Testing method and system for aircraft entertainment display system

Abstract

The invention relates to the technical field of aircraft system testing, in particular to a testing method and system for an aircraft entertainment display system, and the method comprises the steps: connecting an aircraft entertainment display system to be monitored; capturing an operation code of the to-be-monitored aircraft entertainment display system when the aircraft entertainment display system is started; inputting an extraction instruction to obtain multiple groups of test codes from the operation codes; assignments of each group of test codes are obtained through debugging, and corresponding test instructions are formed; respectively packaging the test instructions to form an interactive operation interface; calling at least one to-be-used test instruction through the interactive operation interface; acquiring a test code and an assignment corresponding to the to-be-used test instruction, and transmitting the test code and the assignment to the to-be-tested aircraft entertainment display system for testing; and receiving a test result operated by the standby test instruction, and displaying the test result on the interactive operation interface. By utilizing the method, the aircraft entertainment display system can be overhauled after the original factory industrial personal computer breaks down, and safe operation in the period is ensured.

Description

Technical Field

[0001] The 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 the existing technology, when testing an aircraft entertainment display system (such as an aircraft entertainment display system produced by Thales), it is necessary to use the original industrial computer and the original automatic testing software to perform functional testing, otherwise the test cannot be performed. However, the original industrial computer sometimes fails. Once the industrial computer fails, the aircraft entertainment display system cannot be tested. In addition, after the original industrial computer fails, it must be sent to the original factory for maintenance, and the maintenance time can be as long as several months. During this period, the aircraft entertainment display system cannot be tested, which poses a safety hazard. Therefore, how to repair the aircraft entertainment display system after the original industrial computer fails to ensure the safe operation of the aircraft entertainment display system during this period is a problem that needs to be solved urgently. 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 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 assignment of the test codes; encapsulating the test instructions respectively according to the functions of the test instructions to form an interactive operation interface, wherein the interactive operation interface includes at least one calling option, and each of the calling options is used to call one or more of the test instructions; connecting the aircraft entertainment display system to be tested; calling at least one standby test instruction by interacting with the calling option of the interactive operation interface; obtaining the test code and assignment corresponding to the standby test instruction, and transmitting them to the aircraft entertainment display system to be tested for testing; receiving the test result of the running of the standby test instruction, and displaying the test result on the interactive operation interface.

[0004] Another aspect of the present invention provides a test system for an aircraft entertainment display system, comprising: The first interface is used to connect to the aircraft entertainment display system to be monitored; A code capture module, used to capture the running code of the aircraft entertainment display system to be monitored when it is turned on; A code extraction module, used for inputting extraction instructions 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 the 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, used to encapsulate 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 which is used to call one or more of the test instructions; The second interface is used to connect to the entertainment display system of the aircraft to be tested; A calling test module, used for calling 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 is used to acquire the test code and value assignment corresponding to the test instruction to be used, and transmit the test code and value assignment to the aircraft entertainment display system to be tested through 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.

[0005] The beneficial effect of the present invention is that, through the test method and system for an aircraft entertainment display system provided by the present invention, the underlying code of the aircraft entertainment display system can be directly obtained, and the code can be parsed and converted into test instructions, and the test instructions are encapsulated in a visual and interactive operation interface, and the aircraft entertainment display system is tested using the operation interface. The test method and system for an aircraft entertainment display system of the present invention can also repair the aircraft entertainment display system after the original industrial computer fails, so as to ensure the safe operation of the aircraft entertainment display system during this period. BRIEF DESCRIPTION OF THE DRAWINGS

[0006] Figure 1 A flow chart of a testing method for an aircraft entertainment display system provided in Embodiment 1 of the present invention; Figure 2 An example diagram of the underlying running code when the aircraft entertainment display system provided by Embodiment 1 of the present invention is turned on; Figure 3 An example diagram of the software interface design of the interactive operation interface provided in Example 1 of the present invention; Figure 4 This is an example diagram of a sub-option interface of the interactive operation interface provided in Example 1 of the present invention; Figure 5 A flowchart of determining a repair request based on a fault level and a new or old level provided in Embodiment 1 of the present invention; Figure 6Schematic diagram of the test system structure of the aircraft entertainment display system provided in Embodiment 1 of the present invention; Figure 7 Schematic diagram of the repair report determination system structure provided in Embodiment 1 of the present invention. Specific implementation manners

[0007] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0008] Embodiment 1 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. As Figure 1 shown, the test method for the aircraft entertainment display system in this embodiment specifically includes the following steps: Step S101, connect the aircraft entertainment display system to be monitored; specifically, in the debugging part, an aircraft entertainment display system that can operate normally can be used as the aircraft entertainment display system to be monitored, so as to obtain a complete data stream and thus obtain the correct operating code. In a specific implementation method, the aircraft entertainment display system to be monitored can be connected through a serial bus. For example, a general RS232 serial port software can be installed on the computer port of the test user. The test user uses an RS232 serial cable and a network cable to connect the aircraft entertainment display system (hereinafter also referred to as the display) to the test user's computer.

[0009] Step S102, capture the operating code of the aircraft entertainment display system to be monitored when it is powered on; specifically, power on and run the aircraft entertainment display system to be monitored, and the test user's computer reads the underlying operating code of the aircraft entertainment display system when it is powered on through the RS232 serial cable. As Figure 2 shown is an example diagram of the underlying operating code of the aircraft entertainment display system when it is powered on. In an alternative implementation manner, step S102 can be specifically implemented through the following steps: Step 1021, use the serial bus to obtain the data stream running on the aircraft entertainment display system to be monitored when it is powered on; specifically, a serial port debugging tool can be used to intercept the data, and data timing synchronization and other processing may also be required when intercepting the data to ensure the accuracy of the data.

[0010] Step 1022: Parse and obtain the running code from the data stream. Specifically, the captured data stream may be binary or in a specific encoding and needs to be parsed into a readable format. It may also be necessary to reverse-engineer and parse the protocol structure (such as including message headers, checksums, data fields, etc.). For example, depth packet parsing algorithms and CRC checksum reversal can be used to parse the data stream in order to obtain the running code. By parsing the data stream, the accuracy of the obtained running code can be ensured.

[0011] Step S103: Use an extraction instruction to obtain multiple sets of test code from the running code; specifically, the extraction instruction is used to determine which of the numerous running codes are test codes and extract them. For example, for the Thales aircraft entertainment display system, the extraction instruction can be the atp_svdu4 instruction. The atp_svdu4 belongs to a low-level debugging instruction and is 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 including touch screen tests, image tests, etc.).

[0012] In a specific implementation example, the extraction instruction statement root@android: / # atp_svdu4_ can be input on the running code page. This instruction is used to obtain the test code of the aircraft entertainment display system. Some of the obtained test code can be as follows: rooteandroid: / # atp_svdu4_ atp_svdu4_atpusb_test.sh atp_svdu4_audio_io_test.sh atp_svdu4_audio_setup.sh atp_svdu4_audiocontrol.sh atp_svdu4_audioplayer.sh atp_svdu4_button_test.sh atp_svdu4_ccr_test.sh atp_svdu4_disableidle_scrn.sh atp_svdu4_display_hone_scrn.sh atp_svdu4_eth_txrx_test.sh atp_svdu4_ext_video_test.sh atp_svdu4_ext_video_test2.sh atp_svdu4_getpartnum.sh atp_svdu4_hdmipip_test.sh atp_svdu4_hdmipip_test2.sh Step S104: Obtain the assignments of each group of test codes through debugging, and form corresponding test instructions based on the test codes and their assignments. Specifically, after obtaining the test codes, it is also necessary to determine the assignment rules of the code parameters through debugging, and finally form a complete set of test instructions. Only after correctly assigning the test codes can a complete set of test instructions be formed.

[0013] Step S105: Package the test instructions separately according to the functions of the test instructions to form an interactive operation interface. Among them, the interactive operation interface includes at least one call option, and each call option is used to call one or more test instructions. Specifically, classify the test instructions according to their functions (such as image testing, audio testing, etc.) and package them to obtain a corresponding visual and interactive test interface. The interactive operation interface can be in the form of a visual and interactive software product, and the interactive operation interface is implemented through the software interface. The interactive operation interface can integrate many test options and complete the test by interacting with the test options. For example, a "touch screen test" option can be set in the interactive operation interface. When this option of "touch screen test" is selected, the corresponding test instructions are called, and then the code contained in the instructions is transmitted to the aircraft entertainment display system through the serial port to test the aircraft entertainment display system.

[0014] In an optional embodiment, the call option further includes: a call sub-option, and the call sub-option is used to call one test instruction. By setting the sub-option, the test of the aircraft entertainment display system can be completed more precisely.

[0015] In a specific embodiment, the interactive operation interface can be as Figure 3 、 4 shown. Figure 3 It is a software interface design of an interactive operation interface, and various test options for the THALES aircraft entertainment display system to be implemented in this embodiment can be included on this software interface. Figure 4 It is an example of the sub-option interface, Figure 4 as shown is the sub-option interface under the "memory card test" call option. The operation interface and operation program of the present invention can be designed based on the C++ language, which is convenient for users to operate.

[0016] It should be noted that, Figure 3 and Figure 4The 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.

[0017] Through the above steps S101 to S105, a visual interactive operation interface for testing is constructed, so as to be used for subsequent testing of the corresponding system. 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.

[0018] Step S106, connecting 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.

[0019] In a specific implementation, the test user can use an RS232 serial port cable and an Ethernet cable to connect a 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 In the main interface of the software, you can also confirm and fill in the basic information of the aircraft entertainment display system to be tested for subsequent use. At the same time, in the main interface of the software, you can also check whether the RS232 port and network port IP have been automatically recognized correctly by the software.

[0020] Step S107, by interacting with the calling option of the interactive operation interface, at least one test instruction to be used is called; specifically, a test function (calling option) can be clicked on the interactive operation interface to call the test instruction to be used from the aforementioned packaged test instruction set. The interactive operation interface can automatically complete all test options one by one, or execute the test options according to the input selected by the test user.

[0021] In an optional implementation, by interacting with the call option of the interactive operation interface, at least one test instruction to be used is called, specifically comprising: selecting a call sub-option by interacting with the call option of the interactive operation interface; and calling a test instruction to be used according to the selected call sub-option. By setting the sub-options to perform the test, the test of the aircraft entertainment display system can be completed in a more refined manner.

[0022] In a specific implementation, the test can be started after everything is ready in step S106. Test items are selected one by one according to the system settings or the test user's input, or a secondary test interface (such as Figure 4The sub-option interface shown). In the secondary test interface, each sub-test item of the current test item can be displayed. After receiving the input to start the test (for example, after receiving the start instruction set by the system or detecting that the corresponding test option button is clicked), the automatic test will start.

[0023] Step S108: Obtain the test code and assignment corresponding to the test instruction to be used, and transmit them to the aircraft entertainment display system to be tested for testing; specifically, after determining the test instruction to be used, the test code and assignment corresponding to this test instruction are automatically input into the entertainment display system under test through the serial port to start the test.

[0024] Step S109: Receive the test results of the test instruction to be used, and display the test results on the interactive operation interface. Specifically, after the aircraft entertainment display system completely executes the test code, it transmits the test results (which can be specific test results, such as the number of pixel errors; or the result representing whether the test passes, such as "pass") back to the computer port of the test user through the serial port. The specific test results will be presented in real time in the "Status Display" column as shown in Figure 4 or display "pass" through the interactive operation interface. In addition, after completing the tests for all test items according to the above steps, the software can also automatically generate a test report for the test user to choose to print and use.

[0025] The test method for the aircraft entertainment display system provided in this embodiment can directly obtain the underlying code of the aircraft entertainment display system, parse and convert 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 test method for the aircraft entertainment display system in this embodiment can also repair the aircraft entertainment display system even after the original factory industrial computer fails, so as to ensure the safe operation of the aircraft entertainment display system during this period.

[0026] In addition, since the entertainment display system under test is installed on the aircraft, and the service life of the aircraft is usually several decades or even hundreds of years, there will be some aircraft entertainment display systems that are old models. It may be difficult to find replacement parts for the components of the aircraft entertainment display system, resulting in a situation where it is impossible to report a repair even if a failure occurs. Therefore, after detecting that the aircraft entertainment display system fails, it is also necessary to make an overall judgment based on the above actual situation to determine whether the aircraft entertainment display system needs to be reported for repair. Therefore, in an optional embodiment, the test method for the aircraft entertainment display system in this embodiment further includes the following steps for judging whether to report a repair according to the failure level and the new and old level, as Figure 5 shown: Step S110: Establish an influence factor weight table. The influence factors include a first influence factor and a second influence factor. The first influence factor is the fault level, and the second influence factor is the newness level. The influence factor weight table includes the corresponding weight values when the influence factors take different levels. Specifically, both the fault level and the newness level will affect the decision on whether the aircraft entertainment display system needs to be reported for repair. Therefore, both are used as influence factors for calculation to comprehensively consider whether the aircraft entertainment display system needs to be repaired.

[0027] In a specific embodiment, the fault level can be set to 4 levels. Levels 1 to 4 respectively represent: irreversible fault, severe fault, medium fault, and minor fault. Weight values can be assigned to fault levels 1 to 4 respectively. For example, the weight values can be 100, 10, 5, and 1 respectively. Among them, the weight value of the irreversible fault is set to be particularly high, which can ensure that once an irreversible fault occurs, regardless of the newness degree, it must be reported for repair. The newness level is set to 4 levels. Levels 1 to 4 respectively represent: very new, semi-new, relatively old, and old. Weight values can be assigned to newness levels 1 to 4 respectively. For example, the weight values can be 20, 10, 5, and 1 respectively.

[0028] Step S111: Determine the fault level corresponding to the aircraft entertainment display system to be tested according to the test results and the fault determination threshold table, and determine the weight value of the first influence factor according to the fault level and the influence factor weight table. Specifically, the fault level can be judged by comparing the test results.

[0029] In an alternative embodiment, the fault determination threshold table includes: the threshold corresponding to each fault level. Determining the fault level of the aircraft entertainment display system to be tested according to the test results and the fault determination threshold table specifically includes: comparing the test results with the threshold corresponding to each fault level, and determining the fault level corresponding to the test results according to the comparison results. Specifically, the test results can be the specific fault details. Taking the test of the touch screen as an example, the test results can be the error situation of specific pixels (such as how many pixel points are in error). The fault determination threshold table is set separately for each test. Taking the test of the touch screen as an example, the fault determination threshold table can respectively set the thresholds of the number of pixel points in error corresponding to different fault levels. For example, if less than 10 pixel points (or 0.1% of the pixel points) are in error, it can be judged as a minor fault; if more than 2000 pixel points (or 20% of the pixel points) are in error, it can be judged as an irreversible fault. In addition, when determining the fault, the distribution concentration of the error pixel points can also be considered to comprehensively determine the fault level.

[0030] Step S112: Determine the model and service life of the aircraft entertainment display system to be tested. Specifically, the model and service life can be obtained according to the basic information of the aircraft entertainment display system to be tested described above.

[0031] Step S113: Determine the new - old level corresponding to the entertainment display system of the aircraft to be tested according to the model and service life of the entertainment display system of the aircraft to be tested, and determine the weight value of the second influencing factor according to the new - old level and the influencing factor weight table. Specifically, by comprehensively considering its model and service life, the new - old level of the entertainment display system of the aircraft to be tested can be evaluated more reasonably.

[0032] Step S114: Determine whether the entertainment display system of the aircraft to be tested needs to be reported for repair according to the weight value of the first influencing factor and the weight value of the second influencing factor. Specifically, according to the setting of the foregoing weight values, the weight value of the first influencing factor and the weight value of the second influencing factor can be added or multiplied. Compare the result of adding or multiplying the two with the preset repair threshold. If the preset repair threshold is reached, repair processing is required.

[0033] Based on the above steps, during the automated testing process, first determine the fault level based on the test results returned by the test, and then combine the old - new degree of the aircraft model (model, years, etc.) to determine whether the test passes and whether repair is required. For minor faults and older systems, no repair report may be made; for irreversible faults, repair reports are required regardless of new or old.

[0034] Take a specific test example to illustrate: When testing the touch screen, set the repair threshold to 10, and the processing method for the weight value of the first influencing factor and the weight value of the second influencing factor is multiplication. If the test results returned are that 10 pixel points are displayed incorrectly, and the pixel positions of these 10 pixel points are relatively far apart, the fault level will be marked as level 4 at this time. If the aircraft model is very old at this time, the weight values of both the fault level and the new - old level are 1. At this time, the comprehensive calculation result of the first influencing factor and the second influencing factor is 1, which does not reach the preset repair threshold of 10. Therefore, the test result feedback is passed. The reason for this judgment is that some aircraft models are very old, there may be no 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 usability, no repair report is made. If the marked fault level is level 4, but the aircraft is very new, the weight value of the fault level is 1, but the weight value of the new - old level is 20. At this time, the comprehensive calculation result of the first influencing factor and the second influencing factor is 20, which has reached the preset repair threshold of 10. Then the display test fails and repair is required. However, if the fault level is level 1, at this time the weight value of the fault level is 100, then regardless of whether the aircraft is new or old, the comprehensive calculation result of the first influencing factor and the second influencing factor exceeds the preset repair threshold of 10. Therefore, the test fails and repair is required.

[0035] This embodiment also provides a test system 20 for an aircraft entertainment display system, which is used to execute the aforementioned test method for the aircraft entertainment display system. The content that has been elaborated in detail in the aforementioned test method will not be repeated here. Refer to the description in the aforementioned test method. As Figure 6 shown, the test system 20 includes: A first interface 201 for connecting the aircraft entertainment display system to be monitored; specifically, the first interface 201 and the subsequent second interface 206 can be the same serial bus interface or different serial bus interfaces. For example, a general RS232 serial port software can be installed on the computer port of the test user, and the test user uses an RS232 serial cable and a network cable to connect the aircraft entertainment display system to the test user's computer.

[0036] A code capture module 202 for capturing the running code of the aircraft entertainment display system to be monitored when it is powered on; specifically, when the aircraft entertainment display system to be monitored is powered on and running, the test user's computer reads the underlying running code of the aircraft entertainment display system when it is powered on through an RS232 serial cable.

[0037] In an optional embodiment, the code capture module 202 capturing the running code of the aircraft entertainment display system to be monitored when it is powered on specifically includes: receiving the data stream obtained by the serial bus of the aircraft entertainment display system to be monitored when it is powered on; parsing and obtaining the running code from the data stream. Specifically, a serial port debugging tool can be used to intercept data through the serial bus of the first interface 201. When intercepting data, it may also be necessary to perform processing such as timing synchronization on the data to ensure the accuracy of the data. The captured data stream may be binary or in a specific encoding and needs to be parsed into a readable format. It may also be necessary to reverse engineer and parse the protocol structure (such as including a message header, checksum, data field, etc.). For example, a deep packet parsing algorithm and CRC checksum reversal can be used to parse the data stream in order to obtain the running code. By parsing the data stream, the accuracy of the obtained running code can be ensured.

[0038] A code extraction module 203 for obtaining multiple groups of test codes from the running code by inputting an extraction instruction; specifically, the extraction instruction is used to determine which of the numerous running codes are test codes and extract them. For example, for the THALES aircraft entertainment display system, the extraction instruction can adopt the atp_svdu4 instruction. The atp_svdu4 belongs to an underlying debugging instruction and is used to enter the engineering test mode of the THALES aircraft entertainment display system. After inputting this instruction, the system will return multiple groups of test codes (such as test codes including touch screen tests, image tests, etc.).

[0039] The test instruction generation module 204 is used to obtain the assignment of each set of test codes through debugging, and form corresponding test instructions according to the test codes and the assignment of the test codes; specifically, after obtaining the test codes, it is also necessary to determine the assignment rules of the code parameters through debugging, and finally form a complete test instruction set. Only after the test codes are correctly assigned, can a complete test instruction be formed.

[0040] The test instruction encapsulation and interactive operation module 205 is used to encapsulate the test instructions according to the functions of the test instructions to form an interactive operation interface, wherein the interactive operation interface includes at least one call option, and each call option is used to call one or more test instructions; specifically, each test instruction is encapsulated according to the functional classification of the test instruction (such as image test, audio test, etc.) to obtain a corresponding visual interactive test interface. The interactive operation interface can be formed in the form of a visual and interactive software product, and the interactive operation interface is implemented through a software interface. The interactive operation interface can integrate many test options, and the test is completed by interacting with the test options. For example, a "touch screen test" option can be set in the interactive operation interface. When the "touch screen test" option is selected, the corresponding test instruction is called, and then the code contained in the instruction is transmitted to the aircraft entertainment display system through the serial port to implement the test of the aircraft entertainment display system.

[0041] In an optional implementation, the call option further includes: a call sub-option, and 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.

[0042] 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.

[0043] The calling test module 207 is used to call at least one test instruction to be used by interacting with the calling option of the interactive operation interface; specifically, a test function (calling option) can be clicked on the interactive operation interface to call the test instruction to be used from the aforementioned packaged test instruction set. The interactive operation interface can automatically complete all test options one by one, or execute the test options according to the input selected by the test user.

[0044] In an optional implementation, the calling test module 207 calls at least one test instruction to be used by interacting with the calling option of the interactive operation interface, specifically including: selecting a calling sub-option by interacting with the calling option of the interactive operation interface; and calling a test instruction to be used according to the selected calling sub-option. By setting the sub-options to perform the test, the test of the aircraft entertainment display system can be completed in a more refined manner.

[0045] 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 them 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 the test.

[0046] 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 the results 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 results will be displayed on the computer port such as Figure 4 The status is displayed in real time in the "Status Display" column, or the "pass" is displayed through the interactive operation interface. In addition, after completing the test of all test items according to the above steps. The software can also automatically generate a test report so that the test user can choose to print it for use.

[0047] The test system for the aircraft entertainment display system provided in this embodiment can directly obtain the underlying code of the aircraft entertainment display system, convert the code into test instructions, encapsulate the test instructions in a visual and interactive operation interface, and use the operation interface to test the aircraft entertainment display system. The test system for the aircraft entertainment display system of this embodiment can also repair the aircraft entertainment display system after the original industrial computer fails, so as to ensure the safe operation of the aircraft entertainment display system during this period.

[0048] In addition, since the measured entertainment display system is installed on an aircraft, and the service life of an aircraft is usually several decades or even hundreds of years, there will be some aircraft entertainment display systems that are old models. Moreover, it may be difficult to find replacement parts for the components of the aircraft entertainment display system, resulting in a situation where even if a failure occurs, it is impossible to report for repair. Therefore, after detecting a failure in the aircraft entertainment display system, it is also necessary to make an overall judgment based on the above actual situation as to whether the aircraft entertainment display system needs to be reported for repair. In an alternative embodiment, the test system 20 of this embodiment may further include a repair determination system 30 that determines whether to report for repair based on the failure level and the degree of newness or oldness, as Figure 7 shown. The repair determination system 30 specifically includes: A weight table module 301 for establishing an influence factor weight table, where the influence factors include a first influence factor and a second influence factor. The first influence factor is the failure level, and the second influence factor is the newness or oldness level. The influence factor weight table includes the corresponding weight values when the influence factors take different levels. Specifically, both the failure level and the newness or oldness level will affect the decision on whether the aircraft entertainment display system needs to be reported for repair. Therefore, the two are used as influence factors for calculation to comprehensively consider whether to perform a repair process on the aircraft entertainment display system.

[0049] A failure determination module 302 for determining the failure level corresponding to the aircraft entertainment display system to be tested according to the test results and the failure determination threshold table, and determining the weight value of the first influence factor according to the failure level and the influence factor weight table. Specifically, the failure level can be determined by comparing the test results.

[0050] In an alternative embodiment, the failure determination threshold table includes: the thresholds corresponding to each failure level. The failure determination module 302 determines the failure level of the aircraft entertainment display system to be tested according to the test results and the failure determination threshold table, specifically including: comparing the test results with the thresholds corresponding to each failure level, and determining the failure level corresponding to the test results according to the comparison results. Specifically, the test results can be the specific failure details. Taking the test of the touch screen as an example, the test results can be the error conditions of specific pixels (such as the number of pixel points in error). The failure determination threshold table is set separately for each test. Taking the test of the touch screen as an example, the failure determination threshold table can respectively set the thresholds for the number of pixel points in error corresponding to different failure levels. For example, if there are less than 10 pixel points (or 0.1% of the pixel points) in error, it can be determined as a minor failure; if there are more than 2000 pixel points (or 20% of the pixel points) in error, it can be determined as an irreversible failure. In addition, when determining the failure, the distribution concentration of the pixel points in error can also be considered to comprehensively determine the failure level.

[0051] The new and old determination module 303 is used to determine the model and service life of the entertainment display system of the aircraft to be tested, determine the corresponding new and old level of the entertainment display system of the aircraft to be tested according to the model and service life of the entertainment display system of the aircraft to be tested, and determine the weight value of the second influencing factor according to the new and old level and the influencing factor weight table; specifically, the model and service life can be obtained according to the basic information of the entertainment display system of the aircraft to be tested described above, and by comprehensively considering its model and service life, the new and old level of the entertainment display system of the aircraft to be tested can be evaluated more reasonably.

[0052] The repair request determination module 304 is used to determine whether the entertainment display system of the aircraft to be tested needs to request repair according to the weight value of the first influencing factor and the weight value of the second influencing factor. Specifically, according to the setting of the weight value described above, the weight value of the first influencing factor and the weight value of the second influencing factor can be added or multiplied, and the result of adding or multiplying the two is compared with the preset repair request threshold. If the preset repair request threshold is reached, repair request processing is required.

[0053] Based on the above repair request determination system 30, during the automated test process, first determine the fault level based on the test results returned by the test, and then determine whether the test passes and whether repair is required in combination with the old and new degree (model, service life, etc.) of the aircraft model. For minor faults and older systems, no repair request may be made; for irreversible faults, repair requests are required regardless of new or old.

[0054] In the description of the embodiments of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "center", "top", "bottom", "top part", "bottom part", "inner", "outer", "inner side", "outer side", etc. is the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and is 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 a limitation of the present invention. Among them, the "inner side" refers to the internal or enclosed area or space. The "periphery" refers to the area around a specific component or specific area.

[0055] In the description of the embodiments of the present invention, the terms "first", "second", "third", "fourth" are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, the features defined with "first", "second", "third", "fourth" may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise specified, the meaning of "a plurality" is two or more.

[0056] In the description of the embodiments of the present invention, it should be noted that unless otherwise clearly specified and defined, the terms "installation", "connection", "linkage", and "assembly" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a direct connection, or an indirect connection through an intermediate medium, and it may be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0057] In the description of the embodiments of the present invention, specific features, structures, materials, or characteristics can be combined in a suitable manner in any one or more embodiments or examples.

[0058] In the description of the embodiments of the present invention, it should be understood that "-" and "~" represent the range between two numerical values, and this range includes the endpoints. For example, "A - B" 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.

[0059] In the description of the embodiments of the present invention, the term "and / or" herein is merely a description of the association relationship of the associated objects, indicating that there can be three relationships. For example, A and / or B can represent: A exists alone, A and B exist simultaneously, and B exists alone. In addition, the character " / " herein generally represents an "or" relationship between the associated objects before and after.

[0060] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirits of the present invention. The scope of the present 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; Capturing the running code of the aircraft entertainment display system to be monitored when it is turned on; Input extraction instructions 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 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 which is used to call one or more of the test instructions; Connect to the aircraft entertainment display system to be tested; Call at least one test instruction to be used by interacting with the calling option of the interactive operation interface; Acquire the test code and value corresponding to the test instruction to be used, and transmit them to the aircraft entertainment display system to be tested for testing; The test result of the execution of the standby test instruction is received, and the test result is displayed on the interactive operation interface.

2. The test method according to claim 1, wherein The connecting to the aircraft entertainment display system to be monitored comprises: connecting the aircraft entertainment display system to be monitored via a serial port bus; The operation code of capturing the aircraft entertainment display system to be monitored when it is turned on includes: The serial port bus is used to obtain the data stream of the aircraft entertainment display system to be monitored when it is turned on; The running code is obtained by parsing the data stream.

3. The test method according to claim 1, characterized in that 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; Determine the fault level corresponding to the aircraft entertainment display system to be tested according to the test result and the fault judgment threshold table, and determine 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 newness and oldness level corresponding to the aircraft entertainment display system to be tested according to the model and service life of the aircraft entertainment display system to be tested, and determining the weight value of the second influencing factor according to the newness and oldness level and the influencing factor weight table; According to the weight value of the first influencing factor and the weight value of the second influencing factor, it is determined whether the aircraft entertainment display system to be tested needs to be repaired.

4. The test method according to claim 3, characterized in that The fault determination threshold table includes: a threshold corresponding to each fault level; The step of judging the fault level of the aircraft entertainment display system to be tested according to the test result and the fault judgment 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.

5. The testing method according to claim 1, wherein The calling option also includes: a calling sub-option, wherein the calling sub-option is used to call one of the test instructions; The calling 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 calling sub-options by interacting with the calling option of the interactive operation interface; One of the waiting test instructions is called according to the selected calling sub-option.

6. 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; A code capture module, used to capture the running code of the aircraft entertainment display system to be monitored when it is turned on; A code extraction module, used for inputting extraction instructions 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 the 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, used to encapsulate 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 which is used to call one or more of the test instructions; The second interface is used to connect to the entertainment display system of the aircraft to be tested; A calling test module, used for calling 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 is used to acquire the test code and value assignment corresponding to the test instruction to be used, and transmit the test code and value assignment to the aircraft entertainment display system to be tested through 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.

7. The test system according to claim 6, characterized in that, The first interface is a serial bus; The code capture module captures the running code of the aircraft entertainment display system to be monitored when it is turned on, specifically including: Receiving a data stream of the aircraft entertainment display system to be monitored when it is turned on, obtained by the serial port bus; The running code is obtained by parsing the data stream.

8. The test system according to claim 6, characterized in that, The system further comprises: A weight table module is used to establish 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; a fault determination module, configured to determine the fault level corresponding to the aircraft entertainment display system to be tested according to the test result and the fault determination threshold table, and to determine the weight value of the first influencing factor according to the fault level and the influencing factor weight table; A newness and oldness determination module is used to determine the model and service life of the aircraft entertainment display system to be tested, determine the newness and oldness level corresponding to the aircraft entertainment display system to be tested according to the model and service life of the aircraft entertainment display system to be tested, and determine the weight value of the second impact factor according to the newness and oldness level 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 according to the weight value of the first influencing factor and the weight value of the second influencing factor.

9. The test system according to claim 8, wherein 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.

10. The test system according to claim 6, wherein The calling option also includes: a calling sub-option, wherein the calling sub-option is used to call one of the test instructions; The calling test module calls at least one test instruction to be used by interacting with the calling option of the interactive operation interface, specifically including: Selecting one of the calling sub-options by interacting with the calling option of the interactive operation interface; One of the waiting test instructions is called according to the selected calling sub-option.

Images