Fault processing method, device and equipment of aircraft and storage medium
By obtaining the status parameters of the aircraft, confirming the target correlation parameters and finding false alarms, the problem of high false alarm rate during aircraft operation is solved, and the maintenance efficiency and accuracy of fault reporting is improved.
Patent Information
- Application Number
- CN202510411120.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-02
- Publication Date
- 2025-07-22
AI Technical Summary
A large number of false alarms occurred during the operation of the aircraft, resulting in a significant increase in the workload of ineffective operations and inefficient maintenance.
By obtaining the status parameters of the aircraft, confirming the target correlation parameters, and finding the corresponding first fault report from multiple fault reports based on the preset configuration file to suppress false alarms.
Effectively reduce false alarm rate, improve maintenance efficiency of the machinery, and improve the accuracy and storage efficiency of fault reporting.
Smart Images
Figure CN120356273A_ABST
Abstract
Description
Technical Field
[0001] Embodiments of the present application relate to the technical field of aircraft, and in particular, to a method, apparatus, device, and storage medium for fault handling of an aircraft. Background Art
[0002] With the operation of commercial aircraft, airlines have increasingly focused on the accuracy of problem location and the improvement of maintenance efficiency. Due to a large number of "false alarms" (such as failure messages that do not require maintenance by maintenance personnel) during the operation of the aircraft, the ineffective workload of maintenance personnel in actual flight routes has increased significantly, resulting in low maintenance efficiency. Summary of the Invention
[0003] Embodiments of the present application provide a method, apparatus, device, and storage medium for fault handling of an aircraft, which can effectively reduce the false alarm rate and improve the maintenance efficiency of maintenance personnel.
[0004] In a first aspect, an embodiment of the present application provides a method for fault handling of an aircraft, characterized by including:
[0005] Obtain a first state parameter of the aircraft and confirm a target associated parameter of the first state parameter;
[0006] Based on a preset configuration file, search for a first fault report corresponding to the target associated parameter from multiple fault reports to be processed by the aircraft; wherein, the configuration file includes multiple associated parameters determined based on state parameters of at least some systems of the aircraft, and fault reports of cross-linked systems affected by the multiple associated parameters;
[0007] In response to finding the first fault report, suppress the first fault report.
[0008] In an implementation manner, the confirmation of the target associated parameter of the first state parameter includes:
[0009] Based on the parameter processing logic corresponding to the system to which the first state parameter belongs, perform logical processing on the first state parameter to obtain the target associated parameter.
[0010] In an implementation manner, the system to which the first state parameter belongs includes the flight control system of the aircraft, and the parameter processing logic corresponding to the flight control system includes confirming the number of parameter signals;
[0011] The obtaining of the target associated parameter includes:
[0012] Confirm the number of parameter signals of the flight control system and use the number as the target associated parameter.
[0013] In one embodiment, the configuration file further includes a cascading scenario corresponding to each of the plurality of associated parameters;
[0014] Before searching for a first fault report corresponding to the target associated parameter from among a plurality of fault reports to be processed by the aircraft, it further includes:
[0015] Confirming that there is a cascading scenario corresponding to the target associated parameter in the configuration file.
[0016] In one embodiment, after finding the first fault report, it further includes:
[0017] Displaying a second fault report among the plurality of fault reports, where the second fault report is generated by the system to which the first state parameter belongs.
[0018] In one embodiment, the fault handling method further includes:
[0019] Storing the second fault report.
[0020] In one embodiment, the displaying the second fault report among the plurality of fault reports includes:
[0021] Generating a failure message including the second fault report;
[0022] Displaying the failure message.
[0023] In one embodiment, the fault handling method further includes:
[0024] Confirming a second state parameter related to the failure message;
[0025] Displaying the second state parameter associated with the failure message.
[0026] In one embodiment, the fault handling method further includes:
[0027] Confirming a cockpit effect message related to the failure message;
[0028] Displaying the cockpit effect message associated with the failure message.
[0029] In a second aspect, an embodiment of the present application provides a fault handling device for an aircraft, characterized by including:
[0030] A parameter processing module configured to obtain a first state parameter of the aircraft and confirm a target associated parameter of the first state parameter;
[0031] A fault handling module, configured to find a first fault report corresponding to the target associated parameter in multiple fault reports to be processed of the aircraft based on a preset configuration file; wherein, the configuration file includes multiple associated parameters determined based on status parameters of at least some systems of the aircraft, and fault reports of cross-linked systems affected by each of the multiple associated parameters;
[0032] The fault handling module is further configured to suppress the first fault report in response to finding the first fault report.
[0033] In a third aspect, an embodiment of the present application provides an electronic device, which includes a memory and a processor. A computer program is stored in the memory. When the processor executes the computer program, it implements the fault handling method of the aircraft described in any implementation manner in the first aspect.
[0034] In a fourth aspect, an embodiment of the present application provides a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, it implements the fault handling method of the aircraft described in any implementation manner in the first aspect.
[0035] In a fifth aspect, an embodiment of the present application provides a computer program product, including a computer program / instructions. When the computer program / instructions are executed by a processor, it implements the fault handling method of the aircraft described in any implementation manner in the first aspect.
[0036] The fault handling solution of the aircraft provided by the embodiment of the present application can, after obtaining the first status parameter of the aircraft, confirm the target associated parameter of the first status parameter, and then based on the preset configuration file, find the first fault report corresponding to the target associated parameter from multiple fault reports to be processed of the aircraft, and in response to finding the first fault report, know that the first fault report is a false alarm generated by the cross-linked system affected by the target associated parameter, so as to suppress the first fault report and not display and store the first fault report. Thereby, the false alarm rate can be effectively reduced and the maintenance efficiency of the aircraft maintenance personnel can be improved. Description of the Drawings
[0037] The following will make the technical solutions and other beneficial effects of the present application obvious by describing the specific implementation manners of the present application in detail with reference to the drawings.
[0038] Figure 1 It is a schematic diagram of a false alarm generated under the cascade effect;
[0039] Figure 2 It is a flowchart of the fault handling method of the aircraft provided by the embodiment of the present application;
[0040] Figure 3 It is a schematic diagram of an implementation scenario of a fault handling method for an aircraft provided by an embodiment of the present application;
[0041] Figure 4 It is another flowchart of a fault handling method for an aircraft provided by an embodiment of the present application;
[0042] Figure 5 It is a schematic structural diagram of a fault handling device for an aircraft provided by an embodiment of the present application. Detailed implementation manners
[0043] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative efforts belong to the scope of protection of the present application.
[0044] In the description of the present application, it should be noted that unless otherwise clearly defined and limited, the term "and / or" in this article is only a description of the association relationship of associated objects, indicating that there can be three relationships. For example, A and / or B can represent: A exists alone, A and B exist simultaneously, and B exists alone. In addition, the character " / " in this article generally represents an "or" relationship between the associated objects before and after without special instructions.
[0045] Currently, multiple member systems are usually installed on an aircraft. The multiple member systems include, for example, but are not limited to, multiple items such as a flight control system, a fuel system, a navigation system, a hydraulic system, a pneumatic system, and an air conditioning system. For any one of the multiple member systems, the member system may have a fault due to a fault in its upstream system or being in a specific working state. Such a fault generated by the member system can be called a cascading fault.
[0046] In practice, some cascading faults do not require maintenance operations by maintenance personnel. For example, faults generated by a member system due to the influence of the state parameters of its upstream system do not require maintenance operations by maintenance personnel, and the fault report generated for this fault can be regarded as a false alarm. Due to a large number of false alarms occurring during the operation of the aircraft, the ineffective workload of maintenance personnel in actual flight routes has increased significantly, and the maintenance efficiency is low.
[0047] Figure 1 It is a schematic diagram of a false alarm generated under the cascading effect. As Figure 1As shown, system A fails, generating a fault report A1. Additionally, since system A fails to send parameter signals to cross-linked systems B, C, ……, N, false alarms will be generated in cross-linked systems B, C, ……, N. For example, fault report B1 is generated in cross-linked system B, fault report C1 is generated in cross-linked system C, and fault report N1 is generated in cross-linked system N. Among them, fault reports A1, B1, C1, ……, N1 can generate multiple failure messages, such as Figure 1 the failure messages A2, ……, N2 shown in
[0048] The Onboard Maintenance System (OMS) will display and / or store these multiple failure messages. Since the failure messages generated based on fault reports B1, C1, ……, N1 do not require actual operations by maintenance personnel, the display and / or storage of these failure messages will waste a large amount of maintenance time for maintenance personnel, resulting in a significant increase in the ineffective workload of maintenance personnel and low maintenance efficiency.
[0049] The handling of cascading faults can be achieved by defining a handling method in the "inter-system fault diagnosis model" of the "aircraft maintenance system diagnosis model". However, this method does not consider cascading faults caused by state parameters.
[0050] The embodiment of the present application provides a fault handling solution for an aircraft, which can assist in handling cascading faults based on the state parameters of the aircraft to effectively reduce the false alarm rate and improve the maintenance efficiency of maintenance personnel. Among them, the aircraft includes, but is not limited to, an airplane.
[0051] It should be noted that the fault handling solution for the aircraft provided by the embodiment of the present application includes a preprocessing step. In this preprocessing step, a configuration file for fault handling of the aircraft is set. The configuration file includes multiple associated parameters determined based on the state parameters of at least part of the systems of the aircraft, and the fault reports of the cross-linked systems affected by each of the multiple associated parameters. Among them, the at least part of the systems includes one or more member systems among the various member systems of the aircraft. For any one of the at least part of the systems, parameter processing logic can be configured for the system, and based on the parameter processing logic, the state parameters of the system are logically processed to obtain the associated parameters of the state parameters. It should be understood that the parameter processing logic can be set according to actual requirements and is not specifically limited here.
[0052] Figure 2It is a flowchart of a fault handling method for an aircraft provided by an embodiment of the present application. This fault handling method can be executed by any device, system, apparatus, platform, or cluster of devices with data storage, computing, and processing capabilities, etc.
[0053] As Figure 2 shown, the fault handling method for an aircraft includes the following steps:
[0054] S201: Obtain the first state parameter of the aircraft and confirm the target associated parameter of the first state parameter;
[0055] S203: Based on a preset configuration file, find the first fault report corresponding to the target associated parameter from multiple fault reports to be processed by the aircraft; wherein, the configuration file includes multiple associated parameters determined based on the state parameters of at least part of the systems of the aircraft, and the fault reports of the cross-linked systems affected by each of the multiple associated parameters;
[0056] S205: In response to finding the first fault report, suppress the first fault report.
[0057] For the fault handling method for an aircraft provided by an embodiment of the present application, after obtaining the first state parameter of the aircraft, the target associated parameter of the first state parameter can be confirmed, and then based on the preset configuration file, the first fault report corresponding to the target associated parameter can be found from multiple fault reports to be processed by the aircraft. And in response to finding the first fault report, it can be known that the first fault report is a false alarm generated by the cross-linked system affected by the target associated parameter, so as to suppress the first fault report and not display and store the first fault report. Thus, the false alarm rate can be effectively reduced and the maintenance efficiency of the aircraft maintenance personnel can be improved.
[0058] Next, specific descriptions will be made for steps S201, S203, and S205.
[0059] In step S201, after obtaining the first state parameter of the aircraft, the target associated parameter of the first state parameter is confirmed. Among them, the first state parameter includes parameter signals sent by one or more member systems of the aircraft. The target associated parameter can be obtained by logically processing the first state parameter.
[0060] In practice, there can be various methods for confirming the target associated parameter.
[0061] For example, a corresponding relationship between the state parameter and the associated parameter can be established in advance, so as to confirm the target associated parameter of the first state parameter based on this corresponding relationship.
[0062] For another example, according to the description in the foregoing, at least some systems of the aircraft can be respectively configured with parameter processing logic. Based on this, the first status parameter can be logically processed based on the parameter processing logic corresponding to the system to which the first status parameter belongs, so as to obtain the target associated parameter.
[0063] Further, when the system to which the first status parameter belongs includes the flight control system of the aircraft, and the parameter processing logic corresponding to the flight control system includes confirming the number of parameter signals, the number of parameter signals of the flight control system can be confirmed, and this number can be used as the target associated parameter.
[0064] Taking the influence of the flight control self-test of the aircraft on the associated system as an example. During the taxiing-in phase of the aircraft, when the ground speed is less than 30 knots, the main flight control computer enters the post-flight self-test phase. During the self-test phase, the main flight control computer restarts, resulting in multiple cross-linked systems reporting faults because they cannot receive the parameter signals sent by the main flight control computer. Suppose the flight control system includes three flight control computers, one of which is the main flight control computer. When the main flight control computer performs self-test, it can only obtain the parameter signals sent by the other two flight control computers: FLT_CTRL_Maintenance = 1. The number of this parameter signal is 2, and 2 can be used as the associated parameter of this parameter signal.
[0065] In step S203, based on the preset configuration file, the first fault report corresponding to the target associated parameter is searched from multiple fault reports to be processed by the aircraft. For example, the associated parameter identical to the target associated parameter can be searched in the configuration file first. If found, each fault report corresponding to the identical associated parameter is obtained from the configuration file, and then the fault report included in each of these fault reports is searched from the multiple fault reports to be processed by the aircraft, and the found fault report is used as the first fault report corresponding to the target associated parameter.
[0066] It should be understood that the first fault report is a fault report generated under the influence of the target associated parameter and belongs to a false alarm, and should not be displayed and stored.
[0067] In step S205, in response to finding the first fault report, the first fault report is suppressed, such as not displaying and storing the first fault report.
[0068] In one embodiment, after the first fault report is found, the method further includes: displaying a second fault report among the multiple fault reports, where the second fault report is generated by the system to which the first status parameter belongs. It should be noted that the second fault report can be referred to as the root fault. By suppressing the first fault report and displaying the second fault report after the first fault report is found, the root fault can be isolated, enabling the maintenance staff to only perform maintenance operations on the root fault. Thereby, the accuracy and integrity of cascading fault handling can be improved, the false alarm rate can be further reduced, and the maintenance efficiency of the maintenance staff can be improved.
[0069] In one embodiment, after the first fault report is found, the method further includes: storing the second fault report. By suppressing the first fault report and storing the second fault report after the first fault report is found, a large number of false alarms can be avoided from being stored, thereby saving storage space, improving the accuracy rate of fault reports and the maintenance efficiency, and achieving cost reduction and efficiency improvement.
[0070] In one embodiment, when displaying the second fault report, a Failure message including the second fault report can be specifically generated and the Failure message can be displayed. Further, in order to facilitate the maintenance staff to perform fault maintenance quickly and accurately, the second status parameter and / or Flight Deck Effect (FDE) message related to the Failure message can be confirmed, and the second status parameter and / or the FDE message can be associated with the Failure message for display. Among them, the FDE message usually includes types such as warnings, cautions, prompts, and statuses.
[0071] Correspondingly, when storing the second fault report, the Failure message as described above can be specifically stored. Further, the second status parameter and / or the FDE message can be associated with the Failure message for storage.
[0072] Taking Figure 2 the aircraft described above as an example, in one embodiment, Figure 2 the implementation scenario of the fault handling method described can include an Aircraft Customized Management Tool (ACMT), an Aircraft Condition Monitoring System (ACMS), and a Central Maintenance System (CMS) as shown in Figure 3 . Among them, Figure 3 is a schematic diagram of the implementation scenario of the fault handling method for the aircraft provided in the embodiments of the present application.
[0073] As Figure 3As shown, the aircraft customization management tool, the aircraft status monitoring system, and the central maintenance system can communicate with each other. The configuration file described in the previous text can be stored in the aircraft customization management tool. Further, the aircraft customization management tool may further include, for example, Figure 3 the configuration module shown in, and the configuration file can be configured and stored in this configuration module. Optionally, the parameter processing logics corresponding to at least part of the systems as described above can also be stored in the aircraft customization management tool.
[0074] The aircraft status monitoring system can be configured to read configuration information from the aircraft customization management tool and perform step S201 as described above. This configuration information may include, for example, the parameter processing logics corresponding to at least part of the above systems.
[0075] Further, the aircraft status monitoring system may include, for example, Figure 3 the parameter processing module shown in, and step S201 is performed by this parameter processing module.
[0076] Furthermore, the aircraft status monitoring system may further include, for example, Figure 3 the parameter receiving module and the associated parameter output module shown in.
[0077] Among them, the parameter receiving module can receive the first status parameter of the aircraft and send the first status parameter to the parameter processing module, so that the parameter processing module confirms the target associated parameter of the first status parameter and sends the target associated parameter to the central maintenance system via the associated parameter output module. In addition, the parameter receiving module can also receive configuration information from the aircraft customization management tool and send this configuration information to the parameter processing module.
[0078] The central maintenance system can be configured to read the configuration file from the aircraft customization management tool, for example, read the configuration file from the configuration module of the aircraft customization management tool, and perform steps S203 and S205 as described above, and display and / or store the root fault (such as the second fault report described in the previous text).
[0079] Further, the central maintenance system may further include a fault processing module. The fault processing module can receive the target associated parameter from the associated parameter output module of the aircraft status monitoring system and perform steps S203 and S205.
[0080] Furthermore, the central maintenance system may further include at least one of a fault report acquisition module, a status parameter association module, a cockpit effect association module, etc.
[0081] Among them, the fault report acquisition module can be configured to acquire the fault report to be processed by the aircraft and send the fault report to the fault handling module. The status parameter association module can be configured to confirm the second status parameter related to the failure message including the second fault report and associate the failure message with the second status parameter. The cockpit effect association module can be configured to confirm the cockpit effect message related to the failure message and associate the failure message with the cockpit effect message.
[0082] In practice, the aircraft can involve multiple cascading scenarios. The multiple cascading scenarios can be aircraft-level cascading scenarios. Taking an aircraft as an example, the aircraft-level cascading scenarios can include, for example, but are not limited to: during post-flight self-test operations of the flight control system, it may cause false alarms for high-lift, display, landing gear, etc. because they cannot receive signals from the flight control computer in the self-test state; when the flight management GPS signal is invalid, it may cause false alarms for high-lift, hydraulic, atmosphere, etc. because they receive invalid GPS signals.
[0083] In order to deeply cover various cascading scenarios during the operation of the aircraft and improve the coverage rate of aircraft status recognition, in one embodiment, the configuration file as described above may further include multiple cascading scenarios. Specifically, while the configuration file includes the multiple association parameters as described above and the fault reports of the cross-linked systems affected by the multiple association parameters respectively, it also includes the cascading scenarios corresponding to the multiple association parameters respectively. In addition, the configuration module where the configuration file is located in the aircraft customization management tool can be called the scenario configuration module, and the configuration information as described above includes the configuration file.
[0084] In addition, the fault handling method of the aircraft provided in the embodiments of the present application may include as Figure 4 shown in the steps. Among them, Figure 4 is another flowchart of the fault handling method of the aircraft provided in the embodiments of the present application. The fault handling method includes the following steps:
[0085] S401: Acquire the first status parameter of the aircraft and confirm the target association parameter of the first status parameter;
[0086] S403: In response to confirming that there is a cascading scenario corresponding to the target association parameter in the preset configuration file, based on the configuration file, search for the first fault report corresponding to the target association parameter from the multiple fault reports to be processed by the aircraft; wherein, the configuration file includes multiple association parameters determined based on the status parameters of at least part of the systems of the aircraft, and the cascading scenarios and the fault reports of the cross-linked systems affected by the multiple association parameters respectively;
[0087] S405: In response to finding the first fault report, suppress the first fault report.
[0088] Among them, for the search process of the first fault report in steps S401 and S403 and the explanation of S405, reference can be made to the relevant descriptions in the previous text, which will not be elaborated here.
[0089] In addition, in step S403, when confirming whether there is a cascading scenario corresponding to the target associated parameter in the configuration file, since each associated parameter in the configuration file is configured with a corresponding cascading scenario, the associated parameter identical to the target associated parameter can be searched in the configuration file. If found, it can be confirmed that there is a cascading scenario corresponding to the target associated parameter in the configuration file.
[0090] Figure 4 The solution provided by the corresponding embodiment can, after obtaining the first state parameter of the aircraft, confirm the target associated parameter of the first state parameter, and then in response to confirming that there is a cascading scenario corresponding to the target associated parameter in the preset configuration file, based on this configuration file, search for the first fault report corresponding to the target associated parameter from multiple fault reports to be processed by the aircraft, and in response to finding the first fault report, learn that the first fault report is a false alarm generated by the cross-linking system affected by the target associated parameter, thereby suppressing the first fault report so as not to display and store the first fault report. Thereby, the false alarm rate can be effectively reduced, the maintenance efficiency of the aircraft maintenance personnel can be improved, and various cascading scenarios during the operation of the aircraft can be deeply covered, improving the coverage rate of aircraft state recognition.
[0091] According to the description in the previous text, the fault handling method for the aircraft provided by the embodiment of the present application is proposed and implemented based on the state parameters of the aircraft, which can combine the associated parameters of the state parameters with the fault reports of each member system to suppress false alarms, and finally display and / or store the root fault. This fault handling method is beneficial to the identification and handling of cascading faults, can effectively reduce the false alarm rate, improve the accuracy and maintenance efficiency of fault reports, and can deeply cover various cascading scenarios during the operation of the aircraft, improve the coverage rate of aircraft state recognition, and can achieve cost reduction and efficiency increase.
[0092] Figure 5 It is a schematic structural diagram of a fault handling device for an aircraft provided by an embodiment of the present application. The fault handling device includes:
[0093] A parameter processing module 501, configured to obtain the first state parameter of the aircraft and confirm the target associated parameter of the first state parameter;
[0094] A fault handling module 502, configured to search for a first fault report corresponding to the target associated parameter from multiple fault reports to be processed by the aircraft based on a preset configuration file; wherein, the configuration file includes multiple associated parameters determined based on the state parameters of at least part of the systems of the aircraft, and the fault reports of the cross-linking systems affected by the multiple associated parameters respectively;
[0095] The fault handling module 502 is further configured to suppress the first fault report in response to finding the first fault report.
[0096] In one embodiment, the parameter processing module 501 is further configured to: perform logical processing on the first status parameter based on the parameter processing logic corresponding to the system to which the first status parameter belongs, and obtain the target associated parameter.
[0097] In one embodiment, the system to which the first status parameter belongs includes the flight control system of the aircraft, and the parameter processing logic corresponding to the flight control system includes confirming the number of parameter signals; the parameter processing module 501 is further configured to: confirm the number of parameter signals of the flight control system, and use the number as the target associated parameter.
[0098] In one embodiment, the configuration file further includes the cascade scenarios corresponding to the above-mentioned multiple associated parameters; the fault handling module 502 is further configured to: before finding the first fault report corresponding to the target associated parameter from the multiple fault reports to be processed by the aircraft, confirm that there is a cascade scenario corresponding to the target associated parameter in the configuration file.
[0099] In one embodiment, the above-mentioned fault handling device further includes: a display module (not shown in the figure), configured to display a second fault report among the above-mentioned multiple fault reports, and the second fault report is generated by the system to which the first status parameter belongs.
[0100] In one embodiment, the above-mentioned fault handling device further includes: a storage module (not shown in the figure), configured to store the second fault report.
[0101] In one embodiment, the above-mentioned display module is further configured to: generate a failure message including the second fault report; display the failure message.
[0102] In one embodiment, the above-mentioned fault handling device further includes: a status parameter association module (not shown in the figure), configured to confirm a second status parameter related to the above-mentioned failure message; the above-mentioned display module is further configured to display the second status parameter associated with the above-mentioned failure message.
[0103] In one embodiment, the above-mentioned fault handling device further includes: a cockpit effect association module (not shown in the figure), configured to confirm a cockpit effect message related to the above-mentioned failure message; the above-mentioned display module is further configured to display the cockpit effect message associated with the above-mentioned failure message.
[0104] It should be noted that other aspects and implementation details of the fault handling device of the aircraft provided in the embodiments of the present application are the same as or similar to those of the fault handling method of the aircraft described above, and will not be elaborated here.
[0105] Embodiments of the present application further provide an electronic device, which includes a memory and a processor. A computer program is stored in the memory. When the processor executes the computer program, it implements the Figure 2 or Figure 4 fault handling method of the aircraft described.
[0106] Embodiments of the present application further provide a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, it implements the Figure 2 or Figure 4 fault handling method of the aircraft described.
[0107] Embodiments of the present application further provide a computer program product, including a computer program / instructions. When the computer program / instructions are executed by a processor, it implements the Figure 2 or Figure 4 fault handling method of the aircraft described.
[0108] As described above, only some implementation manners of the embodiments of the present application are provided, and there is no limitation in any form to this application. The protection scope of the embodiments of the present application is not limited thereto. Any simple modifications, equivalent changes and modifications that can be easily thought of by those skilled in the technical field of the present application within the technical scope disclosed by the embodiments of the present application should be covered within the protection scope of the embodiments of the present application.
Claims
1. A fault handling method for an aircraft, characterized in that, Including: Obtain a first state parameter of the aircraft and confirm a target associated parameter of the first state parameter; Based on a preset configuration file, find a first fault report corresponding to the target associated parameter from multiple fault reports to be processed by the aircraft; wherein, the configuration file includes multiple associated parameters determined based on state parameters of at least part of the systems of the aircraft, and fault reports of cross-linked systems affected by each of the multiple associated parameters; In response to finding the first fault report, suppress the first fault report.
2. The fault handling method according to claim 1, characterized in that The confirming the target associated parameter of the first state parameter includes: Based on the parameter processing logic corresponding to the system to which the first state parameter belongs, perform logical processing on the first state parameter to obtain the target associated parameter.
3. The fault handling method according to claim 2, wherein The system to which the first state parameter belongs includes the flight control system of the aircraft, and the parameter processing logic corresponding to the flight control system includes confirming the number of parameter signals; The obtaining the target associated parameter includes: Confirm the number of parameter signals of the flight control system and use the number as the target associated parameter.
4. The fault handling method according to claim 1, characterized in that, The configuration file further includes cascade scenarios corresponding to each of the multiple associated parameters; Before finding the first fault report corresponding to the target associated parameter from multiple fault reports to be processed by the aircraft, it further includes: Confirm that there is a cascade scenario corresponding to the target associated parameter in the configuration file.
5. The fault handling method according to claim 1, wherein After finding the first fault report, it further includes: Display a second fault report among the multiple fault reports, where the second fault report is generated by the system to which the first state parameter belongs.
6. The fault handling method according to claim 5, characterized in that It further includes: Store the second fault report.
7. The fault handling method according to claim 5, wherein The displaying the second fault report among the multiple fault reports includes: Generate a failure message including the second fault report; Display the failure message.
8. The fault handling method according to claim 7, wherein, It further includes: Confirm a second state parameter related to the failure message; Associate the second state parameter with the failure message for display.
9. The fault handling method according to claim 7 or 8, characterized in that, It further includes: Confirm a cockpit effect message related to the failure message; Associate the cockpit effect message with the failure message for display.
10. A fault handling device for an aircraft, characterized in that, Including: A parameter processing module configured to obtain a first state parameter of the aircraft and confirm a target associated parameter of the first state parameter; A fault processing module configured to, based on a preset configuration file, find a first fault report corresponding to the target associated parameter from multiple fault reports to be processed by the aircraft; wherein, the configuration file includes multiple associated parameters determined based on state parameters of at least part of the systems of the aircraft, and fault reports of cross-linked systems affected by each of the multiple associated parameters; The fault processing module is further configured to, in response to finding the first fault report, suppress the first fault report.
11. An electronic device, characterized in that, The electronic device includes a memory and a processor, and a computer program is stored in the memory. When the processor executes the computer program, it implements the fault processing method according to any one of claims 1-9.
12. A computer-readable storage medium, characterized in that, A computer program is stored on the computer-readable storage medium. When the computer program is executed by a processor, the fault handling method according to any one of claims 1-9 is implemented.