CN103728965A - Monitoring device and method for aircraft engine and FADEC system - Google Patents
Monitoring device and method for aircraft engine and FADEC system Download PDFInfo
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- CN103728965A CN103728965A CN201210389070.1A CN201210389070A CN103728965A CN 103728965 A CN103728965 A CN 103728965A CN 201210389070 A CN201210389070 A CN 201210389070A CN 103728965 A CN103728965 A CN 103728965A
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Abstract
The invention discloses a monitoring device and method for an aircraft engine and an FADEC system. A signal collection device of the monitoring device is used for collecting state parameters of the aircraft engine in real time and transmitting the state parameters to a health management device. The health management device is used for analyzing and processing the state parameters in real time, evaluating the health state of the aircraft engine and forecasting the service life of engine components. The monitoring device and method for the aircraft engine and the FADEC system can monitor the work state of the engine in real time, automatically locate the components breaking down, forecast potential faults, submit diagnosis and forecast reports, offer the maintenance advice, provide perfect health management service, improve the reliability of an engine control system, achieve on-condition maintenance and lower the maintenance cost of the engine.
Description
Technical field
The present invention relates to engine monitoring device technical field, relate in particular to a kind of monitoring arrangement of aeromotor and method, FADEC system.
Background technology
Along with the development of aero engine technology, aero-engine performance strengthens gradually, structure is day by day complicated, and these have all increased the depth & wideth that engine condition monitors and manages.In addition, aeromotor operation and maintenance cost are high, and maintenance theory is from the safeguarding to the condition based maintenance direction transformation of pressing reliability requirement by life-span or state of the art of past, newly safeguard that the substantive requirements of form carry out reliable Evaluation and Prediction to each stage engine condition.These requirements have determined EHMS(Engine Health Management System: engine is health management system arranged) two main applications: 1, guarantee engine healthy and stable work, improve flight safety; 2, by engine and unit failure are diagnosed and life prediction, the operation of synthesise various resource management engine, the maintenance cost of reduction engine.
At present, the airborne EHMS function of existing scheme is integrated in EEC(Electronic Engine Control: electronic engine control) realize in system, can realize the status surveillance function to systems such as gas circuit, combustion/lubricating oil.The control function of EEC relatively, health control task rank is lower, and practical function is comparatively simple.Therefore, cannot meet the demand of health control and the life prediction of the big-block engine that complexity is higher.Existing another kind of scheme is for being used independently RCU(Remote Collection Unit: long range acquisition unit) realize the collection of monitoring data, but it does not realize the local storage of large capacity monitoring data, fault diagnosis functions, cannot realize the comprehensive health monitoring of engine and management.
Summary of the invention
In view of this, the technical matters that the present invention will solve is to provide a kind of monitoring arrangement of aeromotor, for a kind of, can realize the status surveillance of engine and the device of health management function.
A monitoring arrangement for aeromotor, comprising: signal pickup assembly, for the state parameter of Real-time Collection aeromotor, and sends to health controller by described state parameter; Health controller, for described state parameter is carried out to real-time analysis and processing, and by described state parameter input health forecast model, assesses the health status of described aeromotor in conjunction with historical data, and the life-span of engine components is predicted.
According to the monitoring arrangement of aeromotor of the present invention embodiment, further, described signal pickup assembly comprises: engine signal collecting unit, for Real-time Collection, be arranged on the sensor signal on aeromotor parts, and obtain status information, failure message and flight parameter in electronic engine management system.
According to the monitoring arrangement of aeromotor of the present invention embodiment, further, described sensor signal comprises: air-channel system parameter, fuel system parameter, oil system parameter and vibration parameters; Signal Pretreatment unit, for described sensor signal being carried out to filtering, amplifying and process, and is converted to digital signal.
According to the monitoring arrangement of aeromotor of the present invention embodiment, further, described health controller comprises: abnormality detection unit, for described sensor signal is carried out to abnormality detection; Failure diagnosis unit, for locating the sensor that produces abnormal signal, by the signal input fault diagnostic model of Real-time Collection, and in conjunction with the status information in described electronic engine management system, failure message and flight parameter, carry out association analysis, engine components are carried out to fault diagnosis, and according to the ordering rule setting in advance, abnormal and fault are sorted; Or, anomaly parameter is sent to ground maintenance terminal or ground EHMS analyzes, and obtains analysis result; Health evaluating unit, for the abnormal or fault according to the result real-time assessment of failure diagnosis unit output; By health forecast model to occur one or the engine components of secondary failure carry out life appraisal and prediction; Statement-of-health generates and indicating member, for generating statement-of-health, if there is abnormal or fault, sends alarm signal, and for described abnormal or alarm generation maintenance suggestion.
According to the monitoring arrangement of aeromotor of the present invention embodiment, further, the fault of engine components is divided into Pyatyi, and level fault is miniature fault, and component capabilities reduces by 10%; Secondary failure is small-sized fault, and component capabilities reduces by 20%; Three grades of faults are medium-sized fault, and component capabilities reduces by 30%; Level Four fault is large-scale fault, and component capabilities reduces by 40%; Pyatyi fault is huge fault, and component capabilities reduces more than 50%.
According to the monitoring arrangement of aeromotor of the present invention embodiment, further, communicator carries out data interaction by communication bus and airplane synthetic management system, EEC, ground maintenance terminal and ground EHMS.
According to the monitoring arrangement of aeromotor of the present invention embodiment, further, described communicator sends to described airplane synthetic management system, EEC, ground maintenance terminal or ground EHMS by the state parameter of engine, abnormal, fault, described statement-of-health or maintenance suggestion.
According to the monitoring arrangement of aeromotor of the present invention embodiment, further, also comprise: data storage device, for storing the state parameter of described engine, abnormal and fault log; Described state parameter comprises: engine parameter service time, engine behavior parameter and engine operation environmental parameter.
The technical matters that the present invention will solve is to provide a kind of FADEC system of aeromotor, comprises the monitoring arrangement of aeromotor as above.
The technical matters that the present invention will solve is to provide a kind of supervision method of aeromotor, can monitor the state of engine and carry out health control.
A supervision method for aeromotor, comprising: the state parameter of signal pickup assembly Real-time Collection aeromotor, and described state parameter is sent to health controller; Health controller carries out real-time analysis and processing to described state parameter, and by described state parameter input health forecast model, assesses the health status of described aeromotor in conjunction with historical data, and the life-span of engine components is predicted.
According to an embodiment of the supervision method of aeromotor of the present invention, further, described signal pickup assembly Real-time Collection is arranged on the sensor signal on aeromotor parts, and obtains status information, failure message and flight parameter in electronic engine management system.
According to an embodiment of the supervision method of aeromotor of the present invention, further, described sensor signal comprises: air-channel system parameter, fuel system parameter, oil system parameter and vibration parameters; Described signal pickup assembly carries out filtering, amplifies and process described sensor signal, and is converted to digital signal.
According to an embodiment of the supervision method of aeromotor of the present invention, further, described health controller carries out abnormality detection to described sensor signal, there is abnormal sensor in location, by the signal input fault diagnostic model of Real-time Collection, and in conjunction with the status information in described electronic engine management system, failure message and flight parameter, carry out association analysis, engine components are carried out to fault diagnosis, and according to the ordering rule setting in advance, abnormal and fault are sorted; Or, anomaly parameter is sent to ground maintenance terminal or ground EHMS analyzes, and obtains analysis result; Described health controller carries out the order of severity of real-time assessment fault according to the result of failure diagnosis unit output, by health forecast model to occur one or the engine components of secondary failure carry out life appraisal and prediction; Described health controller generates statement-of-health, if there is abnormal or fault, sends alarm signal, and for described abnormal or alarm generation maintenance suggestion.
According to an embodiment of the supervision method of aeromotor of the present invention, further, the fault of engine components is divided into Pyatyi, and level fault is miniature fault, and component capabilities reduces by 10%; Secondary failure is small-sized fault, and component capabilities reduces by 20%; Three grades of faults are medium-sized fault, and component capabilities reduces by 30%; Level Four fault is large-scale fault, and component capabilities reduces by 40%; Pyatyi fault is huge fault, and component capabilities reduces more than 50%.
According to an embodiment of the supervision method of aeromotor of the present invention, further, described communicator carries out the mutual of data by communication bus and aircraft, EEC, ground maintenance terminal and ground EHMS; Wherein, described communicator sends to described aircraft, EEC, ground maintenance terminal or ground EHMS by the state parameter of engine, abnormal, fault, statement-of-health or maintenance suggestion.
The monitoring arrangement of aeromotor of the present invention and method can be carried out real time monitoring to engine behavior, and the parts that broken down in location automatically are also predicted potential fault, submit diagnosis and prediction address to, provide maintenance suggestion, realize and look feelings maintenance.
Accompanying drawing explanation
In order to be illustrated more clearly in the embodiment of the present invention or technical scheme of the prior art, to the accompanying drawing of required use in embodiment or description of the Prior Art be briefly described below, apparently, accompanying drawing in the following describes is only some embodiments of the present invention, for those of ordinary skills, do not paying under the prerequisite of creative work, can also obtain according to these accompanying drawings other accompanying drawing.
Fig. 1 is according to the schematic diagram of the monitoring arrangement of aeromotor of the present invention embodiment;
Fig. 2 is according to the schematic diagram of signal pickup assembly in the monitoring arrangement of aeromotor of the present invention embodiment;
Fig. 3 is according to the schematic diagram of health controller in the monitoring arrangement of aeromotor of the present invention embodiment;
Fig. 4 is according to the process flow diagram of an embodiment of the supervision method of aeromotor of the present invention;
Fig. 5 is according to the process flow diagram of another embodiment of the supervision method of aeromotor of the present invention.
Embodiment
With reference to the accompanying drawings the present invention is described more fully, exemplary embodiment of the present invention is wherein described.Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is clearly and completely described, obviously, described embodiment is only the present invention's part embodiment, rather than whole embodiment.Based on the embodiment in the present invention, those of ordinary skills, not making the every other embodiment obtaining under creative work prerequisite, belong to the scope of protection of the invention.
Fig. 1 is according to the schematic diagram of the monitoring arrangement of aeromotor of the present invention embodiment.As shown in the figure, the monitoring arrangement 1 of aeromotor comprises: signal pickup assembly 11, health controller 12.The state parameter of signal pickup assembly 11 Real-time Collection aeromotors, and state parameter is sent to health controller 12.Health controller 12 carries out real-time analysis and processing to state parameter, the health status of assessment aeromotor, and the life-span of engine components is predicted.
According to one embodiment of present invention, in health controller 12, can set in advance health forecast model.Health forecast model can illustrate the contacting of health forecast object and its correlative factor, interdependent, change and the relation of motion, to there is the forecast model of setting up on the basis of certain more stable correlationship between a kind of more stable structure or phenomenon, the information parameter that namely comprehensive various approach obtains, carries out prediction certain precision, careful and estimates.Can set up multiple health forecast models for different engine components, also multiple health forecast Models Sets can be become to a health forecast model with the engine components of unified input, output interface.Data are inputted to health forecast model, in conjunction with historical data, can assess the health status of described aeromotor, and the life-span of the each parts of engine is predicted.
Health controller 12 carries out real-time analysis and processing to state parameter, and state parameter is inputted to health forecast model, assesses the health status of described aeromotor in conjunction with historical data, and the life-span of engine components is predicted.
According to one embodiment of present invention, communicator 13 carries out data interaction with device or the system of monitoring arrangement outside.For example, communicator 13 carries out data interaction with EEC3 and ground EHMS4 system.Communicator 13 also can carry out data interaction with airplane synthetic management system.Communication module 13 can guarantee the monitoring data that provides accurate, real-time, and important state supplemental characteristic, mantenance data etc. send to ground EHMS and maintenance system etc. when engine is moved.
According to one embodiment of present invention, monitoring arrangement 1 also can comprise data storage device 14.Data storage device 14 is stored the state parameter of engine, abnormal and fault log.State parameter comprises: engine parameter service time, engine behavior parameter and engine operation environmental parameter etc.The logical excess capacity NVM(Non-Volatile Memory of data storage device 14: nonvolatile memory) real-time storage engine health monitoring data, and can send as required engine health data.
The monitoring arrangement of aeromotor of the present invention can carry out real time monitoring to engine behavior, and the parts that broken down in location automatically are also predicted potential fault, submit diagnosis and prediction address to, provide maintenance suggestion, realizes and looks feelings maintenance.Utilization from the related data that monitors sensor special and control system etc., monitors the correlation behavior parameter of engine, when occurring that parameter transfinites, gives a warning in time to crew; Working condition to engine is diagnosed, and the health status of assessment engine, predicted the critical component life-span of engine, provides maintenance suggestion in good time.When finding that component working is abnormal, when inefficacy or fault, the service data of engine before and after record storage dependent event, and can put forward as required earthward EHMS or Support system and send event data and comprehensively analyze.
Fig. 2 is according to the schematic diagram of signal pickup assembly in the monitoring arrangement of aeromotor of the present invention embodiment.As shown in Figure 2: signal pickup assembly 21 comprises: engine signal collecting unit 211 and Signal Pretreatment unit 212.Engine signal collecting unit 211 Real-time Collections are arranged on the sensor signal on aeromotor parts, and obtain status information, failure message and flight parameter in electronic engine management system; Wherein, sensor signal comprises: air-channel system parameter, fuel system parameter, oil system parameter and vibration parameters; Signal Pretreatment unit 212 carries out filtering, amplifies and process sensor signal, and is converted to digital signal.
According to one embodiment of present invention, signal pickup assembly 21 consists of analog input Acquisition Circuit, switching value input Acquisition Circuit etc.Analog input Acquisition Circuit mainly completes the signal condition links such as the filtering, amplification of sensor input analog amount signal, realizes the standard handovers of physical signalling, then gathers by A/D link, is converted to the discernible quantity of information of digital processing unit.Switching value input circuit mainly completes disappearing of switching value input signal and trembles processing, shaping and sampling.Characterize the physical signalling of engine various state parameters, after filtering, send health control module to after signal condition, the conversion such as amplification.
Fig. 3 is according to the schematic diagram of health controller in the monitoring arrangement of aeromotor of the present invention embodiment.As shown in Figure 3, health controller 31 comprises: abnormality detection unit 311, failure diagnosis unit 312, health evaluating unit 313, statement-of-health generate and indicating member 414.Abnormality detection unit 311 carries out abnormality detection to sensor signal.The abnormality detection that transfinites to engine air passage, engine combustion/oil system, engine luggine parameter can be realized in abnormality detection unit 311.
Failure diagnosis unit 312 is for locating the sensor that produces abnormal signal, by the signal input fault diagnostic model of Real-time Collection, and the status information in binding engine electronic control system, failure message and flight parameter, carry out association analysis, engine components are carried out to fault diagnosis, and according to the ordering rule setting in advance, abnormal and fault are sorted; Or, anomaly parameter is sent to ground maintenance terminal or ground EHMS analyzes, and obtains analysis result.
According to one embodiment of present invention, in failure diagnosis unit 312, can set in advance fault diagnosis model.The information parameter that the comprehensive various approach of fault diagnosis model obtain, carries out prediction certain precision, careful and estimates, carries out the diagnosis of fault.By data input fault diagnostic model, in conjunction with historical data, can judge whether breaking down of aeromotor.
According to one embodiment of present invention, the fault of engine components is divided into Pyatyi, and level fault is miniature fault, and component capabilities reduces by 10%, does not affect engine overall performance; Secondary failure is small-sized fault, and component capabilities reduces by 20%, does not affect engine overall performance; Three grades of faults are medium-sized fault, and component capabilities reduces by 30%, slight effect engine overall performance; Level Four fault is large-scale fault, and component capabilities reduces by 40%, has a strong impact on engine overall performance; Pyatyi fault is huge fault, and component capabilities reduces more than 50%, causes engine overall performance to be lost.
Health evaluating unit 313, according to the order of severity of the result real-time assessment fault of failure diagnosis unit output, carries out life forecast to engine components, and according to the ordering rule setting in advance, abnormal and fault is sorted.
According to an embodiment, health evaluating unit 313 is abnormal or fault according to the result real-time assessment of failure diagnosis unit output; By health forecast model to occur one or the engine components of secondary failure carry out life appraisal and prediction.According to an embodiment, also can carry out life prediction and assessment to the fault of other rank.
According to an embodiment, health evaluating unit 313 is when carrying out predicting and evaluating, can from airplane synthetic management system, ground EHMS and maintenance system, obtain the information such as empirical parameter, historical information, diagnostic model by communicator, also can from data storage device, obtain the information such as empirical parameter, historical information, diagnostic model.
Statement-of-health generates with indicating member 314 and generates statement-of-health, if there is abnormal or fault, sends alarm signal, and generates maintenance suggestion for abnormal or alarm.Statement-of-health generates with indicating member 314 also can provide aircraft cockpit to indicate required information (alarm of transfiniting), can generate statement-of-health and the maintenance suggestion for maintainer, checked.
According to one embodiment of present invention, health controller 31 is by high-performance CPU and coprocessor control.According to the information of the each parts of engine that collect, according to Gernral Check-up model, carry out real-time analysis and processing, the signal that transfinites is sent to alarm, and the life-span of engine critical component is predicted, form statement-of-health, combined analysis historical data provides maintenance suggestion in good time.
The monitoring arrangement collection of aeromotor of the present invention is arranged on the sensor signal on engine all parts, reads control sensor parameters, failure message and flight parameter from EEC and aircraft related system simultaneously; Need sensor to be processed is gathered to raw data and process, Condition Monitoring Unit Real-Time Monitoring and record various state parameters; While noting abnormalities, comprehensively other parameters are to abnormal confirmation or filtration, and carry out fault diagnosis, and last degree of confidence, severity, urgency according to abnormal and fault assessed the health of each system unit; And generate statement-of-health and submit to aircraft central authorities maintenance calculations machine, simultaneously by aircraft requirement, need the signal of alarm and state to be sent to aircraft warning system when abnormal.
According to one embodiment of present invention, motherboard in the monitoring arrangement of aeromotor of the present invention is realized the electric interconnection between each device, because existing high-frequency digital signal in monitoring arrangement has again millivolt level simulating signal, so answer emphasis to consider how to eliminate the interference between various signals in motherboard design process.
The control software of monitoring arrangement is realized the functions such as Power-On Self-Test, status surveillance, warning, fault diagnosis, failure prediction, engine life management, engine rotor equilibrium analysis.
Each device of monitoring arrangement and chassis design should be analyzed simulation result according to its heat, carry out rational thermal design, to obtain good radiating effect.
Structural strengthening design is carried out in the printed board of each device of monitoring arrangement, strengthens printed board non-deformability.According to the electromagnetic environment feature of engine, circuit board, structural member are carried out to electromagnetic Compatibility Design, guarantee monitoring arrangement reliably working in complex electromagnetic environment; The structural member of monitoring arrangement is used piece of refractory metal material design, guarantees the operating ambient temperature of its refractory temperature far above monitoring arrangement.
According to one embodiment of present invention, the FADEC(Full Authority Digital Electronic Control of aeromotor: full powers limits digital electronic controller) comprise aeromotor monitoring arrangement as above.Monitoring arrangement of the present invention is the course line field-replaceable unit in FADEC system.
Fig. 4 is according to the process flow diagram of an embodiment of the supervision method of aeromotor of the present invention.As shown in the figure, the supervision method of aeromotor comprises:
According to one embodiment of present invention, signal pickup assembly Real-time Collection is arranged on the sensor signal on aeromotor parts, and obtains status information, failure message and flight parameter in electronic engine management system; Wherein, sensor signal comprises: air-channel system parameter, fuel system parameter, oil system parameter and vibration parameters; Signal pickup assembly carries out filtering, amplifies and process sensor signal, and is converted to digital signal.
Fig. 5 is according to the process flow diagram of another embodiment of the supervision method of aeromotor of the present invention.As shown in the figure, the supervision method of aeromotor comprises:
According to an embodiment, health controller anomaly parameter can be sent to ground maintenance terminal or ground EHMS analyzes, and obtains analysis result.
The monitoring arrangement of aeromotor of the present invention and method can be aeromotor perfect Health management service are provided, and realize real time monitoring, health Evaluation, the life prediction of engine health status and the alarm of transfiniting; Realized the real-time storage of large capacity engine health data; Form engine statement-of-health and maintenance suggestion; Improve engine control system reliability; Feelings maintenance is looked in realization, reduces engine maintenance cost.
May realize in many ways method and system of the present invention.For example, can realize method and system of the present invention by any combination of software, hardware, firmware or software, hardware, firmware.The said sequence that is used for the step of method is only in order to describe, and the step of method of the present invention is not limited to above specifically described order, unless otherwise specified.In addition, in certain embodiments, can be also the program being recorded in recording medium by the invention process, these programs comprise the machine readable instructions for realizing the method according to this invention.Thereby the present invention also covers the recording medium of storing the program for carrying out the method according to this invention.
Description of the invention provides for example with for the purpose of describing, and is not exhaustively or limit the invention to disclosed form.Many modifications and variations are obvious for the ordinary skill in the art.Selecting and describing embodiment is for better explanation principle of the present invention and practical application, thereby and makes those of ordinary skill in the art can understand the present invention's design to be suitable for the various embodiment with various modifications of special-purpose.
Claims (14)
1. a monitoring arrangement for aeromotor, is characterized in that, comprising:
Signal pickup assembly, for the state parameter of Real-time Collection aeromotor, and sends to health controller by described state parameter;
Health controller, for described state parameter is carried out to real-time analysis and processing, and by described state parameter input health forecast model, assesses the health status of described aeromotor in conjunction with historical data, and the life-span of engine components is predicted.
2. monitoring arrangement as claimed in claim 1, is characterized in that, described signal pickup assembly comprises:
Engine signal collecting unit, is arranged on the sensor signal on aeromotor parts for Real-time Collection, and obtains status information, failure message and flight parameter in electronic engine management system;
Signal Pretreatment unit, for described sensor signal being carried out to filtering, amplifying and process, and is converted to digital signal.
3. monitoring arrangement as claimed in claim 2, is characterized in that:
Described sensor signal comprises: air-channel system parameter, fuel system parameter, oil system parameter and vibration parameters.
4. monitoring arrangement as claimed in claim 2, is characterized in that, described health controller comprises:
Abnormality detection unit, for carrying out abnormality detection to described sensor signal;
Failure diagnosis unit, for locating the sensor that produces abnormal signal, by the signal input fault diagnostic model of Real-time Collection, and in conjunction with the status information in described electronic engine management system, failure message and flight parameter, carry out association analysis, engine components are carried out to fault diagnosis, and according to the ordering rule setting in advance, abnormal and fault are sorted; Or, anomaly parameter is sent to ground maintenance terminal or ground EHMS analyzes, and obtains analysis result;
Health evaluating unit, for the abnormal or fault according to the result real-time assessment of failure diagnosis unit output; By health forecast model to occur one or the engine components of secondary failure carry out life appraisal and prediction;
Statement-of-health generates and indicating member, for generating statement-of-health, if there is abnormal or fault, sends alarm signal, and for described abnormal or alarm generation maintenance suggestion.
5. monitoring arrangement as claimed in claim 4, is characterized in that:
The fault of engine components is divided into Pyatyi, and level fault is miniature fault, and component capabilities reduces by 10%; Secondary failure is small-sized fault, and component capabilities reduces by 20%; Three grades of faults are medium-sized fault, and component capabilities reduces by 30%; Level Four fault is large-scale fault, and component capabilities reduces by 40%; Pyatyi fault is huge fault, and component capabilities reduces more than 50%.
6. monitoring arrangement as claimed in claim 4, is characterized in that, also comprises: communicator;
Described communicator carries out data interaction by communication bus and aircraft, EEC, ground maintenance terminal and ground EHMS;
Wherein, described communicator sends to described aircraft, EEC, ground maintenance terminal or ground EHMS by the state parameter of engine, abnormal, fault, described statement-of-health or maintenance suggestion.
7. monitoring arrangement as claimed in claim 4, is characterized in that, also comprises: data storage device, for storing the state parameter of described engine, abnormal and fault log;
Wherein, described state parameter comprises: engine parameter service time, engine behavior parameter and engine operation environmental parameter.
8. an aeromotor FADEC system, is characterized in that:
Comprise the monitoring arrangement of the aeromotor as described in claim 1 to 7 any one.
9. a supervision method for aeromotor, is characterized in that, comprising:
The state parameter of signal pickup assembly Real-time Collection aeromotor, and described state parameter is sent to health controller;
Health controller carries out real-time analysis and processing to described state parameter, and by described state parameter input health forecast model, assesses the health status of described aeromotor in conjunction with historical data, and the life-span of engine components is predicted.
10. supervision method as claimed in claim 9, is characterized in that:
Described signal pickup assembly Real-time Collection is arranged on the sensor signal on aeromotor parts, and obtains status information, failure message and flight parameter in electronic engine management system.
11. supervision methods as claimed in claim 10, is characterized in that:
Described sensor signal comprises: air-channel system parameter, fuel system parameter, oil system parameter and vibration parameters; Described signal pickup assembly carries out filtering, amplifies and process described sensor signal, and is converted to digital signal.
12. supervision methods as claimed in claim 10, is characterized in that:
Described health controller carries out abnormality detection to described sensor signal, there is abnormal sensor in location, by the signal input fault diagnostic model of Real-time Collection, and in conjunction with the status information in described electronic engine management system, failure message and flight parameter, carry out association analysis, engine components are carried out to fault diagnosis, and according to the ordering rule setting in advance, abnormal and fault are sorted; Or, anomaly parameter is sent to ground maintenance terminal or ground EHMS analyzes, and obtains analysis result;
Described health controller carries out the order of severity of real-time assessment fault according to the result of failure diagnosis unit output, and by health forecast model to occur one or the engine components of secondary failure carry out life appraisal and prediction; Described health controller generates statement-of-health, if there is abnormal or fault, sends alarm signal, and for described abnormal or alarm generation maintenance suggestion.
13. supervision methods as claimed in claim 12, is characterized in that:
The fault of engine components is divided into Pyatyi, and level fault is miniature fault, and component capabilities reduces by 10%; Secondary failure is small-sized fault, and component capabilities reduces by 20%; Three grades of faults are medium-sized fault, and component capabilities reduces by 30%; Level Four fault is large-scale fault, and component capabilities reduces by 40%; Pyatyi fault is huge fault, and component capabilities reduces more than 50%.
14. supervision methods as claimed in claim 12, is characterized in that:
Communicator carries out the mutual of data by communication bus and aircraft, EEC, ground maintenance terminal and ground EHMS; Wherein, described communicator sends to described aircraft, EEC, ground maintenance terminal or ground EHMS by the state parameter of engine, abnormal, fault, statement-of-health or maintenance suggestion.
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