CN115617024A - Airborne PHM system based on FACE framework - Google Patents
Airborne PHM system based on FACE framework Download PDFInfo
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- CN115617024A CN115617024A CN202211610946.0A CN202211610946A CN115617024A CN 115617024 A CN115617024 A CN 115617024A CN 202211610946 A CN202211610946 A CN 202211610946A CN 115617024 A CN115617024 A CN 115617024A
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- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0218—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterised by the fault detection method dealing with either existing or incipient faults
- G05B23/0221—Preprocessing measurements, e.g. data collection rate adjustment; Standardization of measurements; Time series or signal analysis, e.g. frequency analysis or wavelets; Trustworthiness of measurements; Indexes therefor; Measurements using easily measured parameters to estimate parameters difficult to measure; Virtual sensor creation; De-noising; Sensor fusion; Unconventional preprocessing inherently present in specific fault detection methods like PCA-based methods
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Abstract
The application relates to the technical field of design of airborne systems, in particular to an airborne PHM system based on an FACE framework. The system comprises a fault diagnosis module, a fault diagnosis module and a fault diagnosis module, wherein the fault diagnosis module is used for carrying out fault diagnosis on received data; the state monitoring execution module is used for receiving airborne monitoring data through the data adaptation module; the ground test execution module is used for starting auxiliary diagnosis on the received request data transmitted by the fault diagnosis module or the data adaptation module; the software and hardware configuration management execution module is used for starting configuration management operation on the received request data transmitted by the fault diagnosis module or the data adaptation module; the comprehensive data processing module is used for recording historical operation data of the airborne PHM system; and the data adaptation module is used for mutually converting the data of the module inside the airborne PHM system and the data of the operating system outside the airborne PHM system. The method and the device effectively improve the software development capability of the airborne PHM system and the efficiency of engineering application operation in the aircraft.
Description
Technical Field
The application belongs to the technical field of airborne system design, and particularly relates to an airborne PHM system based on an FACE framework.
Background
The complexity of design and development of an aircraft onboard PHM system is continuously improved, the function and complexity of onboard PHM system software are also continuously increased, the function requirements of an engineering onboard PHM system cannot be met by functions such as single fault rule reasoning, diagnosis knowledge base and the like, and the functions of expanding a multi-type composite fault diagnosis method and matched state monitoring, ground testing, software and hardware configuration management and the like are urgently needed. Meanwhile, as next generation airborne software environment architecture (FACE) is continuously popularized and applied, the airborne PHM system software needs to be designed on the basis of satisfying the FACE architecture. The main purpose of the FACE architecture is to improve the portability and reusability of aviation software on different software and hardware target platforms, standardize the business process and promote the development of reusable functional components between different architectures. Therefore, the FACE architecture particularly focuses on software function point separation decoupling and software function reuse, a five-layer framework structure comprising an operating system, I/O service, specific platform service (PSS), transmission service (TSS) and portable components is designed based on layered decoupling, the research and development integration difficulty and cost reduction of the whole layer of the aircraft equipment can be realized based on the target, but standard layers or interfaces of the FACE architecture design need to be docked in the development process of the airborne equipment software, the design complexity of specific airborne equipment software is improved, particularly, the airborne PHM system software needs to perform information interaction with various systems or components of the aircraft in the actual engineering application process, and the realization difficulty of the airborne PHM system software design is increased sharply.
Disclosure of Invention
In order to solve at least one of the technical problems, the invention designs an airborne PHM system based on a FACE architecture, and solves the problems that the software of an engineering airborne PHM system is complex to develop and is difficult to maintain and the like.
The application provides an airborne PHM system based on a FACE architecture,
the onboard PHM system performs data interaction with an operating system formed by a FACE architecture in the form of a portable component in the FACE architecture, and comprises:
the fault diagnosis module is used for carrying out fault diagnosis on the received data, sending the diagnosis result to the comprehensive data processing module and outputting the diagnosis result to the outside through the data adaptation module;
the state monitoring execution module continuously operates and is used for receiving airborne monitoring data through the data adaptation module, sending the monitored abnormal data to the fault diagnosis module and carrying out fault diagnosis through the fault diagnosis module;
the ground test execution module is used for starting auxiliary diagnosis on the received request data transmitted by the fault diagnosis module or the data adaptation module and sending an auxiliary diagnosis execution result to the fault diagnosis module and the data adaptation module;
the software and hardware configuration management execution module is used for starting configuration management operation on the received request data transmitted by the fault diagnosis module or the data adaptation module;
the comprehensive data processing module is used for recording historical operating data of the airborne PHM system and calling the fault diagnosis module when fault diagnosis is carried out; and
and the data adaptation module is used for mutually converting data used by the fault diagnosis execution module, the state monitoring execution module, the ground test execution module, the software and hardware configuration management execution module and the comprehensive data processing module in the airborne PHM system and data of an operating system outside the airborne PHM system.
Preferably, the fault diagnosis module comprises four fault diagnosis methods, namely a rule-based fault diagnosis method, a case-based fault diagnosis method, a life prediction early warning method and an intelligent health assessment method, and is configured to trigger operation based on data events and used for sequentially executing the four fault diagnosis methods on received data.
Preferably, the fault diagnosis module is further configured to request the integrated data processing module to call historical data of a set time period in the course of executing a life prediction-based early warning method or an intelligent health assessment-based method.
Preferably, the fault diagnosis module is further configured to send request data for assisting in completing the test by the surface equipment to the surface test execution module in the process of executing the fault diagnosis.
Preferably, the ground test execution module, after receiving the request data transmitted by the fault diagnosis module or the data adaptation module, further determines test information corresponding to the request data based on the ground test configuration data, and starts auxiliary diagnosis based on the test information.
Preferably, the data adaptation module includes a data partition processing unit for dividing the received data into electronic area data, control area data, mechanical area data, and power area data.
Preferably, the onboard PHM system further includes configuration data, where the configuration data includes fault diagnosis configuration data for instructing the fault diagnosis module to execute, status monitoring configuration data for instructing the status monitoring execution module to execute, ground test configuration data for instructing the ground test execution module to execute, and software and hardware configuration management configuration data for instructing the software and hardware configuration management execution module to execute.
Preferably, the data adaptation module includes an operating system service interface and a data transmission service interface meeting the FACE architecture requirements, and the operating system service interface provides basic file operation and runtime operation for the airborne PHM system; the data transmission service interface provides data input and output operation for the airborne PHM system.
The application provides a multi-type composite fault diagnosis method and a matched health management function, and effectively improves the development capability of airborne PHM system software and the efficiency of engineering application operation in an aircraft.
Drawings
Fig. 1 is a system architecture diagram of an embodiment of an onboard PHM system based on FACE architecture according to the present application.
Fig. 2 is an enlarged schematic view of a part a of the embodiment shown in fig. 1 of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making creative efforts shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The present application provides an airborne PHM system based on a FACE architecture, as shown in fig. 1 and 2, the airborne PHM system performs data interaction with an operating system formed by the FACE architecture in the form of a portable component in the FACE architecture, and the airborne PHM system includes:
the fault diagnosis module is used for carrying out fault diagnosis on the received data, sending the diagnosis result to the comprehensive data processing module and outputting the diagnosis result to the outside through the data adaptation module;
the state monitoring execution module continuously operates and is used for receiving airborne monitoring data through the data adaptation module, sending the monitored abnormal data to the fault diagnosis module and carrying out fault diagnosis through the fault diagnosis module;
the ground test execution module is used for starting auxiliary diagnosis on the received request data transmitted by the fault diagnosis module or the data adaptation module and sending an auxiliary diagnosis execution result to the fault diagnosis module and the data adaptation module;
the software and hardware configuration management execution module is used for starting configuration management operation on the received request data transmitted by the fault diagnosis module or the data adaptation module;
the comprehensive data processing module is used for recording historical operating data of the airborne PHM system and calling the fault diagnosis module when fault diagnosis is carried out; and
and the data adaptation module is used for mutually converting data used by the fault diagnosis execution module, the state monitoring execution module, the ground test execution module, the software and hardware configuration management execution module and the comprehensive data processing module in the airborne PHM system and data of an operating system outside the airborne PHM system.
In some optional embodiments, the fault diagnosis module includes four fault diagnosis methods, namely a rule-based fault diagnosis method, a case-based fault diagnosis method, a life prediction-based early warning method and an intelligent health assessment method, and is configured to trigger operation based on a data event, and is configured to sequentially execute the four fault diagnosis methods on received data.
In the embodiment, the fault diagnosis execution module is configured to provide a composite fault diagnosis method, including a rule-based fault diagnosis method, a case-based fault diagnosis method, a life prediction early warning method and an intelligent health assessment method, the modules acquire execution logic by loading configuration data corresponding to each method, execute the execution logic in sequence based on the scheduling of the modules, trigger the operation of the modules based on data events, start the fault diagnosis method after receiving data transmitted by the data adaptation module and other modules, and sequentially perform rule, case, life prediction early warning and intelligent health assessment operations; taking an aircraft engine part as an example, periodically sending data to a fault diagnosis execution module through a data adaptation module, performing rule diagnosis after the module receives the data, stopping if no abnormity is found on the rule or operation needing further diagnosis is required, calling a corresponding fault diagnosis conclusion if abnormity is found, and simultaneously determining whether to perform operations such as case, life prediction early warning, intelligent health assessment and the like according to the rule until the diagnosis process is finished.
In some optional embodiments, the fault diagnosis module is further configured to request the integrated data processing module to invoke historical data for a set period of time during execution of the life prediction based early warning method or the intelligent health assessment based method.
In the embodiment, the life prediction early warning and the intelligent health assessment can read part of historical data stored by the comprehensive data processing module to complete more accurate diagnosis operation in a matching manner under the condition of requirement, generally, methods such as the life prediction early warning and the intelligent health assessment need to be combined with a period of historical data to realize a diagnosis result, and the fault diagnosis process of the method is realized by reading the stored historical data.
In some optional embodiments, the fault diagnosis module is further configured to, during the performing of the fault diagnosis, send request data for assistance in completing the test by the surface equipment to the surface test performing module.
In the embodiment, the fault diagnosis execution module can send request data to the ground test execution module and the software and hardware configuration management execution module, taking an aircraft engine part as an example, when PHM software executes rule fault diagnosis before the aircraft takes off to find that the engine parameter is abnormal, the request data can be sent to the ground test execution module, the ground test execution module sends instruction data of the engine ground test through the data adaptation module after receiving the request, the engine completes the ground test in a matching way, and a test result is returned through the data adaptation module to assist in completing the fault diagnosis process. And the diagnosis result of the fault diagnosis execution module is output through the data adaptation module and is stored in the comprehensive data processing module.
The system comprises a state monitoring execution module, a ground test execution module and a software and hardware configuration management execution module, wherein the state monitoring execution module, the ground test execution module and the software and hardware configuration management execution module are configured to provide a matching function for a fault diagnosis execution module; the state monitoring execution module is always operated in the operation process, receives airborne monitoring data through the data adaptation module, judges the airborne monitoring data in real time according to state monitoring configuration data, transmits abnormal data to the fault diagnosis execution module to start fault diagnosis if the airborne monitoring data is abnormal, and simultaneously stores and records the abnormal data to the comprehensive data processing module; the ground test execution module is triggered to operate based on the data event, starts execution after receiving request data transmitted by the fault diagnosis module or the data adaptation module, loads test information corresponding to the request data in ground test configuration data, executes a test, acquires a result, sends the result to the fault diagnosis module and the data adaptation module, and simultaneously stores the result in the comprehensive data processing module; the software and hardware configuration management execution module is triggered to operate based on the data event, starts execution after receiving request data transmitted by the fault diagnosis module or the data adaptation module, loads information corresponding to the request data in the software and hardware configuration management configuration data, executes configuration management operation, acquires the configuration management data, sends the configuration management data to the module requesting the data, and simultaneously stores the configuration management data to the comprehensive data processing module.
The data adaptation module is configured to provide data transceiving service for the outside, deal with a data transmission interface provided by a FACE architecture, and process data for the inside into data content which can be used by the fault diagnosis execution module, the state monitoring execution module, the ground test execution module, the software and hardware configuration management execution module and the comprehensive data processing module; the data adaptation module cancels a data acquisition module which is generally designed by the traditional onboard PHM system software based on a non-FACE architecture, and receives data transmitted by all systems or equipment of the whole aircraft through a data transmission interface provided by the FACE architecture.
In some optional embodiments, the data adaptation module comprises a data partition processing unit for dividing the received data into electronic zone data, control zone data, mechanical zone data, and power zone data.
In the embodiment, the area-level PHM software which is generally designed under the traditional non-FACE-based architecture is omitted from the airborne PHM system, the area-level PHM software functions are all combined into the airborne PHM system software functions, the fact that the airborne PHM system software can receive original overall real-time data of the aircraft is guaranteed, the overall state of the aircraft is more real and effective, and fault diagnosis is carried out.
The comprehensive data processing module can store historical data snapshots of a period of time received by the data adaptation module, particularly can define the time required to be stored aiming at different types of data, and realizes different storage modes of different parameters; the module supports and stores diagnostic result data, state monitoring abnormal data, ground test result data and software and hardware configuration management data generated in the software operation process; meanwhile, the integrated data processing module supports other modules to read data.
In some optional embodiments, the onboard PHM system further comprises configuration data, wherein the configuration data comprises fault diagnosis configuration data for instructing the fault diagnosis module to perform, status monitoring configuration data for instructing the status monitoring execution module to perform, ground test configuration data for instructing the ground test execution module to perform, and software and hardware configuration management configuration data for instructing the software and hardware configuration management execution module to perform.
In this embodiment, the configuration data includes all PHM software execution logics, including fault association parameters, fault rules, fault cases, life prediction and early warning algorithms, intelligent health assessment algorithms, state monitoring association parameters, state monitoring criteria, ground test procedures, software and hardware configuration base tables, and the like; the modules of the software can normally run after being respectively loaded with the configuration data, and the execution logic is determined by the configuration file, so that the PHM software fault diagnosis related logic modification and upgrade only needs to replace the configuration data without modifying software codes, and the maintainability in the actual engineering application of the software is improved. Taking a life prediction early warning algorithm as an example, a prediction algorithm based on a time sequence can be configured; taking an intelligent health assessment algorithm as an example, the method can be configured into an inference model obtained after training through a large amount of historical data based on an artificial intelligent neural network algorithm or deep learning, along with accumulation of aircraft historical data and fault samples, a new inference model can be continuously trained and replaced, accuracy and reliability of fault diagnosis health assessment are increased, in order to save aircraft onboard computing power, training is generally set to be performed at a ground stage, and onboard PHM system software is not provided with an automatic learning and model updating function.
In some optional embodiments, the data adaptation module includes an operating system service interface and a data transmission service interface meeting FACE architecture requirements, where the operating system service interface provides basic file operation and runtime operation for the onboard PHM system; the data transmission service interface provides data input and output operation for the airborne PHM system.
It should be noted that the implementation manner of the functional components shown in the above embodiments may be hardware, software, firmware, or a combination thereof. When implemented in hardware, it may be, for example, an electronic circuit, an Application Specific Integrated Circuit (ASIC), suitable firmware, plug-in, function card, or the like. When implemented in software, the elements of the invention are the programs or code segments used to perform the required tasks. The program or code segments may be stored in a machine-readable medium or transmitted by a data signal carried in a carrier wave over a transmission medium or a communication link. A "machine-readable medium" may include any medium that can store or transfer information. Examples of a machine-readable medium include an electronic circuit, a semiconductor memory device, a ROM, a flash memory, an Erasable ROM (EROM), a floppy disk, a CD-ROM, an optical disk, a hard disk, an optical fiber medium, a Radio Frequency (RF) link, and so forth. The code segments may be downloaded via computer networks such as the internet, intranet, etc.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. An airborne PHM system based on a FACE architecture, which is characterized in that the airborne PHM system performs data interaction with an operating system formed by the FACE architecture in a form of a portable component in the FACE architecture, and comprises:
the fault diagnosis module is used for carrying out fault diagnosis on the received data, sending the diagnosis result to the comprehensive data processing module and outputting the diagnosis result to the outside through the data adaptation module;
the state monitoring execution module continuously operates and is used for receiving airborne monitoring data through the data adaptation module, sending the monitored abnormal data to the fault diagnosis module and carrying out fault diagnosis through the fault diagnosis module;
the ground test execution module is used for starting auxiliary diagnosis on the received request data transmitted by the fault diagnosis module or the data adaptation module and sending an auxiliary diagnosis execution result to the fault diagnosis module and the data adaptation module;
the software and hardware configuration management execution module is used for starting configuration management operation on the received request data transmitted by the fault diagnosis module or the data adaptation module;
the comprehensive data processing module is used for recording historical operation data of the onboard PHM system and calling the historical operation data when the fault diagnosis module carries out fault diagnosis; and
and the data adaptation module is used for mutually converting data used by the fault diagnosis execution module, the state monitoring execution module, the ground test execution module, the software and hardware configuration management execution module and the comprehensive data processing module in the airborne PHM system and data of an operating system outside the airborne PHM system.
2. The FACE architecture-based airborne PHM system of claim 1, wherein the fault diagnosis module comprises four fault diagnosis methods in total, namely a rule-based fault diagnosis method, a case-based fault diagnosis method, a life prediction-based early warning method and an intelligent health assessment method, and is configured to be triggered to operate based on data events for sequentially executing the four fault diagnosis methods on received data.
3. The FACE architecture-based on-board PHM system of claim 2, wherein the fault diagnosis module is further configured to request invocation of historical data for a set time period from the integrated data processing module in executing a life prediction based early warning method or an intelligent health assessment based method.
4. The FACE architecture-based onboard PHM system as recited in claim 2, wherein the troubleshooting module is further configured to transmit request data for a ground-based device-assisted completion test to the ground test execution module during the performing troubleshooting process.
5. The FACE architecture-based on-board PHM system of claim 1, wherein the ground test execution module, upon receiving the request data transmitted by the fault diagnosis module or the data adaptation module, further comprises determining test information corresponding to the request data based on ground test configuration data, and initiating auxiliary diagnosis based on the test information.
6. The FACE architecture-based on-board PHM system of claim 1, wherein the data adaptation module comprises a data partition processing unit for dividing the received data into electronic region data, control region data, mechanical region data, and power region data.
7. The FACE architecture-based airborne PHM system of claim 1, further comprising configuration data including fault diagnosis configuration data for instructing execution of the fault diagnosis module, status monitoring configuration data for instructing execution of the status monitoring execution module, ground test configuration data for instructing execution of the ground test execution module, and software and hardware configuration management configuration data for instructing execution of the software and hardware configuration management execution module.
8. The FACE architecture-based airborne PHM system as claimed in claim 1, wherein said data adaptation module comprises an operating system service interface and a data transmission service interface conforming to FACE architecture requirements, said operating system service interface providing basic file operation, runtime operation for said airborne PHM system; the data transmission service interface provides data input and output operation for the airborne PHM system.
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