An aircraft test management system and method

Abstract

The application discloses an airplane test management system and method, which is connected with an airplane test system, and the airplane test system comprises an anti-skid control box test device of a target airplane; the airplane test management system comprises a state configuration module, a state detection module and a post-processing module; the state configuration module is used for configuring initial test parameters of the anti-skid control box test device, and the initial test parameters are used for the anti-skid control box test device to perform test based on the initial test parameters; the state detection module is used for detecting and displaying test process parameters and test results fed back by the anti-skid control box test device in a test process; and the post-processing module is used for saving the test process parameters and the test results, and performing analysis on the test process parameters and the test results to obtain post-processing results. In this way, the anti-skid control box test device can be comprehensively managed in a systematic manner, the test efficiency is improved, and the research and development and optimization of the anti-skid control box are facilitated.

Description

Technical Field

[0001] This application relates to the field of testing technology, and in particular to an aircraft test management system and method. Background Technology

[0002] In an aircraft landing gear system, the anti-skid control box is a critical component ensuring safe landing and takeoff. Its key function is to control the braking system during landing or takeoff to prevent wheel slippage or lockup, thus ensuring a safe landing and takeoff. Therefore, a testing program for the anti-skid control box is particularly important.

[0003] Currently, testing of anti-skid control boxes typically relies on dedicated hardware testing equipment. This equipment can simulate wheel speed, brake signals, and even fault conditions to verify the basic functions and fault response capabilities of the control box. Furthermore, the proposed improvements at the control strategy level aim to optimize the control logic of the anti-skid system under specific operating conditions (such as low-speed cornering) to prevent brake failure.

[0004] However, existing testing solutions have significant limitations. While hardware testers can perform functional verification, the testing process lacks systematic and comprehensive management. The configuration of test parameters, monitoring of the testing process, and recording and analysis of test data are often independent processes, relying on manual operation and judgment, resulting in low testing efficiency and difficulty in ensuring consistency and repeatability. Furthermore, faced with massive amounts of test data, there is a lack of effective tools for in-depth analysis and post-processing, failing to fully extract data value to support performance optimization and fault diagnosis of the anti-slip control box.

[0005] In practical applications, there is no systematic management scheme for testing anti-slip control boxes. Therefore, it is not convenient to comprehensively manage the testing process of anti-slip control boxes, resulting in low testing efficiency. Summary of the Invention

[0006] This application provides an aircraft test management system and method to facilitate comprehensive management of the testing process of the anti-skid control box and improve testing efficiency.

[0007] In a first aspect, embodiments of this application provide an aircraft test management system, characterized in that the aircraft test management system is connected to an aircraft test system, and the flight test system includes an anti-skid control box test device for a target aircraft; The aircraft test management system includes: a status configuration module, a status detection module, and a post-processing module; The status configuration module is used to configure the initial test parameters of the anti-slip control box testing device, and the initial test parameters are used by the anti-slip control box testing device to perform tests based on the initial test parameters. The status detection module is used to detect and display the test process parameters and test results fed back by the anti-slip control box test device during the test process; The post-processing module is used to save the test process parameters and the test results, and to analyze the test process parameters and the test results to obtain the post-processing results.

[0008] Optionally, the state configuration module specifically includes a model configuration unit and a working condition configuration unit; The model configuration unit is used to configure the model parameters corresponding to the anti-slip control box testing device; The working condition configuration unit is used to configure the working condition parameters, initial state parameters and simulation mode corresponding to the anti-slip control box test device.

[0009] Optionally, the aircraft test management system further includes: a fault handling module; The fault handling module is used to configure the simulated fault information of the anti-slip control box testing device, inject the simulated fault information into the anti-slip control box testing device, and display the fault display results of the anti-slip control box testing device in response to the simulated fault information.

[0010] Optionally, the anti-slip control box testing device is used to perform tests based on the initial test parameters using GCAir software; The aircraft test management system also includes: an automatic test module; The automatic testing module is used to import the project built by the GCAir software into the automated testing tool TestManager, configure automatic testing parameters through TestManager, perform batch testing, and obtain batch test reports.

[0011] Optionally, the post-processing module is specifically used for: Obtain analysis requirements information; Based on the analysis requirements analysis, the test process parameters and the test results are analyzed to obtain the post-processing results, which are matched with the analysis requirements information.

[0012] Secondly, this application provides an aircraft test management method, which is applied to any implementation of the aircraft test management system described in the first aspect above. The aircraft test management system is connected to the aircraft test system. The flight test system includes an anti-skid control box test device for the target aircraft. The aircraft test management system includes: a status configuration module, a status detection module, and a post-processing module. The method includes: The initial test parameters of the anti-slip control box testing device are configured through the state configuration module. The initial test parameters are used by the anti-slip control box testing device to perform tests based on the initial test parameters. The status detection module detects and displays the test process parameters and test results fed back by the anti-slip control box testing device during the test. The post-processing module saves the test process parameters and the test results, and analyzes the test process parameters and the test results to obtain the post-processing results.

[0013] Optionally, the state configuration module specifically includes a model configuration unit and a working condition configuration unit; The initial test parameters of the anti-slip control box test device are configured through the state configuration module, including: Configure the model parameters corresponding to the anti-slip control box testing device through the model configuration unit; The working condition configuration unit configures the working condition parameters, initial state parameters, and simulation mode of the anti-slip control box test device.

[0014] Optionally, the aircraft test management system further includes: a fault handling module; The method further includes: The fault handling module configures the simulated fault information of the anti-slip control box testing device, injects the simulated fault information into the anti-slip control box testing device, and displays the fault display results of the anti-slip control box testing device in response to the simulated fault information.

[0015] Optionally, the anti-slip control box testing device is used to perform tests based on the initial test parameters using GCAir software; The aircraft test management system also includes: an automatic test module; The method further includes: The automated testing module imports the project built by the GCAir software into the automated testing tool TestManager. TestManager is then used to configure automated testing parameters and perform batch testing to obtain a batch test report.

[0016] Optionally, the post-processing module analyzes the test process parameters and the test results to obtain post-processing results, including: Obtain analysis requirements information; Based on the analysis requirements analysis, the test process parameters and the test results are analyzed to obtain the post-processing results, which are matched with the analysis requirements information.

[0017] As can be seen from the above technical solutions, the embodiments of this application have the following advantages: This invention constructs a complete closed-loop test management system by integrating multiple modules, including status configuration, real-time monitoring, fault injection, automated testing, and data post-processing. This overcomes the problems of fragmented testing processes, reliance on manual operation, and low efficiency in existing technologies, achieving unified and efficient management of the entire testing process for anti-slip control boxes.

[0018] The invention's unique fault handling module allows for the proactive injection of simulated faults into the system, thereby comprehensively testing the fault detection and handling capabilities of the anti-slip control box in a safe and controllable environment. This provides a powerful means to discover potential design flaws and verify system robustness, which is difficult to achieve with traditional functional testing.

[0019] The post-processing module of this invention can perform customized and in-depth analysis of massive amounts of test process parameters and results, transforming raw data into intuitive and effective post-processing results (such as performance reports, trend analyses, etc.). This provides precise data support for R&D personnel to optimize control algorithms and improve product design, realizing data-driven R&D and optimization.

[0020] In this embodiment, an aircraft test management system can be provided, which is connected to an aircraft test system, and the flight test system includes an anti-skid control box test device for a target aircraft. Accordingly, the aircraft test management system includes: a status configuration module, a status detection module, and a post-processing module; the status configuration module is used to configure initial test parameters for the anti-skid control box test device, which are used by the anti-skid control box test device to perform tests based on these initial test parameters; the status detection module is used to detect and display the test process parameters and test results fed back by the anti-skid control box test device during the test; the post-processing module is used to save the test process parameters and test results, and analyze the test process parameters and test results to obtain post-processing results.

[0021] It is evident that the communication connection between the aircraft test management system and the aircraft test system enables data exchange, allowing the aircraft test management system to manage the anti-skid control box test device within the aircraft test system. Specifically, through the cooperation of the status configuration module, status detection module, and post-processing module, initial test parameters can be configured for the anti-skid control box test device before testing. During testing, the test process parameters and results fed back by the anti-skid control box test device can be detected and displayed. Furthermore, secondary analysis of the test process parameters and results can be performed to obtain post-processing results. This systematic approach allows for comprehensive management of the anti-skid control box test device, improving testing efficiency and contributing to the research and optimization of the anti-skid control box.

[0022] In summary, this invention not only addresses the pain point of lacking a systematic integrated platform in the testing and management of anti-slip control boxes, but also significantly improves testing efficiency, depth, and data value through automation, intelligence, and in-depth analysis. This has important positive significance for accelerating the research and development process of aircraft braking systems and improving product quality and reliability. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the structure of an aircraft test management system provided in an embodiment of this application; Figure 2a A schematic diagram of a display page for an aircraft test management system provided in an embodiment of this application; Figure 2b A schematic diagram of a display page for a status configuration module provided in an embodiment of this application; Figure 2c A schematic diagram of a display page for a fault handling module provided in an embodiment of this application; Figure 2d A schematic diagram of a display page for a post-processing module provided in an embodiment of this application; Figure 3 This is a schematic diagram of the structure of an aircraft testing system provided in an embodiment of this application; Figure 4 A flowchart illustrating an aircraft test management method provided in this application embodiment. Detailed Implementation

[0024] As mentioned earlier, in practical applications, there is no systematic management scheme for testing anti-slip control boxes. Therefore, it is not convenient to comprehensively manage the testing process of anti-slip control boxes, resulting in low testing efficiency.

[0025] Based on this, to solve the above problems, embodiments of this application provide an aircraft test management system connected to an aircraft test system, wherein the flight test system includes an anti-skid control box test device for a target aircraft. Accordingly, the aircraft test management system includes: a status configuration module, a status detection module, and a post-processing module; the status configuration module is used to configure initial test parameters for the anti-skid control box test device, which are used by the anti-skid control box test device to perform tests based on these initial test parameters; the status detection module is used to detect and display the test process parameters and test results fed back by the anti-skid control box test device during the test; the post-processing module is used to save the test process parameters and test results, and analyze the test process parameters and test results to obtain post-processing results.

[0026] It is evident that the communication connection between the aircraft test management system and the aircraft test system enables data exchange, allowing the aircraft test management system to manage the anti-skid control box test device within the aircraft test system. Specifically, through the cooperation of the status configuration module, status detection module, and post-processing module, initial test parameters can be configured for the anti-skid control box test device before testing. During testing, the test process parameters and results fed back by the anti-skid control box test device can be detected and displayed. Furthermore, secondary analysis of the test process parameters and results can be performed to obtain post-processing results. This systematic approach allows for comprehensive management of the anti-skid control box test device, improving testing efficiency and contributing to the research and optimization of the anti-skid control box.

[0027] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0028] Figure 1 This is a schematic diagram of the structure of an aircraft test management system provided in an embodiment of this application. (Combined with...) Figure 1 As shown in the embodiment of this application, the flight test management system is connected to the aircraft test system, wherein the flight test system includes an anti-skid control box test device for the target aircraft. For a detailed description of the flight test system, please refer to the following embodiments, which will not be elaborated upon here.

[0029] Accordingly, the aircraft test management system may include: a status configuration module, a status detection module, and a post-processing module.

[0030] The status configuration module is used to configure the initial test parameters of the anti-slip control box test device. The initial test parameters are used by the anti-slip control box test device to perform tests based on the initial test parameters.

[0031] The status detection module is used to detect and display the test process parameters and test results fed back by the anti-slip control box test device during the test.

[0032] The post-processing module is used to save the test process parameters and test results, and to analyze the test process parameters and test results to obtain the post-processing results.

[0033] The initial test parameters of the anti-slip control box test device can be used to indicate the initial test status of the device, such as aircraft mass, takeoff airport, or inability to fill in information. For ease of understanding, a possible implementation method is described below.

[0034] As one possible implementation, the aforementioned state configuration module specifically includes a model configuration unit and a working condition configuration unit. The model configuration unit is used to configure the model parameters corresponding to the anti-slip control box test device; the working condition configuration unit is used to configure the working condition parameters, initial state parameters, and simulation mode corresponding to the anti-slip control box test device. In this way, the state configuration module allows for comprehensive and effective configuration of all initial test parameters of the anti-slip control box test device, facilitating subsequent testing based on these initial test parameters.

[0035] Combination Figure 2a As shown, embodiments of this application can provide a display page for an aircraft test management system. This display page may include controls corresponding to the status configuration module (i.e., system initial status configuration), controls corresponding to the status detection module (i.e., system status monitoring), controls corresponding to the fault handling module (i.e., system faults), controls corresponding to the post-processing module (i.e., system simulation post-processing), and controls corresponding to the automatic testing module (i.e., automatic test testing).

[0036] Furthermore, combined Figure 2b As shown, the state configuration module can further include controls and menu pages corresponding to the model configuration unit and the operating condition configuration unit, respectively. The menu page corresponding to the model configuration unit allows configuration of parameters for various simulation models, such as aircraft type, landing gear structure configuration, and brake disc model model, to perform corresponding anti-skid control box tests. The menu page corresponding to the operating condition configuration unit allows configuration of the target aircraft's operating condition parameters, initial state parameters, and simulation modes under different operating conditions. Initial state parameters include, for example, initial state configurations for takeoff, cruise, landing, and taxiing. Simulation modes can include three types: fully virtual simulation, semi-physical simulation (virtual model + simulator + control box), and virtual model + simulator simulation.

[0037] In addition, the aircraft test management system also includes a fault handling module. This module is used to configure simulated fault information for the anti-skid control box test device, inject simulated fault information into the test device, and display the fault display results of the test device in response to the simulated fault information. This provides a fault environment for the anti-skid control box test device, facilitating the testing of its relevant performance under fault conditions.

[0038] Accordingly, combined Figure 2cAs shown, the fault handling module may further include controls and menu pages corresponding to a fault triggering unit, a fault display unit, and a fault recording unit, respectively. The menu page corresponding to the fault triggering unit allows selection of various faults, the menu page corresponding to the fault display unit provides a visual representation of various faults, and the menu page corresponding to the fault recording unit records the fault status.

[0039] Furthermore, in this embodiment, after the anti-slip control box testing device receives the configured initial test parameters, it can perform tests based on the initial test parameters using GCAir software. Accordingly, in this aircraft test management system, in addition to using GCAir engineering to test the anti-slip control box testing device, batch testing can also be achieved.

[0040] Specifically, the aircraft test management system may also include an automated testing module. This module can import projects built with GCAir software into the automated testing tool TestManager. TestManager allows for the configuration of automated testing parameters and the execution of batch tests, generating batch test reports. In other words, leveraging TestManager's powerful task scheduling capabilities, imported GCAir projects can be tested in batches, fully utilizing system resources, significantly shortening the overall testing cycle, improving testing efficiency, quickly obtaining test results, and promptly identifying potential problems.

[0041] Furthermore, the aforementioned post-processing module can be specifically used to: acquire analysis requirement information; analyze test process parameters and test results based on the analysis requirement analysis to obtain post-processing results, which are then matched with the analysis requirement information. In this way, the post-processing results can accurately correspond to specific analysis requirements, meeting the expectations and requirements of project stakeholders for test result analysis, and providing strong support for software quality assurance and continuous improvement.

[0042] Accordingly, combined Figure 2d As shown, the post-processing module may further include controls and menu pages corresponding to the braking efficiency unit and the data management unit, respectively. The braking efficiency unit can select a braking efficiency data source and calculate the braking efficiency based on the data source; the data management unit can manage the test process parameters and test results obtained above.

[0043] As can be seen from the above-mentioned content regarding the flight test management system, this application embodiment can provide an aircraft test management system connected to an aircraft test system, and the flight test system includes an anti-skid control box test device for a target aircraft. Accordingly, the aircraft test management system includes: a status configuration module, a status detection module, and a post-processing module; the status configuration module is used to configure the initial test parameters of the anti-skid control box test device, which are used by the anti-skid control box test device to perform tests based on the initial test parameters; the status detection module is used to detect and display the test process parameters and test results fed back by the anti-skid control box test device during the test; the post-processing module is used to save the test process parameters and test results, and analyze the test process parameters and test results to obtain post-processing results.

[0044] It is evident that the communication connection between the aircraft test management system and the aircraft test system enables data exchange, allowing the aircraft test management system to manage the anti-skid control box test device within the aircraft test system. Specifically, through the cooperation of the status configuration module, status detection module, and post-processing module, initial test parameters can be configured for the anti-skid control box test device before testing. During testing, the test process parameters and results fed back by the anti-skid control box test device can be detected and displayed. Furthermore, secondary analysis of the test process parameters and results can be performed to obtain post-processing results. This systematic approach allows for comprehensive management of the anti-skid control box test device, improving testing efficiency and contributing to the research and optimization of the anti-skid control box.

[0045] Furthermore, to facilitate understanding of the specific implementation of this solution, a structural schematic diagram of an aircraft testing system is provided below in conjunction with the accompanying drawings.

[0046] Figure 3 This is a schematic diagram of the structure of an aircraft testing system provided in an embodiment of this application. (Combined with...) Figure 3 As shown in the embodiments of this application, the flight test system may include: a human-machine interface device and an anti-skid control box testing device for the target aircraft. The anti-skid control box testing device includes a virtual model of the target aircraft's braking system. The anti-skid control box testing device and the human-machine interface device are communicatively connected.

[0047] Accordingly, the human-computer interaction device can be used to acquire user operation commands and send them to the anti-slip control box testing device. The user operation commands refer to the operation commands issued by the user through the human-computer interaction device.

[0048] The anti-slip control box testing device can be used to determine the virtual control commands of the target aircraft based on user operation commands and virtual models; execute the virtual control commands to obtain operational feedback results; and send the operational feedback results to the human-machine interaction device.

[0049] The virtual model refers to a model used to simulate some of the real hardware of the target aircraft, such as a virtual model integrating sub-models of aircraft dynamics, landing gear, and hydraulic braking systems. Based on this, the anti-skid control box testing device can perform simulations using the aforementioned user operation commands and the virtual model to obtain virtual control commands for the target aircraft. These virtual control commands are used to control the anti-skid control box testing device to simulate the target aircraft's operation. Thus, operational feedback results can be obtained after executing these virtual control commands.

[0050] Correspondingly, the human-computer interaction device can also be used to output operational feedback results. In this way, users can perceive the simulated flight process of the target in a timely and convenient manner through the human-computer interaction device, thereby providing users with a realistic flight experience and restoring the user's real flight environment as much as possible.

[0051] Additionally, it should be noted that in this embodiment, the aircraft testing system may further include a reflective memory network. Both the human-machine interface device and the anti-slip control box testing device can communicate via the reflective memory network. This allows the user to directly operate the anti-slip control box testing device through the peripheral device, i.e., the human-machine interface device, to perform testing and return relevant information to the human-machine interface device, thus completing the testing loop.

[0052] Furthermore, the aircraft testing system may also include a host computer ( Figure 3 (Not shown), the host computer is communicatively connected to the anti-skid control box testing device. This host computer can be used to integrate multiple virtual sub-models of the target aircraft, obtain a virtual model, and send the virtual model to the anti-skid control box testing device.

[0053] Accordingly, the aforementioned anti-slip control box testing device may further include: a lower-level computer system and an anti-slip control box connected to each other. The lower-level computer system can be used to receive a virtual model from a higher-level computer; based on user operation commands, it uses the virtual model to perform real-time simulation to obtain virtual operating data, and sends the virtual operating data to the anti-slip control box. In practical applications, this lower-level computer system can be a real-time simulation system.

[0054] The anti-slip control box, as the actual hardware of the target aircraft, can be used to generate virtual control commands based on virtual operation data; execute virtual control commands using the virtual model to obtain operation feedback results, and send the operation feedback results to the human-machine interaction device and the aforementioned virtual model.

[0055] In practical implementation, the aforementioned virtual sub-models may include: an aircraft dynamics sub-model, a landing gear sub-model, and a hydraulic braking system sub-model. Furthermore, the aforementioned virtual operational data includes dynamic simulation data of the target aircraft, landing gear simulation data, and hydraulic braking simulation data.

[0056] Accordingly, the aircraft dynamics sub-model can be used to perform simulations based on control surface commands in user operation instructions, generate dynamic simulation data, and send the dynamic simulation data to the landing gear sub-model. Control surface commands refer to the operation commands sent by the user to the control surfaces of the target aircraft via the human-machine interface. Based on these control surface commands, the aircraft dynamics sub-model can adjust parameters such as the target aircraft's position, attitude, or speed, obtaining the corresponding adjusted parameters as dynamic simulation data.

[0057] The landing gear sub-model is used to perform simulations based on dynamic simulation data and generate landing gear simulation data. Specifically, the landing gear sub-model can generate parameters such as the landing gear's attitude, wheel speed, or wheel load as landing gear simulation data based on the aforementioned dynamic simulation data.

[0058] The hydraulic braking system sub-model is used for simulation based on pedal commands from user operation instructions, generating hydraulic braking simulation data. The pedal command refers to the user's operation command for the target aircraft's brake pedal sent through the human-machine interface. Based on this pedal command, the hydraulic braking system sub-model can perform braking control and generate data such as hydraulic valve electrical signals as hydraulic braking simulation data.

[0059] In this way, the integrated virtual model is transmitted from the host computer to the slave computer system for real-time simulation. The human-computer interaction device also transmits user operation commands to the slave computer system, which can then use the virtual model for simulation and transmit the resulting variables to the physical anti-slip control box. The physical anti-slip control box receives the information from the virtual model, processes it accordingly, and then transmits the processing results back to the virtual model in the slave computer system for execution, thus forming a complete computational path between the virtual model and the physical anti-slip control box. Furthermore, the operational feedback results obtained after execution can be fed back to the human-computer interaction device, allowing users to perceive information such as sound, visual, aircraft position, and attitude.

[0060] As can be seen from the above-mentioned content regarding the flight test system, in this embodiment, the aircraft test system may include a human-machine interface device and a target aircraft anti-skid control box test device. The anti-skid control box test device includes a virtual model of the target aircraft's braking system, and the anti-skid control box test device and the human-machine interface device are communicatively connected. Accordingly, the human-machine interface device can acquire user operation commands and send these commands to the anti-skid control box test device. The anti-skid control box test device can then determine virtual control commands for the target aircraft based on the user operation commands and the virtual model; execute the virtual control commands to obtain operational feedback results; and send the operational feedback results to the human-machine interface device. Finally, the human-machine interface device can also output the operational feedback results. Therefore, the human-machine interface device can interact with the user, acquire user operation commands, and output operational feedback results to the user, thereby providing the user with a realistic flight experience during use and recreating the user's actual flight environment as closely as possible. Furthermore, the human-machine interface device can transmit user operation commands to the anti-skid control box testing device, which then operates based on these commands, providing a realistic testing environment. In other words, by integrating the human-machine interface device and the anti-skid control box testing device into the aircraft testing system, a realistic flight environment can be provided to users, while simultaneously enabling performance testing of the target aircraft's anti-skid control box. This improves the accuracy of the test results and contributes to the research and optimization of the target aircraft's anti-skid control box.

[0061] Figure 4 This is a flowchart illustrating an aircraft test management method provided in an embodiment of this application. (In conjunction with...) Figure 4 As shown, the aircraft test management method provided in this application embodiment uses the aircraft test management system in the above embodiment as the execution subject to describe the specific implementation of the scheme. The aircraft test management system can be connected to an aircraft test system, which includes an anti-skid control box test device for the target aircraft. The aircraft test management system includes a status configuration module, a status detection module, and a post-processing module. Accordingly, the aircraft test management method may include the following steps S401-S403.

[0062] S401: Configure the initial test parameters of the anti-slip control box testing device through the status configuration module. The initial test parameters are used by the anti-slip control box testing device to perform tests based on the initial test parameters.

[0063] S402: The status detection module detects and displays the test process parameters and test results fed back by the anti-slip control box test device during the test.

[0064] S403: The status detection module detects and displays the test process parameters and test results fed back by the anti-slip control box test device during the test.

[0065] Optionally, the state configuration module specifically includes a model configuration unit and a working condition configuration unit; The initial test parameters of the anti-slip control box test device are configured through the state configuration module, including: Configure the model parameters corresponding to the anti-slip control box testing device through the model configuration unit; The working condition configuration unit configures the working condition parameters, initial state parameters, and simulation mode of the anti-slip control box test device.

[0066] Optionally, the aircraft test management system further includes: a fault handling module; The method further includes: The fault handling module configures the simulated fault information of the anti-slip control box testing device, injects the simulated fault information into the anti-slip control box testing device, and displays the fault display results of the anti-slip control box testing device in response to the simulated fault information.

[0067] Optionally, the anti-slip control box testing device is used to perform tests based on the initial test parameters using GCAir software; The aircraft test management system also includes: an automatic test module; The method further includes: The automated testing module imports the project built by the GCAir software into the automated testing tool TestManager. TestManager is then used to configure automated testing parameters and perform batch testing to obtain a batch test report.

[0068] Optionally, the post-processing module analyzes the test process parameters and the test results to obtain post-processing results, including: Obtain analysis requirements information; Based on the analysis requirements analysis, the test process parameters and the test results are analyzed to obtain the post-processing results, which are matched with the analysis requirements information.

[0069] Furthermore, embodiments of this application also provide an electronic device, including: a processor, a memory, and a system bus; The processor and the memory are connected via the system bus; The memory is used to store one or more programs, the one or more programs including instructions that, when executed by the processor, cause the processor to perform any of the implementation steps of the above-described aircraft testing method.

[0070] Furthermore, embodiments of this application also provide a computer-readable storage medium storing instructions that, when executed on an electronic device, cause any of the above-described steps of the aircraft testing method to be implemented.

[0071] As can be seen from the above description of the embodiments, those skilled in the art can clearly understand that all or part of the steps in the methods of the above embodiments can be implemented by means of software plus necessary general-purpose hardware platforms. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, a server, or a network communication device such as a media gateway, etc.) to execute the methods described in various embodiments or some parts of the embodiments of this application. It should be noted that the various embodiments in this specification are described in a progressive manner, and each embodiment focuses on describing the differences from other embodiments. The same or similar parts between the various embodiments can be referred to mutually.

[0072] The system disclosed in the embodiments is described in a relatively simple manner because it corresponds to the method disclosed in the embodiments. For relevant details, please refer to the method section.

[0073] It should also be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0074] The above description of the disclosed embodiments enables those skilled in the art to make or use this application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of this application. Therefore, this application is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An aircraft test management system, characterized in that, The aircraft test management system is connected to the aircraft test system, which includes a test device for the anti-skid control box of the target aircraft. The aircraft test management system includes: a status configuration module, a status detection module, and a post-processing module; The status configuration module is used to configure the initial test parameters of the anti-slip control box testing device, and the initial test parameters are used by the anti-slip control box testing device to perform tests based on the initial test parameters. The state detection module is used to detect and display the test process parameters and test results fed back by the anti-slip control box test device during the test; the state configuration module specifically includes a model configuration unit and a working condition configuration unit; the model configuration unit is used to configure the model parameters corresponding to the anti-slip control box test device; the working condition configuration unit is used to configure the working condition parameters, initial state parameters, and simulation mode corresponding to the anti-slip control box test device; the simulation mode includes full virtual simulation, semi-physical simulation, and virtual model and simulator simulation; The post-processing module is used to save the test process parameters and the test results, and to analyze the test process parameters and the test results to obtain the post-processing results; The post-processing module is specifically used for: Obtain analysis requirements information; The test process parameters and test results are analyzed based on the analysis requirements information to obtain the post-processing results, which are matched with the analysis requirements information.

2. The aircraft test management system according to claim 1, characterized in that, The aircraft test management system also includes: a fault handling module; The fault handling module is used to configure the simulated fault information of the anti-slip control box testing device, inject the simulated fault information into the anti-slip control box testing device, and display the fault display results of the anti-slip control box testing device in response to the simulated fault information.

3. The aircraft test management system according to claim 1, characterized in that, The anti-slip control box testing device is used to perform tests based on the initial test parameters using GCAir software; The aircraft test management system also includes: an automatic test module; The automatic testing module is used to import the project built by the GCAir software into the automated testing tool TestManager, configure automatic testing parameters through TestManager, perform batch testing, and obtain batch test reports.

4. An aircraft test management method, characterized in that, The aircraft test management system is applied to any one of claims 1 to 3, wherein the aircraft test management system is connected to the aircraft test system, the aircraft test system includes an anti-skid control box test device for the target aircraft, and the aircraft test management system includes: a status configuration module, a status detection module, and a post-processing module. The method includes: The initial test parameters of the anti-slip control box testing device are configured through the state configuration module. The initial test parameters are used by the anti-slip control box testing device to perform tests based on the initial test parameters. The status detection module detects and displays the test process parameters and test results fed back by the anti-slip control box testing device during the test. The post-processing module saves the test process parameters and the test results, and analyzes the test process parameters and the test results to obtain the post-processing results.

5. The aircraft test management method according to claim 4, characterized in that, The state configuration module specifically includes a model configuration unit and a working condition configuration unit; The initial test parameters of the anti-slip control box test device are configured through the status configuration module, including: Configure the model parameters corresponding to the anti-slip control box testing device through the model configuration unit; The working condition configuration unit configures the working condition parameters, initial state parameters, and simulation mode of the anti-slip control box test device.

6. The aircraft test management method according to claim 5, characterized in that, The aircraft test management system also includes: a fault handling module; The method further includes: The fault handling module configures the simulated fault information of the anti-slip control box testing device, injects the simulated fault information into the anti-slip control box testing device, and displays the fault display results of the anti-slip control box testing device in response to the simulated fault information.

7. The aircraft test management method according to claim 4, characterized in that, The anti-slip control box testing device is used to perform tests based on the initial test parameters using GCAir software; The aircraft test management system also includes: an automatic test module; The method further includes: The automated testing module imports the project built by the GCAir software into the automated testing tool TestManager. TestManager is then used to configure automated testing parameters and perform batch testing to obtain a batch test report.

8. The aircraft test management method according to claim 4, characterized in that, The post-processing module analyzes the test process parameters and the test results to obtain post-processing results, including: Obtain analysis requirements information; Based on the analysis requirements analysis, the test process parameters and the test results are analyzed to obtain the post-processing results, which are matched with the analysis requirements information.

Images