Aero-engine fault knowledge conversion method, device, equipment and product

Abstract

The invention relates to an aero-engine fault knowledge conversion method, device, equipment and product, and is applied to the technical field of aero-engines. According to the invention, the historical fault problem of the aero-engine is obtained. And extracting the historical fault problem to obtain historical fault data corresponding to the historical fault problem. The historical fault data are converted, fault knowledge corresponding to the historical fault problems is obtained, and the fault knowledge comprises matters needing attention, methods, tools and solving criteria for solving the same type of problems of the historical fault problems. And according to the fault knowledge and a preset knowledge conversion template, determining a knowledge conversion result corresponding to the historical fault problem. By extracting historical fault data, fault knowledge can be quickly converted. Therefore, the solving criterion of the historical fault problem can be universally applied to similar problems or research and development of the aero-engine, and sharing of knowledge conversion results can be realized. Therefore, the efficiency of fault knowledge conversion can be improved.

Description

Technical Field

[0001] The present application belongs to the field of aero-engine technology, and specifically relates to a method, device, equipment and product for converting aero-engine fault knowledge. Background Art

[0002] Aircraft engines are highly complex and sophisticated thermal machines that are not only the driving force for aircraft flight, but also an important driving force for the development of aviation. However, aircraft engines often fail due to factors such as operation and maintenance, operating losses, and environmental impacts. As the core power unit of aircraft, it is crucial to solve the problem of aircraft engine failure.

[0003] Generally speaking, the fault knowledge for aircraft engine fault detection and maintenance can only solve a single fault problem. However, such a method has a low utilization rate of fault knowledge mining, thus reducing the efficiency of fault knowledge conversion. Summary of the invention

[0004] The present disclosure is proposed in view of the above problems. The present disclosure provides a method, device, equipment and product for converting aircraft engine fault knowledge, which can improve the efficiency of fault knowledge conversion.

[0005] According to one aspect of the present disclosure, a method for converting aircraft engine fault knowledge is provided, comprising: Obtain historical failure issues of aircraft engines; Extracting the historical fault problems to obtain historical fault data corresponding to the historical fault problems, wherein the historical fault data includes fault attribute information and fault resolution measures of the aircraft engine when the historical fault problems occur; The historical fault data is transformed to obtain fault knowledge corresponding to the historical fault problem, wherein the fault knowledge includes precautions, methods and tools, and solution criteria for solving the same type of problems as the historical fault problem; According to the fault knowledge and a preset knowledge conversion template, a knowledge conversion result corresponding to the historical fault problem is determined.

[0006] Optionally, the converting the historical fault data to obtain fault knowledge corresponding to the historical fault problem includes: Based on the system engineering background environment model and the fault scenarios in the fault attribute information, the preset constraint control conditions and preset enabling conditions of the fault object of the aircraft engine are transformed and processed to obtain the fault knowledge, and the preset constraint control conditions include load conditions, operating conditions and test conditions.

[0007] Optionally, obtaining historical fault problems of the aircraft engine includes: Acquire multiple fault levels of the aircraft engine; According to the plurality of fault levels, determining a plurality of fault objects of each of the fault levels; Problems are collected for each of the fault objects to obtain various types of historical fault problems of each of the fault objects.

[0008] Optionally, after converting the historical fault data to obtain fault knowledge corresponding to the historical fault problem, the method further includes: A fault knowledge base of the aircraft engine is constructed based on the fault object and the fault knowledge corresponding to the historical fault problem.

[0009] Optionally, after determining the knowledge conversion result corresponding to the historical fault problem according to the fault knowledge and a preset knowledge conversion template, the method further includes: Based on the knowledge conversion result, the aircraft engine is developed and researched, and the research and development process nodes of the aircraft engine, the operating instructions and specifications of the aircraft engine, the inspection list of the aircraft engine and the standard specifications of the aircraft engine are determined.

[0010] Optionally, after determining the knowledge conversion result corresponding to the historical fault problem according to the fault knowledge and a preset knowledge conversion template, the method further includes: Obtain aircraft engine failure issues; If the fault knowledge corresponding to the fault problem is found in the fault knowledge base, the fault problem is processed according to the fault knowledge; If the fault knowledge corresponding to the fault problem is not found in the fault knowledge base, the fault problem is extracted to determine the fault data; the fault data is transformed to obtain the fault knowledge corresponding to the fault problem, and the fault knowledge base is updated according to the fault knowledge.

[0011] According to another aspect of the present disclosure, a device for converting aircraft engine fault knowledge is provided, comprising: Acquisition module, used to obtain historical fault problems of aircraft engines; An extraction module, used to extract the historical fault problems and obtain historical fault data corresponding to the historical fault problems, wherein the historical fault data includes fault attribute information and fault resolution measures of the aircraft engine when the historical fault problems occur; A conversion module, used to convert the historical fault data to obtain fault knowledge corresponding to the historical fault problem, wherein the fault knowledge includes precautions, methods and tools, and solution criteria for solving the same type of problems as the historical fault problem; The determination module is used to determine the knowledge conversion result corresponding to the historical fault problem according to the fault knowledge and a preset knowledge conversion template.

[0012] According to another aspect of the present disclosure, an electronic device is provided, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the above-mentioned method for converting aircraft engine fault knowledge.

[0013] According to another aspect of the present disclosure, a computer-readable storage medium is provided, on which a computer program is stored, and the program is executed by a processor to implement the above-mentioned method for converting aircraft engine fault knowledge.

[0014] According to another aspect of the present disclosure, a computer program product is provided, including a computer-readable code, or a non-volatile computer-readable storage medium carrying the computer-readable code. When the computer-readable code runs in a processor of an electronic device, the processor in the electronic device executes the method for converting the above-mentioned aircraft engine fault knowledge.

[0015] In the present disclosure, historical fault problems of aircraft engines are obtained. The historical fault problems are extracted to obtain historical fault data corresponding to the historical fault problems. The historical fault data includes fault attribute information and fault solution measures of the aircraft engine when the historical fault problems occur. The historical fault data is transformed to obtain fault knowledge corresponding to the historical fault problems. The fault knowledge includes precautions, methods and tools, and solution criteria for solving the same type of problems of the historical fault problems. According to the fault knowledge and the preset knowledge transformation template, the knowledge transformation result corresponding to the historical fault problem is determined. By refining the historical fault data, the fault knowledge can be quickly transformed. In addition, the solution criteria of the historical fault problems can be applied to similar problems, or in the research and development of the aircraft engine, and the sharing of knowledge transformation results can be achieved. Therefore, the efficiency of fault knowledge transformation can be improved.

[0016] It is to be understood that both the foregoing general description and the following detailed description are exemplary, and are intended to provide further explanation of the technology as claimed. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The above and other purposes, features and advantages of the present disclosure will become more apparent by describing the embodiments of the present disclosure in more detail in conjunction with the accompanying drawings. The accompanying drawings are used to provide a further understanding of the embodiments of the present disclosure and constitute a part of the specification. Together with the embodiments of the present disclosure, they are used to explain the present disclosure and do not constitute a limitation of the present disclosure. In the accompanying drawings, the same reference numerals generally represent the same components or steps.

[0018] Figure 1 A flow chart of a method for converting aircraft engine fault knowledge provided by the present invention.

[0019] Figure 2 A schematic diagram of the structure of multiple fault levels of an aircraft engine provided by the present disclosure.

[0020] Figure 3 Another flow chart of a method for converting aircraft engine fault knowledge provided by the present invention.

[0021] Figure 4 A schematic diagram of the structure of a device for converting aircraft engine fault knowledge provided by the present invention.

[0022] Figure 5 A hardware block diagram of an electronic device provided by the present disclosure.

[0023] Figure 6 A schematic diagram of a computer program product provided by the present disclosure. DETAILED DESCRIPTION

[0024] In order to enable those skilled in the art to more clearly understand the technical solution of the present application, the application scenario of the solution of the present application is first described below.

[0025] Aircraft engines are highly complex and sophisticated thermal machines. They are not only the power of aircraft flight, but also an important driving force for the development of aviation. Aircraft engines often fail due to factors such as operation and maintenance, operating losses and environmental impacts. As the core power unit of aircraft, the resolution of aircraft engine failures is crucial. At the same time, aircraft engine research and development requires experience accumulation. Typical failure cases and troubleshooting experience in the model development process play an important role in the high-quality and efficient development of models.

[0026] At present, in the process of model development of aircraft engines, more attention is paid to quality issues, while the analysis, mining and utilization of fault experience are not paid enough attention. The fault knowledge for fault detection and maintenance of aircraft engines can often only solve a single fault problem, and the extracted fault experience lacks explicit and structured model fault experience summary and extraction methods, and no structured fault knowledge base has been formed. Fault experience does not provide sufficient support for model development during model development and use, resulting in repeated occurrence of the same fault, which seriously affects the quality of model development. At the same time, there is a lack of cross-model sharing channels, and the sharing and sharing of fault experience cannot be achieved during the model development process, which is not convenient for sharing fault experience between models, resulting in extremely low mining and utilization of fault experience. Therefore, the efficiency of fault knowledge conversion will be reduced.

[0027] In order to solve the above technical problems, the present disclosure provides a method, device, equipment and product for transforming aircraft engine fault knowledge. In the present disclosure, historical fault problems of aircraft engines are obtained. The historical fault problems are extracted to obtain historical fault data corresponding to the historical fault problems. The historical fault data includes fault attribute information and fault solution measures of the aircraft engine when the historical fault problems occur. The historical fault data is transformed and processed to obtain fault knowledge corresponding to the historical fault problems. The fault knowledge includes precautions, methods and tools, and solution criteria for solving the same type of problems of the historical fault problems. According to the fault knowledge and the preset knowledge transformation template, the knowledge transformation result corresponding to the historical fault problem is determined. By refining the historical fault data, the fault knowledge can be quickly transformed. In addition, the solution criteria of the historical fault problems can be applied to similar problems, or in the research and development of the aircraft engine, and the sharing of knowledge transformation results can be achieved. Therefore, the efficiency of fault knowledge transformation can be improved.

[0028] In order to make the purpose, technical solution and advantages of the present disclosure more obvious, the exemplary embodiments according to the present disclosure will be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present disclosure, rather than all the embodiments of the present disclosure, and it should be understood that the present disclosure is not limited to the exemplary embodiments described here.

[0029] Figure 1 A flow chart of a method for converting aircraft engine fault knowledge provided by the present disclosure. Figure 1 As shown, the method includes: S101: Obtain historical failure issues of aircraft engines.

[0030] Specifically, we will sort out all kinds of fault problems in the aircraft engine at all levels during the R&D process or operation, such as engine vibration, engine surge, wear, oil leakage, breakage, jamming, blade breakage, peeling, etc. These fault problems will be used as historical fault problems for subsequent knowledge conversion.

[0031] S102: extracting historical fault problems to obtain historical fault data corresponding to the historical fault problems.

[0032] Specifically, there are various fault information in the acquired historical fault problems, and it is necessary to screen and refine the information in the historical fault problems to obtain historical fault data related to the converted fault knowledge. In order to improve the efficiency of fault knowledge conversion. Among them, the historical fault data includes the fault attribute information and fault solution measures of the aircraft engine when the historical fault problem occurs. In this embodiment, the fault attribute information can include the fault level of the fault object, the fault object name and the fault problem name.

[0033] S103: Perform transformation processing on the historical fault data to obtain fault knowledge corresponding to the historical fault problems.

[0034] Specifically, based on the system engineering background environment model, it can be determined that the elements required for the conversion process include input data, control conditions and enabling conditions, that is, the fault attribute information of the historical fault data. In this embodiment, the input data can be the application scenario of the historical fault data, the control conditions can be the data in the historical fault data that can constrain the research and development results, and the enabling conditions can be the data in the historical fault data that can help the research and development skills, so as to obtain fault knowledge. Among them, fault knowledge includes precautions, methods and tools, and solution criteria for solving the same type of problems of historical fault problems.

[0035] S104: Determine the knowledge conversion result corresponding to the historical fault problem according to the fault knowledge and the preset knowledge conversion template.

[0036] Specifically, in this embodiment, the preset knowledge conversion template can be a structured expression framework. By combining the obtained fault knowledge with the template, the corresponding knowledge conversion result can be obtained. The knowledge conversion result can be used to guide the research and development of aircraft engines, and can be used for troubleshooting guidance when encountering similar fault problems. For example, the knowledge conversion result can be expressed in the following form: when performing demand analysis / design / processing technology / verification (such as design scenarios) of a certain component / system, considering the preset constraints, you should pay attention to (such as precautions) what to do / what not to do to avoid certain situations / otherwise it is easy to cause certain situations (such as purpose / cause).

[0037] In the present disclosure, historical fault problems of aircraft engines are obtained. The historical fault problems are extracted to obtain historical fault data corresponding to the historical fault problems. The historical fault data includes fault attribute information and fault solution measures of the aircraft engine when the historical fault problems occur. The historical fault data is transformed to obtain fault knowledge corresponding to the historical fault problems. The fault knowledge includes precautions, methods and tools, and solution criteria for solving the same type of problems of the historical fault problems. According to the fault knowledge and the preset knowledge transformation template, the knowledge transformation result corresponding to the historical fault problem is determined. By refining the historical fault data, the fault knowledge can be quickly transformed. In addition, the solution criteria of the historical fault problems can be applied to similar problems, or in the research and development of the aircraft engine, and the sharing of knowledge transformation results can be achieved. Therefore, the efficiency of fault knowledge transformation can be improved.

[0038] In a possible implementation, an exemplary method of converting historical fault data to obtain fault knowledge corresponding to historical fault problems includes: Based on the system engineering background environment model and the fault scenarios in the fault attribute information, the preset constraint control conditions and preset enabling conditions of the aircraft engine fault object are transformed and processed to obtain the fault knowledge.

[0039] Specifically, based on the system engineering background environment model, the fault scenario in the fault attribute information is used as an input item, the preset constraint control conditions and preset enabling conditions of the fault object are analyzed and transformed, the causes of the fault and improvement measures are analyzed by the method, the fault knowledge is refined and summarized, and the output result is obtained, that is, the fault knowledge that characterizes the precautions, methods and tools, and solution criteria for solving the same type of historical fault problems. In this embodiment, the preset constraint control conditions include load conditions, working conditions, and test conditions, and the preset enabling conditions can be the professional knowledge and thinking model used to solve the fault problem.

[0040] In a possible implementation, an exemplary method for obtaining historical fault problems of an aircraft engine includes: A plurality of fault levels of an aircraft engine are obtained; and a plurality of fault objects of each fault level are determined according to the plurality of fault levels.

[0041] Specifically, according to the aircraft engine product breakdown structure (PBS), multiple fault levels of aircraft engines can be determined, including the whole machine level, component / system level, and component level. Each fault level includes multiple fault objects. Figure 2 A schematic diagram of the structure of multiple fault levels of an aircraft engine provided by the present disclosure, such as Figure 2 As shown, for example, the whole machine layer includes fault objects such as aircraft engine whole machines; the component / system layer includes fault objects such as air intake casing, fan, intermediate casing, high-pressure compressor, combustion chamber, turbine, control system, mechanical system, exhaust system, health management system, etc.; the component layer includes fault objects such as high-pressure compressor rotor, stator assembly, adjustable blade control system, turbine guide vane, turbine casing, turbine rotor, etc.

[0042] Collect problems for each fault object and obtain various historical fault problems of each fault object.

[0043] Specifically, the fault problems of all fault levels of aircraft engines are collected to determine the historical fault problems so that the knowledge of the fault problems can be transformed later. For example, the whole machine level faults include: engine vibration, engine surge, etc.; component / system faults include: wear, oil leakage, fracture, jamming and other fault modes; component level faults include: blade fracture, peeling, etc.

[0044] In a possible implementation manner, after converting the historical fault data to obtain fault knowledge corresponding to the historical fault problem, the method further includes: Based on the fault objects and fault knowledge corresponding to historical fault problems, a fault knowledge base of aircraft engines is constructed.

[0045] Specifically, in this embodiment, a fault knowledge base is constructed from two dimensions: fault knowledge and fault objects of aircraft engine research and development. The fault objects refer to all parts of the multiple fault levels mentioned above, which can also be understood as research and development objects. The fault objects and fault knowledge studied can be coded and given unique numbers so that the fault objects can be associated with the corresponding fault knowledge, thereby tracing the association between the two.

[0046] For example, the numbering format of "unit_model_four-digit serial number" can be used as the unique number of the fault object, and a serial number can be added before the numbering format of the fault object, such as "1_unit_model_four-digit serial number", as the unique number of the fault knowledge, so that the two can be searched accordingly. In this embodiment, the fault object and the fault knowledge can be stored in two data tables.

[0047] In a possible implementation manner, after determining the knowledge conversion result corresponding to the historical fault problem according to the fault knowledge and the preset knowledge conversion template, the method further includes: Based on the results of knowledge transformation, aircraft engines are developed and researched to determine the R&D process nodes, operating instructions, checklists and standard specifications of aircraft engines.

[0048] Specifically, the determined knowledge conversion results are applied to the research and development of aircraft engines, which can be reflected through the process nodes, inspection items, technical requirements, and precautions for use. The process node is the basic unit in the research and development process. The knowledge conversion results can increase, reduce or adjust the process nodes, thereby optimizing the research and development process; the inspection items are the review content of whether the research and development results and requirements of the fault objects at each fault level meet the requirements; the technical requirements are the technical content and requirements proposed in the research and development process; the precautions are the content that needs to be paid attention to in the research and development process. According to the knowledge conversion results, the research and development process nodes of the corresponding fault objects in the research and development process can be determined, and the functions of the fault objects can be clarified; the work instructions can be determined to explain in detail the specific tasks of a business activity involved in the fault object, and obtain the specific operation requirements, basic principles and methods, operation steps and verification methods of each task; determine the combination of inspection items set for the research and development process nodes in the checklist; determine the standard specifications to follow the business criteria and results in the research and development process.

[0049] In a possible implementation manner, after determining the knowledge conversion result corresponding to the historical fault problem according to the fault knowledge and the preset knowledge conversion template, the method further includes: Obtain the fault problem of the aircraft engine; if the fault knowledge corresponding to the fault problem is found in the fault knowledge base, handle the fault problem according to the fault knowledge.

[0050] Specifically, in the process of developing aircraft engines and using knowledge transformation results, the fault problem or the fault object being developed can be determined, and the corresponding fault knowledge can be searched in the pre-built fault knowledge base. If found, the fault problem can be handled according to the corresponding fault knowledge.

[0051] If the fault knowledge corresponding to the fault problem is not found in the fault knowledge base, the fault problem is extracted to determine the fault data; the fault data is transformed to obtain the fault knowledge corresponding to the fault problem, and the fault knowledge base is updated according to the fault knowledge.

[0052] Specifically, if the corresponding fault knowledge is not found in the fault knowledge base, it means that the relevant fault knowledge is not recorded in the fault knowledge base at this time. Then, data extraction and knowledge transformation can be performed on the fault problem to obtain the corresponding fault knowledge, and the fault knowledge base can be updated to form a closed loop for the fault problem.

[0053] Figure 3 Another flow chart of a method for converting aircraft engine fault knowledge provided by the present disclosure. Figure 3 As shown, the method includes: S301: Obtain fault objects for all levels of aircraft engine development.

[0054] Specifically, a product decomposition structure of an aircraft engine is constructed to determine the fault levels of the aircraft engine, and then the fault objects of each fault level in the research and development process are determined.

[0055] S302: Determine the fault data of the fault object of the aircraft engine.

[0056] Specifically, various fault problems that occur in the development process of the aircraft engine are collected for the fault object, and the fault data corresponding to the fault problem is determined. In this embodiment, the fault data can be stored in the form of a table, and Table 1 is an example table of fault data.

[0057] Table 1 Fault data example table

[0058] S303: Perform knowledge conversion based on the fault data, determine the fault knowledge, and obtain the knowledge conversion result according to the preset template.

[0059] Specifically, based on the system engineering background environment model, it can be determined that the elements required for conversion processing include input data, control conditions and enabling conditions, that is, the required fault data, so as to perform knowledge conversion and obtain fault knowledge, and obtain the knowledge conversion results according to the preset template for visualization. Fault knowledge includes precautions, methods and tools, and solution criteria for solving the same type of problems of historical fault problems.

[0060] For example, when designing a fuel nozzle, important characteristics should be clearly defined through XX and XX, and the important characteristic dimension XX should be used as an important control factor for manufacturing and acceptance to avoid XX, otherwise it is easy to cause XX failure.

[0061] S304: Enter the fault data and fault knowledge into the fault case library.

[0062] Specifically, by constructing a fault knowledge base from two dimensions, namely, fault knowledge and fault objects in aircraft engine research and development, the fault objects and fault knowledge under study can be encoded and assigned unique numbers so that the fault objects can be associated with the corresponding fault knowledge, thereby tracing the relationship between the two.

[0063] S305: Integrate knowledge transformation results into the R&D process.

[0064] Specifically, aircraft engines are developed based on the results of knowledge conversion, and the R&D process nodes, operating instructions, checklists and standard specifications of aircraft engines are determined, so as to be integrated into the R&D process.

[0065] Table 2 is a table of knowledge transformation results integrated into R&D process elements. As shown in Table 2, the table records fault knowledge, fault attribute information and R&D process elements.

[0066] Table 2. Knowledge transformation results integrated into R&D process elements

[0067] S306: Apply knowledge to transform results.

[0068] In the process of developing aircraft engines and using the results of knowledge transformation, the corresponding fault knowledge can be found in the pre-built fault knowledge base by determining the fault problem or the fault object being developed. If found, the fault problem can be handled according to the corresponding fault knowledge. If not found, knowledge transformation can be performed and the fault knowledge base can be updated.

[0069] Figure 4 The present invention provides a schematic diagram of the structure of a device for converting aircraft engine fault knowledge. Figure 4As shown, the device 400 includes: an acquisition module 410, an extraction module 420, a conversion module 430 and a determination module 440.

[0070] An acquisition module 410 is used to acquire historical fault problems of the aircraft engine; An extraction module 420 is used to extract the historical fault problem and obtain historical fault data corresponding to the historical fault problem, wherein the historical fault data includes fault attribute information and fault solution measures of the aircraft engine when the historical fault problem occurs; A conversion module 430 is used to convert the historical fault data to obtain fault knowledge corresponding to the historical fault problem, wherein the fault knowledge includes precautions, methods and tools, and solution criteria for solving the same type of problems as the historical fault problem; The determination module 440 is used to determine the knowledge conversion result corresponding to the historical fault problem according to the fault knowledge and a preset knowledge conversion template.

[0071] Optionally, the extraction module is used to: Based on the system engineering background environment model and the fault scenarios in the fault attribute information, the preset constraint control conditions and preset enabling conditions of the fault object of the aircraft engine are transformed and processed to obtain the fault knowledge, and the preset constraint control conditions include load conditions, operating conditions and test conditions.

[0072] Optionally, the acquisition module is used to: Acquire multiple fault levels of the aircraft engine; According to the plurality of fault levels, determining a plurality of fault objects of each of the fault levels; Problems are collected for each of the fault objects to obtain various types of historical fault problems of each of the fault objects.

[0073] Optionally, the device further comprises: After the historical fault data is transformed and processed to obtain the fault knowledge corresponding to the historical fault problem, a fault knowledge base of the aircraft engine is constructed based on the fault object and the fault knowledge corresponding to the historical fault problem.

[0074] Optionally, the device further comprises: After determining the knowledge conversion result corresponding to the historical fault problem according to the fault knowledge and the preset knowledge conversion template, the aircraft engine is developed based on the knowledge conversion result, and the R&D process nodes of the aircraft engine, the operating instructions of the aircraft engine, the inspection list of the aircraft engine and the standard specifications of the aircraft engine are determined.

[0075] Optionally, the device further comprises: After determining the knowledge conversion result corresponding to the historical fault problem according to the fault knowledge and the preset knowledge conversion template, the fault problem of the aircraft engine is obtained; If the fault knowledge corresponding to the fault problem is found in the fault knowledge base, the fault problem is processed according to the fault knowledge; If the fault knowledge corresponding to the fault problem is not found in the fault knowledge base, the fault problem is extracted to determine the fault data; the fault data is transformed to obtain the fault knowledge corresponding to the fault problem, and the fault knowledge base is updated according to the fault knowledge.

[0076] The present application also provides an electronic device to perform the above-mentioned method for converting aircraft engine fault knowledge. Figure 5 It shows a schematic diagram of an electronic device provided by some embodiments of the present application. Figure 5 As shown, the electronic device 50 includes: a processor 500, a memory 501, a bus 502 and a communication interface 503, wherein the processor 500, the communication interface 503 and the memory 501 are connected via the bus 502; the memory 501 stores a computer program that can be run on the processor 500, and when the processor 500 runs the computer program, the method for converting aircraft engine fault knowledge provided in any of the aforementioned embodiments of the present application is executed.

[0077] The memory 501 may include a high-speed random access memory (RAM), and may also include a non-volatile memory, such as at least one disk storage. The communication connection between the device network element and at least one other network element is realized through at least one communication interface 503 (which may be wired or wireless), and the Internet, wide area network, local area network, metropolitan area network, etc. may be used.

[0078] The bus 502 may be an ISA bus, a PCI bus, or an EISA bus, etc. The bus may be divided into an address bus, a data bus, a control bus, etc. The memory 501 is used to store programs, and the processor 500 executes the programs after receiving execution instructions. The method for converting aircraft engine fault knowledge disclosed in any implementation of the embodiment of the present application may be applied to the processor 500, or implemented by the processor 500.

[0079] The processor 500 may be an integrated circuit chip with signal processing capabilities. In the implementation process, each step of the above method can be completed by the hardware integrated logic circuit or software instructions in the processor 500. The above processor 500 can be a general-purpose processor, including a central processing unit (CPU), a network processor (NP), etc.; it can also be a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA) or other programmable logic devices, discrete gates or transistor logic devices, discrete hardware components. The methods, steps and logic block diagrams disclosed in the embodiments of the present application can be implemented or executed. The general-purpose processor can be a microprocessor or the processor can also be any conventional processor. The steps of the method disclosed in the embodiments of the present application can be directly embodied as a hardware decoding processor to be executed, or the hardware and software modules in the decoding processor can be executed. The software module can be located in a mature storage medium in the field such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory or an electrically erasable programmable memory, a register, etc. The storage medium is located in the memory 501, and the processor 500 reads the information in the memory 501 and completes the steps of the above method in combination with its hardware.

[0080] The electronic device provided in the embodiment of the present application and the method for converting aircraft engine fault knowledge provided in the embodiment of the present application are based on the same inventive concept and have the same beneficial effects as the methods adopted, operated or implemented therein.

[0081] An embodiment of the present application also provides a computer-readable storage medium corresponding to the method for converting aircraft engine fault knowledge provided in the aforementioned embodiment. The computer-readable storage medium shown therein may be a CD having a computer program stored thereon. When the computer program is run by a processor, it will execute the method for converting aircraft engine fault knowledge provided in any of the aforementioned embodiments.

[0082] It should be noted that examples of the computer-readable storage medium may also include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other optical or magnetic storage media, which are not listed here one by one.

[0083] The computer-readable storage medium provided in the above-mentioned embodiments of the present application and the method for converting aircraft engine fault knowledge provided in the embodiments of the present application are based on the same inventive concept and have the same beneficial effects as the methods adopted, run or implemented by the application programs stored therein.

[0084] The present application embodiment also provides a computer program product 600, such as Figure 6 The computer program product carries a computer program 601, and the instructions included in the program code can be used to execute the steps of the method for converting aircraft engine fault knowledge described in the above method embodiment. For details, please refer to the above method embodiment, which will not be repeated here.

[0085] The computer program product may be implemented in hardware, software or a combination thereof. In one optional embodiment, the computer program product is implemented as a computer storage medium. In another optional embodiment, the computer program product is implemented as a software product, such as a software development kit (SDK).

[0086] The basic principles of the present disclosure are described above in conjunction with specific embodiments. However, it should be noted that the advantages, strengths, effects, etc. mentioned in the present disclosure are only examples and not limitations, and it cannot be considered that these advantages, strengths, effects, etc. are required by each embodiment of the present disclosure. In addition, the specific details disclosed above are only for the purpose of illustration and ease of understanding, and are not limitations. The above details do not limit the present disclosure to the necessity of adopting the above specific details to be implemented.

[0087] The block diagrams of the devices, apparatuses, equipment, and systems involved in this disclosure are only illustrative examples and are not intended to require or imply that they must be connected, arranged, and configured in the manner shown in the block diagrams. As will be appreciated by those skilled in the art, these devices, apparatuses, equipment, and systems can be connected, arranged, and configured in any manner. Words such as "including", "comprising", "having", etc. are open words, referring to "including but not limited to", and can be used interchangeably with them. The words "or" and "and" used here refer to the words "and / or" and can be used interchangeably with them, unless the context clearly indicates otherwise. The word "such as" used here refers to the phrase "such as but not limited to", and can be used interchangeably with it.

[0088] Additionally, as used herein, "or" used in a list of items beginning with "at least one" indicates a separate list, so that, for example, a list of "at least one of A, B, or C" means A or B or C, or AB or AC or BC, or ABC (i.e., A and B and C). Furthermore, the word "exemplary" does not mean that the example described is preferred or better than other examples.

[0089] It should also be noted that in the system and method of the present disclosure, each component or each step can be decomposed and / or recombined. Such decomposition and / or recombination should be regarded as equivalent solutions of the present disclosure.

[0090] Various changes, substitutions, and modifications of the techniques described herein may be made without departing from the teachings defined by the appended claims. Furthermore, the scope of the claims of the present disclosure is not limited to the specific aspects of the processes, machines, manufactures, compositions of events, means, methods, and actions described above. Currently existing or later to be developed processes, machines, manufactures, compositions of events, means, methods, or actions that perform substantially the same functions or achieve substantially the same results as the corresponding aspects described herein may be utilized. Thus, the appended claims include such processes, machines, manufactures, compositions of events, means, methods, or actions within their scope.

[0091] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use the present disclosure. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein may be applied to other aspects without departing from the scope of the present disclosure. Therefore, the present disclosure is not intended to be limited to the aspects shown herein, but rather to the widest scope consistent with the principles and novel features disclosed herein.

[0092] The above description has been given for the purpose of illustration and description. In addition, this description is not intended to limit the embodiments of the present disclosure to the forms disclosed herein. Although multiple example aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, changes, additions and sub-combinations thereof.

Claims

1. A method for converting aircraft engine fault knowledge, characterized in that: include: Obtain historical failure issues of aircraft engines; Extracting the historical fault problems to obtain historical fault data corresponding to the historical fault problems, wherein the historical fault data includes fault attribute information and fault resolution measures of the aircraft engine when the historical fault problems occur; The historical fault data is transformed to obtain fault knowledge corresponding to the historical fault problem, wherein the fault knowledge includes precautions, methods and tools, and solution criteria for solving the same type of problems as the historical fault problem; According to the fault knowledge and a preset knowledge conversion template, a knowledge conversion result corresponding to the historical fault problem is determined.

2. The method according to claim 1, characterized in that The converting and processing the historical fault data to obtain the fault knowledge corresponding to the historical fault problem includes: Based on the system engineering background environment model and the fault scenarios in the fault attribute information, the preset constraint control conditions and preset enabling conditions of the fault object of the aircraft engine are transformed and processed to obtain the fault knowledge, and the preset constraint control conditions include load conditions, operating conditions and test conditions.

3. The method according to claim 1, characterized in that The problem of obtaining historical failures of aircraft engines includes: Acquire multiple fault levels of the aircraft engine; According to the plurality of fault levels, determining a plurality of fault objects of each of the fault levels; Problems are collected for each of the fault objects to obtain various types of historical fault problems of each of the fault objects.

4. The method according to claim 3, characterized in that After converting the historical fault data to obtain fault knowledge corresponding to the historical fault problem, the method further includes: A fault knowledge base of the aircraft engine is constructed based on the fault object and the fault knowledge corresponding to the historical fault problem.

5. The method according to claim 1, characterized in that After determining the knowledge conversion result corresponding to the historical fault problem according to the fault knowledge and the preset knowledge conversion template, the method further includes: Based on the knowledge conversion result, the aircraft engine is developed and researched, and the research and development process nodes of the aircraft engine, the operating instructions and specifications of the aircraft engine, the inspection list of the aircraft engine and the standard specifications of the aircraft engine are determined.

6. The method according to claim 4, characterized in that After determining the knowledge conversion result corresponding to the historical fault problem according to the fault knowledge and the preset knowledge conversion template, the method further includes: Obtain aircraft engine failure issues; If the fault knowledge corresponding to the fault problem is found in the fault knowledge base, the fault problem is processed according to the fault knowledge; If the fault knowledge corresponding to the fault problem is not found in the fault knowledge base, the fault problem is extracted to determine the fault data; the fault data is transformed to obtain the fault knowledge corresponding to the fault problem, and the fault knowledge base is updated according to the fault knowledge.

7. A device for converting aircraft engine fault knowledge, characterized in that: include: Acquisition module, used to obtain historical fault problems of aircraft engines; An extraction module, used to extract the historical fault problems and obtain historical fault data corresponding to the historical fault problems, wherein the historical fault data includes fault attribute information and fault resolution measures of the aircraft engine when the historical fault problems occur; A conversion module, used to convert the historical fault data to obtain fault knowledge corresponding to the historical fault problem, wherein the fault knowledge includes precautions, methods and tools, and solution criteria for solving the same type of problems as the historical fault problem; The determination module is used to determine the knowledge conversion result corresponding to the historical fault problem according to the fault knowledge and a preset knowledge conversion template.

8. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: The processor runs the computer program to implement the method according to any one of claims 1 to 6.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: The program is executed by a processor to implement the method according to any one of claims 1 to 6.

10. A computer program product, characterized in that The invention comprises a computer-readable code, or a non-volatile computer-readable storage medium carrying the computer-readable code. When the computer-readable code runs in a processor of an electronic device, the processor in the electronic device executes the method as claimed in any one of claims 1 to 6.

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