A data stimulation method for modeling simulation

Abstract

The application discloses a kind of data excitation methods of modeling simulation, it is related to aviation cabin flat display technical field, solve the problem that current random excitation generation technique uses and can not generate a large number of repeated test excitation according to the actual situation of the object to be tested Set compatible test excitation scheme, method includes: according to scene number obtains the fault data of aviation cabin flat display system in different scenes to be measured;Analysis obtains the test sequence of aviation cabin flat display system in different scenes to be measured;Construction test package of aviation cabin flat display system in different scenes to be measured;Test analysis is carried out to aviation cabin flat display system in different scenes to be measured, verify the function of aviation cabin flat display system in different scenes to be measured, the application can avoid a large number of repeated test excitation when excitation test, to improve verification efficiency, while test mode also set compatible test excitation scheme with the object to be tested according to actual situation.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of aviation cockpit flat display technology, and particularly relates to a modeling simulation data excitation method. BACKGROUND

[0002] The aviation cockpit flat display system is a technology integrating display and control systems, and is mainly used for functions such as real-time monitoring, data acquisition, human-computer interaction, and the like, and is mainly applied to industrial automation, aerospace, military application, transportation and the like. When the aviation cockpit flat display system data is simulated and modeled, the modeling simulation data excitation generation technology is usually used. The data excitation generation technology is to simulate the real device sending instructions or data to the measured device (aviation cockpit flat display system), and to analyze the response of the measured device (aviation cockpit flat display system) to verify whether the function of the measured device (aviation cockpit flat display system) is normal.

[0003] At present, the data excitation generation technology in simulation verification mainly includes directional excitation generation technology and random excitation generation technology. The random excitation generation technology is to generate verification excitation in a random manner through a program. Although this method can reduce the human workload and reduce the error rate, a large number of repeated test excitations are generated when the random excitation generation is used, which leads to repeated test excitations and reduces the verification efficiency to a certain extent. Moreover, the test method of the current random excitation generation technology cannot set a test excitation scheme suitable for the measured object according to the actual situation of the measured object.

[0004] Therefore, the application provides a modeling simulation data excitation method. SUMMARY

[0005] The application aims to provide a modeling simulation data excitation method to solve the problems that the current random excitation generation technology generates verification excitation in a random manner through a program, which can reduce the human workload and reduce the error rate, but a large number of repeated test excitations are generated when the random excitation generation is used, which leads to repeated test excitations and reduces the verification efficiency to a certain extent, and the test method of the current random excitation generation technology cannot set a test excitation scheme suitable for the measured object according to the actual situation of the measured object.

[0006] The application can be achieved by the following technical scheme.

[0007] A modeling simulation data excitation method, the method comprising:

[0008] Step S10, obtaining the scene number of the measured scene, and obtaining the fault data of the aviation cockpit flat display system in different measured scenes according to the scene number;

[0009] Step S20, according to the fault data analysis obtained in different test sequence of the aviation cockpit flat display system in the scene to be measured;

[0010] Step S30, according to the historical test list of the same type of aviation cockpit flat display system, the test package of the aviation cockpit flat display system in different scenes to be measured is constructed;

[0011] Step S40, test analysis of the aviation cockpit flat display system in different scenes to be measured by the test package, verify the function of the aviation cockpit flat display system in different scenes to be measured and generate test normal signal or test abnormal signal.

[0012] As a further technical solution of the application, the fault data is the test fault times of the aviation cockpit flat display system in the scene to be measured and the fault maintenance time of each test, and the important coefficient of the scene to be measured.

[0013] As a further technical solution of the application, the step S20 includes the following sub-steps:

[0014] Step S201, obtain the test fault times in different scenes to be measured and the fault maintenance time of each test;

[0015] Step S202, after adding up the fault maintenance time of each test and taking the average, the average fault maintenance time of the scene to be measured is obtained;

[0016] Step S203, then obtain the important coefficient of the scene to be measured;

[0017] Step S204 calculates the test sequence value of the aviation cockpit flat display system in different scenes to be measured;

[0018] Step S205, according to the numerical value of the test sequence value, the descending order is arranged, and the test sequence of the aviation cockpit flat display system is obtained.

[0019] As a further technical solution of the application, the step S30 includes the following sub-steps:

[0020] Step S301, obtain the historical test list of the same type of aviation cockpit flat display system;

[0021] Step S302, according to the historical test list, obtain the test items of the same type of aviation cockpit flat display system in different scenes to be measured and the test data of each group of test items;

[0022] Step S303, extract necessary test items of the aviation cabin flat display system in different to-be-tested scenes in the historical test list, and after extracting the necessary test items, the same test items are summarized into the same set, the number of test items in the set is counted and divided by the number of tests of the aviation cabin flat display system, to obtain the test rate of the test items of the aviation cabin flat display system in different to-be-tested scenes;

[0023] Step S304, compare the test rate with the preset test rate, if the test rate is greater than or equal to the preset test rate, mark the corresponding test item as a to-be-selected test item and enter the next step, otherwise do not perform any operation.

[0024] As a further technical solution of the present application, the test data is test items and test values at the time of testing.

[0025] As a further technical solution of the present application, the step S30 further includes the following sub-steps:

[0026] Step S305, traverse the test values corresponding to the to-be-selected test items, obtain the maximum value and the minimum value in the test values corresponding to the to-be-selected test items, take the minimum value as the left end point of the interval, and take the maximum value as the right end point of the interval, to obtain the standard test value interval of the to-be-selected test items corresponding to the aviation cabin flat display system in different to-be-tested scenes;

[0027] Step S306, similarly, obtain multiple groups of to-be-selected test items and necessary test items, and multiple groups of standard test value intervals corresponding to the to-be-selected test items and the necessary test items;

[0028] Step S307, sort the to-be-selected test items in descending order of test rate, and then combine all the to-be-selected test items and the necessary test items, and all the standard test value intervals corresponding to the to-be-selected test items and the necessary test items to form a test package of the aviation cabin flat display system in different to-be-tested scenes.

[0029] As a further technical solution of the present application, the step S40 includes the following sub-steps:

[0030] Step S401, obtain the test package of the aviation cabin flat display system in different to-be-tested scenes, to obtain the to-be-selected test items and the necessary test items of the aviation cabin flat display system in different to-be-tested scenes, and the standard test value intervals corresponding to the to-be-selected test items and the necessary test items;

[0031] Step S402, test according to the necessary test items, to obtain real-time test values of the aviation cabin flat display system in a to-be-tested scene when the necessary test items are tested;

[0032] Step S403, if the real-time test value does not belong to the standard test value interval, generate a test exception signal.

[0033] If the real-time test value belongs to the standard test value interval, the next necessary test item of the aviation cabin flat display system under the same to-be-tested scene is tested until the necessary test item of the aviation cabin flat display system under the same to-be-tested scene is tested completely.

[0034] Step S404, when all the necessary test items are tested successfully, the optional test item of the aviation cabin flat display system under the same to-be-tested scene is tested, and the real-time test value of the optional test item of the aviation cabin flat display system under the to-be-tested scene is recorded.

[0035] Step S405, if the real-time test value does not belong to the standard test value interval, a test exception signal is generated.

[0036] If the real-time test value belongs to the standard test value interval, the next necessary test item of the aviation cabin flat display system under the same to-be-tested scene is tested.

[0037] Step S406, when all the necessary test items are tested successfully, the aviation cabin flat display system is placed under another to-be-tested scene to test the necessary test item and the optional test item.

[0038] Step S407, when any necessary test item or any optional test item of the aviation cabin flat display system under any to-be-tested scene is tested unsuccessfully, a test exception signal is generated.

[0039] As a further technical scheme of the present application, the method further comprises:

[0040] Step S50, setting a start condition of the to-be-tested item and the necessary test item;

[0041] Step S60, identifying the temporary file, and making the to-be-tested scene to perform the corresponding test item according to the start identifier obtained by the identification.

[0042] As a further technical scheme of the present application, the step S50 comprises the following sub-steps:

[0043] Step S501, obtaining the to-be-tested item and the necessary test item in the test package;

[0044] Step S502, setting a temporary file for the to-be-tested item and the necessary test item, and the temporary file is configured with a corresponding start identifier;

[0045] Step S503, then setting an encryption means for the temporary file.

[0046] As a further technical scheme of the present application, the step S60 comprises the following sub-steps:

[0047] Step S601, the temporary file is decrypted by decryption means, and the start identifier corresponding to the temporary file is obtained by decryption;

[0048] Step S602, the start identifier is compared with the storage identifier in the database;

[0049] Step S603, if the start identifier matches the storage identifier, the test project of the aviation cockpit flat display system in the to-be-tested scene is started;

[0050] Step S604, if the start identifier does not match the storage identifier, no operation is performed.

[0051] In summary, due to the adoption of the above technical solutions, the beneficial effects of the present application are:

[0052] 1、The present application obtains the scene number of the to-be-tested scene, and obtains the test sequence of the aviation cockpit flat display system in different to-be-tested scenes according to fault data analysis, and further constructs the test package of the aviation cockpit flat display system in different to-be-tested scenes according to the historical test list of the same type of aviation cockpit flat display system, finally tests and analyzes the aviation cockpit flat display system in different to-be-tested scenes through the test package, verifies the function of the aviation cockpit flat display system in different to-be-tested scenes, and generates a test normal signal or a test abnormal signal, which can avoid a large number of repeated test excitations during excitation test, thereby improving the verification efficiency, and the test method further sets a test excitation scheme suitable for the to-be-tested object according to the actual situation of the to-be-tested object;

[0053] 2、The present application sets the start condition of the to-be-tested item and the necessary test item, identifies the temporary file, and makes the aviation cockpit flat display system perform the corresponding test item in the to-be-tested scene according to the identified start identifier, which realizes accurate use of the to-be-tested scene excitation test item by setting the start condition, and the test is more accurate and efficient. BRIEF DESCRIPTION OF DRAWINGS

[0054] In order to facilitate those skilled in the art to understand, the present application will be further described below with reference to the drawings.

[0055] Figure 1 The method flowchart of the present application;

[0056] Figure 2 Another method flowchart of the present application;

[0057] Figure 3 The structural schematic diagram of the computer device in the present application. DETAILED DESCRIPTION

[0058] The technical solutions of the present application will be described clearly and completely below in connection with the embodiments. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

[0059] Embodiment 1, please refer to Figure 1 and Figure 2 The technical solution provided by the present application is: a data excitation method for modeling simulation, which is used for simulation test of an aviation cockpit flat display system under different test scenes. In order to facilitate subsequent use, the test scene of the aviation cockpit flat display system that needs to be simulated and tested is a to-be-tested scene, and the method is as follows:

[0060] Step S10, obtain the scene number of the to-be-tested scene, and obtain the fault data of the aviation cockpit flat display system under different to-be-tested scenes according to the scene number;

[0061] The fault data is the test fault number of the aviation cockpit flat display system under the to-be-tested scene, the fault maintenance time of each test, and the important coefficient of the to-be-tested scene. The important coefficient is determined by the use time or use number of the to-be-tested scene of the aviation cockpit flat display system under each test scene. The test scene corresponds to the actual use scene of the aviation cockpit flat display system, that is, when the use time or use number of the aviation cockpit flat display system in a scene is more, the value of the corresponding important coefficient is larger.

[0062] Step S20, obtain the test sequence of the aviation cockpit flat display system under different to-be-tested scenes according to the fault data analysis;

[0063] In this embodiment, the step S20 includes the following sub-steps:

[0064] Step S201, obtain the test fault number Ci under different to-be-tested scenes and the fault maintenance time of each test, and i is the number of the to-be-tested scene;

[0065] Step S202, add up the fault maintenance time of each test to obtain the average fault maintenance time Ti of the to-be-tested scene;

[0066] Step S203, then obtain the important coefficient of the to-be-tested scene, and mark the important coefficient as Xi;

[0067] Step S204, obtain the test sequence value CXi of the aviation cockpit flat display system under different to-be-tested scenes by formula calculation, and the formula is as follows:

[0068] CXi=(Ci / BC+Ti / BT)×Xi, wherein BC is a standard value with the same unit as the test failure number, and BT is a standard value with the same unit as the average failure maintenance time;

[0069] In step S205, the test sequence values are arranged in descending order according to the numerical values, and the test sequence of the aviation cockpit flat display system is obtained.

[0070] In step S30, the test package of the aviation cockpit flat display system under different to-be-tested scenes is constructed according to the historical test list of the same type of aviation cockpit flat display system.

[0071] In this embodiment, the step S30 includes the following sub-steps:

[0072] In step S301, the historical test list of the same type of aviation cockpit flat display system is obtained.

[0073] In step S302, the test items of the same type of aviation cockpit flat display system under different to-be-tested scenes and the test data of each group of test items are obtained according to the historical test list; wherein the test data is the test value of the test item of the aviation cockpit flat display system under different to-be-tested scenes and the test time, for example, the test value is the response time when the test item is the response test item, and it needs to be emphasized that the test value is all reserved after the test is passed, and the test is all eliminated when the test is failed.

[0074] It needs to be specifically explained that the test item can be a response test item, an identification test item, etc.

[0075] In step S303, the necessary test items of the aviation cockpit flat display system under different to-be-tested scenes in the historical test list are extracted, the same test items are summarized into the same set after the necessary test items are extracted, the number of test items in the set is counted and then divided by the test number of the aviation cockpit flat display system, and the test rate of the test items of the aviation cockpit flat display system under different to-be-tested scenes is obtained.

[0076] In step S304, the test rate is compared with the preset test rate, if the test rate is greater than or equal to the preset test rate, the corresponding test item is recorded as a to-be-selected test item and the next step is entered, otherwise no operation is performed.

[0077] In step S305, the test values corresponding to the to-be-selected test items are traversed, the maximum value and the minimum value in the test values corresponding to the to-be-selected test items are obtained, the minimum value is taken as the left end point of the interval, and the maximum value is taken as the right end point of the interval, and the standard test value interval of the to-be-selected test items of the aviation cockpit flat display system under different to-be-tested scenes is obtained.

[0078] Step S306, similarly, a plurality of groups of candidate test items and necessary test items and a plurality of groups of standard test value intervals corresponding to the plurality of groups of candidate test items and necessary test items are obtained;

[0079] Step S307, after sorting the candidate test items in descending order of test rates, a test package of the aviation cockpit flat display system under different test scenes is formed by all the candidate test items and necessary test items and all the standard test value intervals corresponding to the candidate test items and necessary test items;

[0080] If there are candidate test items and necessary test items with the same test rate, the candidate test items and necessary test items are tested synchronously in a concurrent manner.

[0081] Step S40, the aviation cockpit flat display system under different test scenes is tested and analyzed by the test package, the functions of the aviation cockpit flat display system under different test scenes are verified, and a test normal signal or a test abnormal signal is generated;

[0082] In practice, the test package can be sent to the aviation cockpit flat display system by simulating a real device;

[0083] In this embodiment, the step S40 includes the following sub-steps:

[0084] Step S401, a test package of the aviation cockpit flat display system under different test scenes is obtained, candidate test items and necessary test items of the aviation cockpit flat display system under different test scenes are obtained, and standard test value intervals corresponding to the candidate test items and necessary test items are obtained;

[0085] Step S402, the necessary test items are tested, and a real-time test value of the aviation cockpit flat display system under a test scene when the necessary test items are tested is obtained;

[0086] Step S403, if the real-time test value does not belong to the standard test value interval, a test abnormal signal is generated;

[0087] If the real-time test value belongs to the standard test value interval, the next necessary test item of the aviation cockpit flat display system under the same test scene is tested until the necessary test items of the aviation cockpit flat display system under the same test scene are tested;

[0088] Step S404, when all the necessary test items are tested, the candidate test items of the aviation cockpit flat display system under the same test scene are tested, and a real-time test value of the aviation cockpit flat display system under the test scene when the candidate test items are tested is recorded;

[0089] Step S405, if the real-time test value does not belong to the standard test value interval, a test abnormal signal is generated;

[0090] If the real-time test value belongs to the standard test value interval, the next selected test item of the aviation cockpit flat display system under the same to-be-tested scene is tested.

[0091] Step S406, when all the selected test items are tested successfully, the aviation cockpit flat display system is placed in another to-be-tested scene for testing the necessary test items and the selected test items;

[0092] Step S407, when any necessary test item or any selected test item of the aviation cockpit flat display system under any to-be-tested scene fails the test, a test abnormal signal is generated;

[0093] When the necessary test items and the selected test items of the aviation cockpit flat display system under all to-be-tested scenes are tested successfully, a test normal signal is generated.

[0094] After the above technical solution is adopted, the scene number of the to-be-tested scene is acquired, the test sequence of the aviation cockpit flat display system under different to-be-tested scenes is obtained according to the fault data analysis, the test package of the aviation cockpit flat display system under different to-be-tested scenes is constructed according to the historical test list of the same type of aviation cockpit flat display system, and finally the aviation cockpit flat display system under different to-be-tested scenes is tested and analyzed through the test package, the function of the aviation cockpit flat display system under different to-be-tested scenes is verified, and a test normal signal or a test abnormal signal is generated. The scheme can avoid a large number of repeated test excitations during excitation test, thereby improving the verification efficiency. Meanwhile, the test method is also set according to the actual situation of the to-be-tested object, and a test excitation scheme suitable for the to-be-tested object is set.

[0095] As a further scheme of the present application, as shown in Figure 2 The present application further includes the following steps:

[0096] The main purpose of the further scheme is to set the start conditions of the to-be-tested items and the necessary test items when the aviation cockpit flat display system under different to-be-tested scenes is tested and analyzed through the test package, so as to avoid the misstart of other test items and cause the decline of test efficiency.

[0097] Step S50, the start conditions of the to-be-tested items and the necessary test items are set, and the setting process is as follows:

[0098] Step S501, the to-be-tested items and the necessary test items in the test package are acquired;

[0099] Step S502: Set temporary files for both the test item and the necessary test items. The temporary files are configured with corresponding start identifiers. The temporary files are time-sensitive temporary text files, and each test item is set with a corresponding and unique start identifier.

[0100] Step S503, then set an encryption method for the temporary file startup; the encryption method is existing technology, and the existence of the encryption method is to prevent the startup identifier in the temporary file from being tampered with.

[0101] Step S60: Identify the temporary file and use the identified start identifier to enable the aircraft cockpit head-up display system to perform the corresponding test items in the test scenario.

[0102] In this embodiment, step S60 includes the following sub-steps:

[0103] Step S601: Decrypt the temporary file using decryption methods to obtain the startup identifier corresponding to the temporary file;

[0104] Step S602: Compare the startup identifier with the stored identifier in the database;

[0105] Step S603: If the start identifier matches the storage identifier, then start the test item of the aircraft cockpit head-up display system in the test scenario.

[0106] Step S604: If the start identifier and the storage identifier do not match, no operation is performed;

[0107] Among them, the storage identifier is pre-set in the database. When the activation identifier matches the storage identifier, the test method corresponding to the activation test item is used to test and analyze the aircraft cockpit head-up display system in the test scenario.

[0108] After adopting the above technical solution, by setting the start conditions for the test items and necessary test items, and identifying temporary files, the aircraft cockpit head-up display system can perform corresponding test items in the test scenario based on the identified start identifier. This solution achieves accurate activation of test items in the test scenario by setting start conditions, making the test more accurate and efficient.

[0109] In this application, if a corresponding calculation formula appears, the above calculation formula is a dimensionless calculation. The weighting coefficient, proportional coefficient and other coefficients in the formula are set to quantify each parameter to obtain a result value. The size of the weighting coefficient and proportional coefficient is only required to not affect the proportional relationship between the parameter and the result value.

[0110] Example 2: This embodiment of the invention also provides a computer device for running the aforementioned data stimulus method for modeling and simulation; see [link to example].Figure 3 The illustrated embodiment of the present invention provides a structural diagram of a computer device, which includes a memory and a processor. The memory stores one or more computer instructions, which are executed by the processor to implement the aforementioned data stimulation method for modeling and simulation. Specifically, the method involves: obtaining the scenario number of the test scenario; obtaining fault data of the aircraft cockpit head-up display system in different test scenarios based on the scenario number; analyzing the fault data to obtain the test sequence of the aircraft cockpit head-up display system in different test scenarios; constructing a test package for the aircraft cockpit head-up display system in different test scenarios based on a historical test list of similar aircraft cockpit head-up display systems; performing test analysis on the aircraft cockpit head-up display system in different test scenarios using the test package to verify the functionality of the aircraft cockpit head-up display system in different test scenarios and generating normal or abnormal test signals; setting the start conditions for the test items and necessary test items; identifying temporary files and obtaining a start identifier based on the identification to enable the aircraft cockpit head-up display system to perform the corresponding test items in the test scenario;

[0111] Furthermore, Figure 3 The computer device shown also includes a communication bus and a communication interface, with the processor, communication interface, and memory connected via the communication bus;

[0112] The memory may include high-speed random access memory (RAM) or non-volatile memory, such as at least one disk storage device. Communication between this system network element and at least one other network element is achieved through at least one communication interface (wired or wireless), which can use the Internet, wide area network, local area network, metropolitan area network, etc. The communication bus can be an ISA bus, PCI bus, or EISA bus, etc. The communication bus can be divided into address bus, data bus, control bus, etc. For ease of representation, Figure 3 The symbol is represented by only one double-headed arrow, but this does not mean that there is only one communication bus or one type of communication bus.

[0113] The processor may be an integrated circuit chip with signal processing capabilities. In implementation, the steps of the above methods can be completed by integrated logic circuits in the processor's hardware or by software instructions. The processor can be a general-purpose processor, including a Central Processing Unit (CPU), a Network Processor (NP), etc.; it can also be a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), a Field-Programmable Gate Array (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, or discrete hardware components. It can implement or execute the methods, steps, and logic block diagrams disclosed in the embodiments of this invention. The general-purpose processor can be a microprocessor or any conventional processor. The steps of the methods disclosed in the embodiments of this invention can be directly embodied in the execution of a hardware decoding processor, or executed by a combination of hardware and software modules in the decoding processor. The software modules can reside in random access memory, flash memory, read-only memory, programmable read-only memory, electrically erasable programmable memory, registers, or other mature storage media in the art. The storage medium is located in the memory, and the processor reads the information in the memory and, in conjunction with its hardware, completes the steps of the method described in the foregoing embodiments.

[0114] Example 3: This embodiment of the invention also provides a computer storage medium storing computer-executable instructions. When these computer-executable instructions are called and executed by a processor, they cause the processor to implement the aforementioned data stimulus method for modeling and simulation. The method specifically includes: obtaining the scene number of the test scene; obtaining fault data of the aircraft cockpit head-up display system in different test scenes based on the scene number; analyzing the fault data to obtain the test sequence of the aircraft cockpit head-up display system in different test scenes; constructing a test package for the aircraft cockpit head-up display system in different test scenes based on a historical test list of similar aircraft cockpit head-up display systems; performing test analysis on the aircraft cockpit head-up display system in different test scenes using the test package, verifying the functionality of the aircraft cockpit head-up display system in different test scenes, and generating normal or abnormal test signals; setting the start conditions for the test items and necessary test items; identifying temporary files, and using the identified start identifier to enable the aircraft cockpit head-up display system to perform the corresponding test items in the test scene;

[0115] The computer program product of the data stimulation method for modeling and simulation provided in this invention includes a computer storage medium storing program code. The instructions included in the program code can be used to execute the methods in the preceding method embodiments. The methods specifically include: obtaining the scenario number of the scenario under test; obtaining fault data of the aircraft cockpit head-up display system in different scenarios under test based on the scenario number; obtaining the test sequence of the aircraft cockpit head-up display system in different scenarios under test based on the fault data analysis; constructing a test package for the aircraft cockpit head-up display system in different scenarios under test based on the historical test list of similar aircraft cockpit head-up display systems; performing test analysis on the aircraft cockpit head-up display system in different scenarios under test using the test package, verifying the function of the aircraft cockpit head-up display system in different scenarios under test and generating test normal signals or test abnormal signals; setting the start conditions for the test items and necessary test items; identifying temporary files, and using the identified start identifier to enable the aircraft cockpit head-up display system to perform the corresponding test items in the test scenario.

[0116] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working process of the system and / or device described above can be referred to the corresponding process in the foregoing method embodiments, and will not be repeated here.

[0117] Furthermore, in the description of the embodiments of the present invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in the present invention based on the specific circumstances.

[0118] If the aforementioned functions are implemented as software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this invention, essentially, or the part that contributes to the prior art, or a portion of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0119] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A data stimulus method for modeling and simulation, characterized in that, The methods include: Step S10: Obtain the scenario number of the scenario to be tested, and obtain the fault data of the aircraft cockpit head-up display system in different scenarios to be tested based on the scenario number; the fault data includes the number of test failures of the aircraft cockpit head-up display system in the scenario to be tested, the fault repair time during each test, and the importance coefficient of the scenario to be tested; the importance coefficient is determined by the usage time or number of times the aircraft cockpit head-up display system is used in each test scenario. Step S20: Based on the fault data analysis, obtain the test sequence of the aircraft cockpit head-up display system in different test scenarios; Step S20 includes the following sub-steps: Step S201: Obtain the number of test failures and the fault repair time for each test under different test scenarios; Step S202: Sum the fault repair times for each test, take the average value, and obtain the average fault repair time for the test scenario. Step S203, then obtain the importance coefficient of the scene to be tested; Step S204: Calculate the test sequence values ​​of the aircraft cockpit head-up display system in different test scenarios; Step S205: Sort the test sequence values ​​in descending order to obtain the test sequence of the aircraft cockpit head-up display system; Step S30: Based on the historical test list of similar aircraft cockpit head-up display systems, construct test packages for aircraft cockpit head-up display systems under different test scenarios; Step S40: The test package is used to test and analyze the aircraft cockpit head-up display system in different test scenarios to verify the function of the aircraft cockpit head-up display system in different test scenarios and generate normal test signals or abnormal test signals.

2. The data stimulation method for modeling and simulation according to claim 1, characterized in that, Step S30 includes the following sub-steps: Step S301: Obtain a historical test list of similar aircraft cockpit head-up display systems; Step S302: Based on the historical test list, obtain the test items and test data of the same type of aircraft cockpit head-up display system under different test scenarios. Step S303: Extract the necessary test items of the aircraft cockpit head-up display system in different test scenarios from the historical test list. After extracting the necessary test items, group the same test items into the same set. Count the number of test items in the set and divide it by the number of tests of the aircraft cockpit head-up display system to obtain the test rate of the test items of the aircraft cockpit head-up display system in different test scenarios. Step S304: Compare the test rate with the preset test rate. If the test rate is greater than or equal to the preset test rate, the corresponding test item is recorded as a candidate test item and proceeds to the next step; otherwise, no operation is performed.

3. The data stimulation method for modeling and simulation according to claim 2, characterized in that, The test data includes the test items and the test values ​​during the test.

4. The data stimulation method for modeling and simulation according to claim 2, characterized in that, Step S30 further includes the following sub-steps: Step S305: Iterate through and compare the test values ​​corresponding to the selected test items to obtain the maximum and minimum values ​​of the test values ​​corresponding to the selected test items. Use the minimum value as the left endpoint of the interval and the maximum value as the right endpoint of the interval to obtain the standard test value interval corresponding to the selected test items of the aircraft cockpit head-up display system under different test scenarios. Step S306, similarly, yields multiple sets of candidate test items and necessary test items, as well as the standard test value ranges corresponding to the multiple sets of candidate test items and necessary test items. Step S307: After sorting the candidate test items according to the test rate from high to low, all candidate test items and necessary test items, as well as the standard test value ranges corresponding to all candidate test items and necessary test items, are combined to form a test package for the aircraft cockpit head-up display system under different test scenarios.

5. The data stimulation method for modeling and simulation according to claim 4, characterized in that, Step S40 includes the following sub-steps: Step S401: Obtain test packages for the aircraft cockpit head-up display system under different test scenarios, and obtain the optional test items and necessary test items for the aircraft cockpit head-up display system under different test scenarios, as well as the standard test value ranges corresponding to the optional test items and necessary test items. Step S402: Perform tests according to the necessary test items and obtain real-time test values ​​of the aircraft cockpit head-up display system when performing necessary test items in a test scenario. Step S403: If the real-time test value does not fall within the standard test value range, a test anomaly signal is generated. If the real-time test value falls within the standard test value range, then the next necessary test item for the aircraft cockpit head-up display system under the same test scenario will be tested until the necessary test items for the aircraft cockpit head-up display system under the same test scenario are completed. Step S404: After all necessary test items have been tested and passed, the optional test items of the aircraft cockpit head-up display system under the same test scenario are tested, and the real-time test values ​​of the optional test items of the aircraft cockpit head-up display system under the test scenario are recorded. Step S405: If the real-time test value does not fall within the standard test value range, a test anomaly signal is generated. If the real-time test value falls within the standard test value range, then test the next candidate test item for the aircraft cockpit head-up display system under the same test scenario; Step S406: When all the candidate test items have passed the test, the aircraft cockpit head-up display system is placed in another test scenario to test the necessary test items and candidate test items. Step S407: When the aircraft cockpit head-up display system fails any necessary test item or any optional test item in any test scenario, a test anomaly signal is generated.

6. The data stimulation method for modeling and simulation according to claim 1, characterized in that, The method also includes: Step S50: Set the start conditions for the items to be tested and the necessary test items; Step S60: Identify the temporary file and use the identified start identifier to initiate the corresponding test item for the scenario under test.

7. The data stimulation method for modeling and simulation according to claim 6, characterized in that, Step S50 includes the following sub-steps: Step S501: Obtain the test items and necessary test items from the test package; Step S502: Set temporary files for both the project to be tested and the necessary test projects. The temporary files are configured with corresponding startup identifiers. Step S503, then set up encryption methods for the temporary file startup.

8. The data stimulation method for modeling and simulation according to claim 7, characterized in that, Step S60 includes the following sub-steps: Step S601: Decrypt the temporary file using decryption methods to obtain the startup identifier corresponding to the temporary file; Step S602: Compare the startup identifier with the stored identifier in the database; Step S603: If the start identifier matches the storage identifier, then start the test item of the aircraft cockpit head-up display system in the test scenario. In step S604, if the startup identifier and the storage identifier do not match, no operation is performed.

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