An avionics system fault diagnosis method and device based on fault propagation
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- CIVIL AVIATION UNIV OF CHINA
- Filing Date
- 2024-03-19
- Publication Date
- 2026-06-26
AI Technical Summary
Existing technologies are insufficient for rapid or accurate fault diagnosis of avionics systems, especially in cases of fault propagation across components and systems. Furthermore, emerging methods require a large number of training samples or require changes to existing maintenance procedures, making them difficult to apply in actual field maintenance.
A fault propagation model is constructed by acquiring the connection relationships of aircraft components, using XML to describe the components and their fault propagation relationships, and combining it with line maintenance operation information to locate the fault source, including information on malfunctioning parts and replaced parts. The fault propagation model is constructed and traversed to acquire cockpit effects, and finally the fault is located by comparing operational phenomena.
It improves the accuracy and speed of fault location, adapts to existing maintenance procedures without requiring significant changes, and is suitable for actual field maintenance.
Smart Images
Figure CN118192497B_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of fault diagnosis, and in particular relates to a method and apparatus for fault diagnosis of avionics systems based on fault propagation. Background Technology
[0002] Avionics systems, or avionics systems for short, play a crucial role as the "brain and central nervous system" among the three major systems of an aircraft: avionics, electromechanical systems, and power systems. They are responsible for core tasks such as flight control, communication, navigation, surveillance, and display and control, significantly impacting flight quality and safety. In civil aviation maintenance companies, during line maintenance, engineers typically follow the troubleshooting procedures outlined in the AMM (Line Maintenance Manual) and FIM (Fault Isolation Manual), combined with fault information from the onboard maintenance system, to conduct maintenance tests. The main methods employed include swapping backup components (e.g., exchanging the left and right VOR components) or replacing potentially faulty components with new ones (e.g., replacing the onboard VOR component with a brand-new one, which may or may not be faulty), observing the symptoms, and then troubleshooting.
[0003] However, due to the complexity of aircraft avionics systems and the intricate interconnections between various subsystems, faults propagate across components and systems, leading to more complex fault modes. Traditional methods often struggle to diagnose faults quickly or accurately. Emerging fault diagnosis methods, such as those based on Bayesian networks and neural networks, typically require a large number of fault samples for training. However, obtaining such training samples, or obtaining a large number of effective training samples, is often difficult in actual aircraft field maintenance. Other emerging methods may require significant modifications to existing troubleshooting procedures, making them difficult to apply in practical maintenance.
[0004] Based on the current situation of line maintenance in the civil aviation maintenance industry, and taking into account the cross-component and cross-system propagation of avionics system faults on the basis of existing maintenance and testing methods, it remains a challenge to construct avionics system fault diagnosis methods and devices that can be used for actual field maintenance without changing the existing maintenance process and by utilizing the information obtained from existing troubleshooting methods. Summary of the Invention
[0005] To address the problems existing in the prior art, this invention provides a method and apparatus for fault diagnosis of avionics systems based on fault propagation.
[0006] A fault diagnosis method for avionics systems based on fault propagation includes the following steps:
[0007] S1. Obtain the various components of the aircraft and the wiring connections between them. Then, convert them into fault propagation relationships and construct a fault propagation model by performing a structured representation.
[0008] S2, traverse the fault propagation model to obtain the component output;
[0009] S3, acquires fault information of avionics systems output by the airborne maintenance system and operational information and phenomena generated during line maintenance;
[0010] S4. Input the operational information generated during the line maintenance process into the fault propagation model to obtain the fault propagation model after line maintenance.
[0011] S5, traverse the fault propagation model after line maintenance to obtain the component output after line maintenance;
[0012] S6. Obtain the corresponding fault propagation model cockpit effect based on the component output and obtain the corresponding fault propagation model cockpit effect after line maintenance based on the component output after line maintenance.
[0013] S7 compares component output, cockpit effect of fault propagation model, component output after line maintenance, cockpit effect of fault propagation model after line maintenance, operational phenomena generated during line maintenance, and fault information of airborne maintenance system to locate the fault source.
[0014] Furthermore, step S1 includes:
[0015] Obtain the various components of the aircraft and their wiring connections, use XML to describe the various components and their wiring connections, and construct the architecture model of the avionics system.
[0016] Based on the operating principles of avionics systems, the connection relationships of various components in the architecture model are transformed into fault propagation relationships and represented in a structured manner. The fault propagation model is constructed by describing each component and its fault propagation relationship using XML or by using component linked lists and fault propagation path linked lists.
[0017] Furthermore, step S2 includes:
[0018] The health state of each component in the fault propagation model is set as the fault state, and the health state of all other components in the fault propagation model is obtained according to the fault propagation relationship.
[0019] Health status includes fault status and normal status;
[0020] The component output represents the health status of all components in the fault propagation model.
[0021] Furthermore, step S3 includes:
[0022] Obtain information on cross-component issues and phenomena during route maintenance;
[0023] Obtain information on replacement parts and their occurrence during the line maintenance process.
[0024] Furthermore, information on cross-contamination and related phenomena during the route maintenance process is obtained, including:
[0025] The serial device information includes information about the two swapped components;
[0026] The cross-contamination phenomenon includes the cockpit effect after cross-contamination and the component self-test results;
[0027] Obtain information on replacement parts and their occurrences during line maintenance, including:
[0028] The replacement parts information includes information about the original components and information about the new components;
[0029] The phenomenon of replacing parts includes the cockpit effect after replacing parts and the self-test results of components.
[0030] Furthermore, step S4 includes:
[0031] The operational information generated during the line maintenance process is mapped into the fault propagation model to obtain the fault propagation model after line maintenance.
[0032] When the operation information is serial device information, the structured description information representing serial devices in the fault propagation model is repositioned to meet the configuration after the serial device operation.
[0033] When the operation information is replacement information, the health status of the structured description information representing the original component in the fault propagation model is updated.
[0034] Furthermore, step S5 includes:
[0035] The health status of each component in the fault propagation model after line maintenance is set as the fault status, and the health status of all other components in the fault propagation model after line maintenance is obtained according to the fault propagation relationship.
[0036] Health status includes fault status and normal status;
[0037] The output of the component after line maintenance is the health status of all components in the fault propagation model after line maintenance.
[0038] Furthermore, step S6 includes:
[0039] Based on the health status of all components in the fault propagation model, the cockpit effect of the fault propagation model is obtained;
[0040] Based on the health status of all components in the fault propagation model after line maintenance, the cockpit effect of the fault propagation model after line maintenance is obtained.
[0041] Furthermore, step S7 includes:
[0042] The cockpit effect in the operational phenomena generated during line maintenance is compared with the cockpit effect of the fault propagation model and the cockpit effect of the fault propagation model after line maintenance. The search is conducted for the cockpit effect of the fault propagation model and / or the cockpit effect of the fault propagation model after line maintenance for fault location.
[0043] Obtain a series of fault propagation models and / or a series of post-line maintenance fault propagation models corresponding to the cockpit effect for fault location and the post-line maintenance fault propagation model for fault location.
[0044] By comparing the component self-test results, airborne maintenance system fault information, and series component outputs with the series post-line maintenance component outputs in the operational phenomena generated during the line maintenance process, the fault propagation model and / or the post-line maintenance fault propagation model used for fault location are identified; the series component outputs are the series component outputs corresponding to the series fault propagation model, and the series post-line maintenance component outputs are the series post-line maintenance component outputs corresponding to the post-line maintenance fault propagation model.
[0045] Locate the source of the fault based on the fault propagation model used for fault location and / or the post-maintenance fault propagation model used for fault location.
[0046] This invention claims protection for a fault diagnosis device for avionics systems based on fault propagation, comprising an aircraft manual interface module, an architecture model construction module, a fault propagation model construction module, a fault propagation model processing module, and a fault location module connected in sequence. The fault propagation model processing module is connected to an airborne maintenance system interface module and an airline maintenance operation interface module.
[0047] A fault propagation-based avionics system fault diagnosis device is used to perform a defined fault propagation-based avionics system fault diagnosis method.
[0048] This invention discloses a method and apparatus for fault diagnosis of avionics systems based on fault propagation. The fault diagnosis method includes constructing an architecture model of the avionics system, constructing a fault propagation model, traversing the fault propagation model, acquiring fault information from the airborne maintenance system, acquiring operational information and phenomena generated during line maintenance, inputting the operational information generated during line maintenance into the fault propagation model to obtain a post-line maintenance fault propagation model, traversing the post-line maintenance fault propagation model to acquire the cockpit effect of the fault propagation model, and finally locating the fault source based on the above information. This invention considers the problem of fault propagation across components and systems caused by the complexity of avionics systems, improving the accuracy and speed of fault source location caused by fault propagation. Attached Figure Description
[0049] Figure 1 This is a flowchart illustrating a fault diagnosis method for avionics systems based on fault propagation, according to an embodiment of the present invention.
[0050] Figure 2 This is a structural block diagram of an avionics system fault diagnosis device based on fault propagation, according to an embodiment of the present invention. Detailed Implementation
[0051] First embodiment, see appendix Figure 1 A fault diagnosis method for avionics systems based on fault propagation includes the following steps:
[0052] S1. Obtain the various components of the aircraft and the wiring connections between them. Then, convert them into fault propagation relationships and construct a fault propagation model by performing a structured representation.
[0053] S2, traverse the fault propagation model to obtain the component output;
[0054] S3, acquires fault information of avionics systems output by the airborne maintenance system and operational information and phenomena generated during line maintenance;
[0055] S4. Input the operational information generated during the line maintenance process into the fault propagation model to obtain the fault propagation model after line maintenance.
[0056] S5, traverse the fault propagation model after line maintenance to obtain the component output after line maintenance;
[0057] S6. Obtain the corresponding fault propagation model cockpit effect based on the component output and obtain the corresponding fault propagation model cockpit effect after line maintenance based on the component output after line maintenance.
[0058] S7 compares component output, cockpit effect of fault propagation model, component output after line maintenance, cockpit effect of fault propagation model after line maintenance, operational phenomena generated during line maintenance, and fault information of airborne maintenance system to locate the fault source.
[0059] Furthermore, step S1 includes:
[0060] Obtain the various components of the aircraft and their wiring connections, use XML to describe the various components and their wiring connections, and construct the architecture model of the avionics system.
[0061] Based on the operating principles of avionics systems, the connection relationships of various components in the architecture model are transformed into fault propagation relationships and represented in a structured manner. The fault propagation model is constructed by describing each component and its fault propagation relationship using XML or by using component linked lists and fault propagation path linked lists.
[0062] In this embodiment, the aircraft's WDM (System Schematic Manual) and SSM (Wire Connection Manual) describe the various components of the aircraft and their wiring connections. The avionics system components and their connections are extracted from the WDM and SSM manuals and converted into structured representation information. This structured representation can use XML to describe each component and its connections, thereby constructing an architectural model of the avionics system.
[0063] An architecture model of an avionics system provides a structured description of its components and their interconnections. Based on this, and according to the operating principles of the avionics system, the interconnections in the architecture model are transformed into fault propagation relationships and represented in a structured manner. A fault propagation relationship describes one or more fault propagation paths that lead from a component failure to other component failures. The structured representation can use XML to describe each component and its fault propagation relationships, or it can use a component linked list and a fault propagation path linked list. Besides constructing a fault propagation model based on the operating principles of the avionics system, it can also be based on experience from line maintenance or other information describing fault propagation.
[0064] Furthermore, step S2 includes:
[0065] The health state of each component in the fault propagation model is set as the fault state, and the health state of all other components in the fault propagation model is obtained according to the fault propagation relationship.
[0066] Health status includes fault status and normal status;
[0067] The component output represents the health status of all components in the fault propagation model.
[0068] Furthermore, step S3 includes:
[0069] Obtain information on cross-component issues and phenomena during route maintenance;
[0070] Obtain information on replacement parts and their occurrence during the line maintenance process.
[0071] In this embodiment, fault information from the avionics system provided by the airborne maintenance system is acquired, such as a VOR (Vehicle Orbit) fault indicated by the airborne maintenance system. This information can be obtained through the multifunction display in the cockpit or through a maintenance terminal connected to the airborne network. Due to fault propagation, the fault information provided by the airborne maintenance system may not necessarily represent the actual fault, nor may it be able to pinpoint the fault source.
[0072] Furthermore, information on cross-component issues and phenomena during the route maintenance process is obtained, specifically including:
[0073] The serial device information includes information about the two swapped components;
[0074] The cross-contamination phenomenon includes the cockpit effect after cross-contamination and the component self-test results;
[0075] Obtain information on replacement parts and their occurrences during line maintenance, specifically including:
[0076] The replacement parts information includes information about the original components and information about the new components;
[0077] The phenomenon of replacing parts includes the cockpit effect after replacing parts and the self-test results of components.
[0078] In this embodiment, the component information includes information about the two swapped components, such as swapping the left VOR with the right VOR. The phenomena include cockpit effects after the component swap and component self-test results. Due to fault propagation, for example, after swapping the left VOR with the right VOR, the current left VOR (i.e., the original right VOR) can pass the component self-test, and the corresponding VOR indicator on the cockpit display will show normally; conversely, after swapping the left ADF with the right ADF, the current left ADF (i.e., the original right ADF) cannot pass the component self-test, and the corresponding ADF indicator on the cockpit display will show a fault flag.
[0079] Replacement information includes information about the original component and the new component, such as replacing the original VOR component on the left with a new VOR component. Replacement phenomena include cockpit effects after replacement and component self-test results. Due to fault propagation, replacing a component may not necessarily pinpoint the fault source. For example, after replacing the original VOR component on the left with a new VOR component, the left side may now show VOR, meaning the new VOR component passes the component self-test, and the corresponding VOR indicator on the cockpit display will show normally. Similarly, after replacing the original ADF component on the left with a new ADF component, the left side may now show ADF, meaning the new ADF component passes the component self-test, but the corresponding ADF indicator on the cockpit display will show a fault flag. Finally, after replacing the original ADF component on the left with a new ADF component, the left side may now show ADF, meaning the new ADF component fails the component self-test, and the corresponding ADF indicator on the cockpit display will show a fault flag.
[0080] Furthermore, step S4 includes:
[0081] The operational information generated during the line maintenance process is mapped into the fault propagation model to obtain the fault propagation model after line maintenance.
[0082] When the operation information is serial device information, the structured description information representing serial devices in the fault propagation model is repositioned to meet the configuration after the serial device operation.
[0083] When the operation information is replacement information, the health status of the structured description information representing the original component in the fault propagation model is updated.
[0084] In this embodiment, operational information generated during line maintenance, such as component mismatch information or replacement information, is mapped to a fault propagation model to obtain a fault propagation model after line maintenance. For example, if component mismatch information involves swapping the left and right VORs, the structured description information representing the left and right VORs in the fault propagation model is adjusted to fit the configuration after the mismatch operation. Similarly, if replacement involves replacing the original left ADF component with a new one, the health status of the structured description information representing the left ADF component in the fault propagation model is updated.
[0085] Furthermore, step S5 includes:
[0086] The health status of each component in the fault propagation model after line maintenance is set as the fault status, and the health status of all other components in the fault propagation model after line maintenance is obtained according to the fault propagation relationship.
[0087] Health status includes fault status and normal status;
[0088] The output of the component after line maintenance is the health status of all components in the fault propagation model after line maintenance.
[0089] Furthermore, step S6 includes:
[0090] Based on the health status of all components in the fault propagation model, the cockpit effect of the fault propagation model is obtained;
[0091] Based on the health status of all components in the fault propagation model after line maintenance, the cockpit effect of the fault propagation model after line maintenance is obtained.
[0092] In this embodiment, the cockpit effect of the fault propagation model is obtained based on the health status of all components in the fault propagation model. For example, if the VOR on the right side of the fault propagation model is faulty, the cockpit effect of the fault propagation model is that the corresponding VOR indicator on the cockpit display shows a fault flag.
[0093] Based on the health status of all components in the fault propagation model after line maintenance, the cockpit effect of the fault propagation model after line maintenance is obtained. For example, if the right ADF fails in the fault propagation model after line maintenance, the cockpit effect of the fault propagation model after line maintenance is that the corresponding ADF indicator on the cockpit display shows a fault flag.
[0094] Furthermore, step S7 includes:
[0095] The cockpit effect in the operational phenomena generated during line maintenance is compared with the cockpit effect of the fault propagation model and the cockpit effect of the fault propagation model after line maintenance. The search is conducted for the cockpit effect of the fault propagation model and / or the cockpit effect of the fault propagation model after line maintenance for fault location.
[0096] Obtain a series of fault propagation models and / or a series of post-line maintenance fault propagation models corresponding to the cockpit effect for fault location and the post-line maintenance fault propagation model for fault location.
[0097] By comparing the component self-test results, airborne maintenance system fault information, and series component outputs with the series post-line maintenance component outputs in the operational phenomena generated during the line maintenance process, the fault propagation model and / or the post-line maintenance fault propagation model used for fault location are identified; the series component outputs are the series component outputs corresponding to the series fault propagation model, and the series post-line maintenance component outputs are the series post-line maintenance component outputs corresponding to the post-line maintenance fault propagation model.
[0098] Locate the source of the fault based on the fault propagation model used for fault location and / or the post-maintenance fault propagation model used for fault location.
[0099] In this embodiment, the cockpit effect of the fault propagation model used for fault location and / or the cockpit effect of the fault propagation model after line maintenance used for fault location refer to the cockpit effect of the fault propagation model that is consistent with the cockpit effect in the operational phenomena generated during line maintenance and / or the cockpit effect of the fault propagation model after line maintenance. If there is no consistent cockpit effect, the cockpit effect of the fault propagation model that is closest to the cockpit effect in the operational phenomena generated during line maintenance and / or the cockpit effect of the fault propagation model after line maintenance is found. The closest cockpit effect of the fault propagation model and / or the cockpit effect of the fault propagation model after line maintenance can be determined using a similarity search algorithm in the prior art.
[0100] Since different faults may produce the same cockpit effect, the fault propagation models and / or line maintenance post-fault propagation models corresponding to the cockpit effect for fault location and / or the cockpit effect for fault location may be a series and require further screening.
[0101] Based on the reverse correspondence of the steps to obtain the cockpit effect of the corresponding fault propagation model and / or the cockpit effect of the corresponding fault propagation model after line maintenance, a series of fault propagation models and / or a series of fault propagation models after line maintenance can be obtained. At the same time, the corresponding series of component outputs and the corresponding series of component outputs after line maintenance are also obtained.
[0102] When the component output and / or the component output after line maintenance are consistent with the component self-test results and the fault information of the airborne maintenance system observed during the line maintenance process, then the fault propagation model and / or the fault propagation model after line maintenance serves as the fault propagation model and / or the fault propagation model after line maintenance for fault location. If no consistent model is found, the closest one can be identified using existing similarity search algorithms, which will then serve as the fault propagation model and / or the fault propagation model after line maintenance for fault location.
[0103] Based on the health status of components in the fault propagation model used for fault location and / or the post-line maintenance fault propagation model used for fault location, the component in a faulty state is identified as the fault source.
[0104] The second embodiment, as shown in the appendix... Figure 2A fault diagnosis device for avionics systems based on fault propagation includes an aircraft manual interface module, an architecture model construction module, a fault propagation model construction module, a fault propagation model processing module, and a fault location module connected in sequence. The fault propagation model processing module is connected to the airborne maintenance system interface module and the line maintenance operation interface module, respectively.
[0105] The aircraft manual interface module is used to extract avionics system components and their connections from the aircraft WDM manual and SSM manual, and then pass them to the architecture model building module.
[0106] The architecture model building module is used to convert the avionics components and their connections output by the aircraft manual interface module into structured representation information, thereby building the architecture model.
[0107] The fault propagation model construction module is used to construct a fault propagation model of the avionics system based on the architecture model constructed by the architecture model construction module. When constructing the fault propagation model, it is based on the architecture model, the operating principles of the avionics system, experience information from line maintenance, or other information describing fault propagation.
[0108] The airborne maintenance system interface module is used to receive fault maintenance information from the aircraft's airborne maintenance system and transmit it to the fault propagation model processing module; the fault maintenance information is described in a structured manner using XML and then transmitted.
[0109] The line maintenance operation interface module is used to receive operation information and phenomena during aircraft line maintenance and transmit them to the fault propagation model processing module; the operation information and phenomena are described in a structured manner using XML and then transmitted.
[0110] The fault propagation model processing module is used to traverse the fault propagation model, input the information transmitted by the airborne maintenance system interface module and the line maintenance operation interface module into the fault propagation model, and traverse it. Based on the component output, the corresponding fault propagation model cockpit effect is obtained, and based on the component output after line maintenance, the corresponding line maintenance post-fault propagation model cockpit effect is obtained.
[0111] The fault location module receives the output from the fault propagation model processing module and performs fault location.
[0112] The aforementioned fault propagation-based avionics system fault diagnosis device is used to execute a defined fault propagation-based avionics system fault diagnosis method.
[0113] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.
Claims
1. A fault diagnosis method for avionics systems based on fault propagation, characterized in that, Includes the following steps: S1. Obtain the various components of the aircraft and the wiring connections of the various components, and construct a fault propagation model by converting them into fault propagation relationships and performing structured representation. S2, traverse the fault propagation model to obtain the component output; S3, acquires fault information of avionics systems output by the airborne maintenance system and operational information and phenomena generated during line maintenance; S4, input the operation information generated during the route maintenance process into the fault propagation model to obtain the fault propagation model after route maintenance; S5, traverse the fault propagation model after the route maintenance to obtain the component output after the route maintenance; S6. Obtain the corresponding fault propagation model cockpit effect based on the component output and obtain the corresponding fault propagation model cockpit effect after the route maintenance based on the component output after the route maintenance. S7. By comparing the component output, the cockpit effect of the fault propagation model, the component output after the line maintenance, the cockpit effect of the fault propagation model after the line maintenance, the operational phenomena generated during the line maintenance process, and the fault information of the airborne maintenance system, the fault source is located.
2. The avionics system fault diagnosis method based on fault propagation as described in claim 1, characterized in that, Step S1 includes: Obtain the various components of the aircraft and their wiring connections, use XML to describe the various components of the aircraft and their wiring connections, and construct an architecture model of the avionics system. Based on the operating principle of avionics systems, the connection relationships of various components in the architecture model are converted into fault propagation relationships and represented in a structured manner. The fault propagation model is constructed by describing each component and its fault propagation relationship using XML or by using component linked lists and fault propagation path linked lists.
3. The avionics system fault diagnosis method based on fault propagation as described in claim 1, characterized in that, Step S2 includes: The health state of each component in the fault propagation model is set to a fault state, and the health state of all other components in the fault propagation model is obtained according to the fault propagation relationship. The health status includes fault status and normal status; The component output represents the health status of all components in the fault propagation model.
4. The avionics system fault diagnosis method based on fault propagation as described in claim 1, characterized in that, Step S3 includes: Obtain information on cross-component issues and phenomena during route maintenance; Obtain information on replacement parts and their occurrence during the line maintenance process.
5. The avionics system fault diagnosis method based on fault propagation as described in claim 4, characterized in that, The acquisition of cross-device information and cross-device phenomena during the route maintenance process includes: The serial device information includes information about the two swapped components; The component crossover phenomenon includes the cockpit effect after component crossover and the component self-test results; The acquisition of replacement parts information and replacement phenomena during the line maintenance process includes: The replacement component information includes information about the original component and information about the new component; The phenomenon of replacing parts includes the cockpit effect after replacing parts and the self-test results of components.
6. The avionics system fault diagnosis method based on fault propagation as described in claim 1, characterized in that, Step S4 includes: The operational information generated during the route maintenance process is mapped into the fault propagation model to obtain the fault propagation model after route maintenance. When the operation information is serial device information, the structured description information representing serial devices in the fault propagation model is adjusted to meet the configuration after the serial device operation. When the operation information is replacement information, the health status of the structured description information representing the original component in the fault propagation model is updated.
7. The avionics system fault diagnosis method based on fault propagation as described in claim 1, characterized in that, Step S5 includes: The health status of each component in the fault propagation model after the route maintenance is set as the fault status, and the health status of all other components in the fault propagation model after the route maintenance is obtained according to the fault propagation relationship. The health status includes fault status and normal status; The output of the component after the route maintenance is the health status of all components in the fault propagation model after the route maintenance.
8. The avionics system fault diagnosis method based on fault propagation as described in claim 1, characterized in that, Step S6 includes: Based on the health status of all components in the fault propagation model, the cockpit effect of the fault propagation model is obtained; Based on the health status of all components in the fault propagation model after line maintenance, the cockpit effect of the fault propagation model after line maintenance is obtained.
9. The avionics system fault diagnosis method based on fault propagation as described in claim 1, characterized in that, Step S7 includes: The cockpit effect in the operational phenomena generated during the line maintenance process is compared with the cockpit effect of the fault propagation model and the cockpit effect of the fault propagation model after line maintenance, and the fault propagation model cockpit effect for fault location and / or the cockpit effect of the fault propagation model after line maintenance for fault location are searched. Obtain the series of fault propagation models and / or series of fault propagation models corresponding to the cockpit effect of the fault propagation model for fault location and / or the cockpit effect of the line maintenance post-fault propagation model for fault location. The self-test results of components in the operational phenomena generated during the line maintenance process, the fault information of the airborne maintenance system, and the outputs of a series of components and the outputs of components after a series of line maintenance are compared to identify the fault propagation model for fault location and / or the fault propagation model after line maintenance for fault location. The outputs of the series of components are the outputs of the series of components corresponding to the series fault propagation model, and the outputs of components after line maintenance are the outputs of components after line maintenance corresponding to the fault propagation model after line maintenance. The fault source is located based on the fault propagation model for fault location and / or the post-line maintenance fault propagation model for fault location.
10. A fault diagnosis device for avionics systems based on fault propagation, characterized in that, It includes an aircraft manual interface module, an architecture model construction module, a fault propagation model construction module, a fault propagation model processing module, and a fault location module connected in sequence. The fault propagation model processing module is connected to the airborne maintenance system interface module and the line maintenance operation interface module. The aforementioned fault propagation-based avionics system fault diagnosis device is used to perform a fault propagation-based avionics system fault diagnosis method as defined in any one of claims 1-9.