsing the data stream to obtain the running code; Input extraction instructions to obtain multiple groups of test codes from the running code; Obtaining the assignment of each set of the test codes through debugging, and forming corresponding test instructions according to the test codes and the assignment of the test codes; Encapsulating the test instructions respectively according to their functions to form an interactive operation interface, wherein the interactive operation interface includes at least one calling option, each of the calling options being used to call one or more of the test instructions; Connect to the aircraft entertainment display system under test; Call at least one test instruction to be used by interacting with the calling option of the interactive operation interface; Obtaining the test code and value corresponding to the test instruction to be used, and transmitting them to the aircraft entertainment display system to be tested for testing; Receive the test result of the standby test instruction and display the test result on the interactive operation interface.

2. The testing method according to claim 1, wherein: The method further comprises: Establishing an impact factor weight table, wherein the impact factor includes a first impact factor and a second impact factor, the first impact factor is a fault level, the second impact factor is a new and old level, and the impact factor weight table includes weight values ​​corresponding to different levels of the impact factor; Determining the fault level corresponding to the aircraft entertainment display system under test according to the test result and the fault determination threshold table, and determining the weight value of the first influencing factor according to the fault level and the influencing factor weight table; Determine the model and service life of the aircraft entertainment display system to be tested; Determining the age level corresponding to the aircraft entertainment display system to be tested based on the model and service life of the aircraft entertainment display system to be tested, and determining the weight value of the second impact factor based on the age level and the impact factor weight table; Whether the aircraft entertainment display system to be tested needs to be repaired is determined according to the weight value of the first influencing factor and the weight value of the second influencing factor.

3. The testing method according to claim 2, characterized in that: The fault determination threshold table includes: a threshold corresponding to each fault level; Determining the fault level of the aircraft entertainment display system to be tested based on the test results and a fault determination threshold table specifically includes: The test result is compared with a threshold value corresponding to each of the fault levels, and the fault level corresponding to the test result is determined according to the comparison result.

4. The testing method according to claim 1, wherein: The calling option further includes: a calling sub-option, wherein the calling sub-option is used to call one of the test instructions; The calling of at least one test instruction to be used by interacting with the calling option of the interactive operation interface specifically includes: Selecting one of the call sub-options by interacting with the call option on the interactive operation interface; One of the test instructions to be used is called according to the selected calling sub-option.

5. A test system for an aircraft entertainment display system, characterized in that: include: The first interface is used to connect to the aircraft entertainment display system to be monitored via a serial bus; a code capture module, configured to capture the running code of the aircraft entertainment display system to be monitored when it is powered on, wherein capturing the running code of the aircraft entertainment display system to be monitored when it is powered on specifically comprises: receiving a data stream of the aircraft entertainment display system to be monitored running when it is powered on acquired via the serial port bus, and parsing the data stream to obtain the running code; A code extraction module, configured to input an extraction instruction to obtain multiple groups of test codes from the running code; A test instruction generation module is used to obtain the assignment of each group of test codes through debugging, and form corresponding test instructions according to the test codes and the assignment of the test codes; A test instruction encapsulation and interactive operation module, configured to encapsulate the test instructions according to their functions to form an interactive operation interface, wherein the interactive operation interface includes at least one call option, each of which is used to call one or more test instructions; The second interface is used to connect to the aircraft entertainment display system under test; A calling test module, configured to call at least one test instruction to be used by interacting with the calling option of the interactive operation interface; a test code acquisition and value assignment module, configured to acquire the test code and value assignment corresponding to the test instruction to be used, and transmit the acquired test code and value assignment to the aircraft entertainment display system to be tested via the second interface for testing; The test result display module is used to receive the test result of the test instruction to be used and display the test result on the interactive operation interface.

6. The test system according to claim 5, characterized in that: The system further comprises: A weight table module is used to establish an impact factor weight table, wherein the impact factors include a first impact factor and a second impact factor, the first impact factor is the fault level, the second impact factor is the new and old levels, and the impact factor weight table includes weight values ​​corresponding to different levels of the impact factors; a fault determination module, configured to determine the fault level corresponding to the aircraft entertainment display system under test according to the test result and a fault determination threshold table, and to determine a weight value of the first influencing factor according to the fault level and the influencing factor weight table; a newness and oldness determination module, configured to determine the model and service age of the aircraft entertainment display system to be tested, determine the newness and oldness grade corresponding to the aircraft entertainment display system to be tested based on the model and service age of the aircraft entertainment display system to be tested, and determine the weight value of the second impact factor based on the newness and oldness grade and the impact factor weight table; The repair determination module is used to determine whether the aircraft entertainment display system to be tested needs to be repaired based on the weight value of the first influencing factor and the weight value of the second influencing factor.

7. The test system according to claim 6, characterized in that The fault determination threshold table includes: a threshold corresponding to each fault level; The fault determination module determines the fault level of the aircraft entertainment display system to be tested according to the test result and the fault determination threshold table, specifically including: The test result is compared with a threshold value corresponding to each of the fault levels, and the fault level corresponding to the test result is determined according to the comparison result.

8. The test system according to claim 5, wherein: The calling option further includes: a calling sub-option, wherein the calling sub-option is used to call one of the test instructions; The calling test module interacts with the calling option of the interactive operation interface to call at least one test instruction to be used, specifically including: Selecting one of the call sub-options by interacting with the call option on the interactive operation interface; One of the test instructions to be used is called according to the selected calling sub-option.

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