CN103728965B - 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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- CN103728965B CN103728965B CN201210389070.1A CN201210389070A CN103728965B CN 103728965 B CN103728965 B CN 103728965B CN 201210389070 A CN201210389070 A CN 201210389070A CN 103728965 B CN103728965 B CN 103728965B
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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, more particularly, to a kind of monitoring arrangement of aero-engine and side
Method, FADEC system.
Background technology
With the development of aero engine technology, aero-engine performance gradually strengthens, structure is increasingly complicated, and these all increase
Engine condition supervision and the depth managing and range are added.Additionally, aero-engine runs and maintenance cost is high, safeguard reason
Read and safeguarded that new maintenance form will to the condition based maintenance direction transformation by reliability requirement from the past by life-span or state of the art
Ask and each stage engine condition is reliably assessed and predicts.These requirements determine EHMS（Engine Health
Management System：Electromotor is health management system arranged）Two main usess：1st, ensure the healthy and stable work of electromotor
Make, improve flight safety；2nd, by electromotor and component fault diagnosis and biometry, comprehensive each side resource management sends out
The operation of motivation, reduces the maintenance cost of electromotor.
At present, the airborne EHMS function of existing scheme is integrated in EEC（Electronic Engine Control：Electronics is sent out
Motivation controls）Realize in system, can achieve the Stateful Inspection function to systems such as gas circuit, combustion/lubricating oil.The control work(of EEC relatively
For energy, health control task rank is relatively low, realizes function relatively simple.Therefore, it is impossible to meet higher large-scale of complexity
The health control of motivation and the demand of biometry.Existing another kind scheme is using independent RCU（Remote
Collection Unit：Long range acquisition unit）Realize monitoring the collection of data, but it is not realized local Large Copacity and monitors
Data storage, fault diagnosis functions, cannot realize the comprehensive health monitoring of electromotor and management.
Content of the invention
In view of this, the invention solves the problems that a technical problem be that a kind of monitoring arrangement of aero-engine is provided, be
A kind of Stateful Inspection that can realize electromotor and the device of health management function.
A kind of monitoring arrangement of aero-engine, including：Signal pickup assembly, for the shape of Real-time Collection aero-engine
State parameter, and described state parameter is sent to health controller;Health controller, for carrying out to described state parameter
Analyze in real time and process, and described state parameter is inputted health forecast model, assess described aeroplane engine in conjunction with historical data
The health status of machine, and the life-span of engine components is predicted.
One embodiment of the monitoring arrangement of the aero-engine according to the present invention, further, described signals collecting dress
Put including：Engine signal collecting unit, is arranged on the sensor signal on aero-engine part for Real-time Collection, and obtains
Take status information in electronic engine management system, fault message and flight parameter.
One embodiment of the monitoring arrangement of the aero-engine according to the present invention, further, described sensor signal
Including：Air-channel system parameter, fuel system parameter, oil system parameter and vibration parameters；Signal Pretreatment unit, for institute
State sensor signal be filtered, processing and amplifying, and be converted to digital signal.
One embodiment of the monitoring arrangement of the aero-engine according to the present invention, further, described health control dress
Put including：Abnormality detecting unit, for carrying out abnormality detection to described sensor signal；Failure diagnosis unit, produces for positioning
The sensor of raw abnormal signal, by the signal input fault diagnosis model of Real-time Collection, and combines described engine electronic control system
Status information in system, fault message and flight parameter, are associated analyzing, carry out fault diagnosis to engine components, and
According to the ordering rule pre-setting, exception and fault are ranked up；Or, anomaly parameter is sent to ground maintenance terminal
Or ground EHMS is analyzed, and obtain analysis result；Health evaluating unit, for the result being exported according to failure diagnosis unit
Real-time assessment exception or fault；Life appraisal is carried out to the engine components one or secondary failure by health forecast model
And prediction；Statement-of-health generates and indicating member, for generating statement-of-health, then sends alarm letter if there is exception or fault
Number, and generate maintenance suggestion for described abnormal or alarm.
One embodiment of the monitoring arrangement of the aero-engine according to the present invention, further, the event of engine components
Barrier is divided into Pyatyi, and level fault is miniature fault, and component capabilities reduce by 10%；Secondary failure is mini fault, and component capabilities drop
Low by 20%；Three-level fault is medium-sized fault, and component capabilities reduce by 30%；Level Four fault is large-scale fault, and component capabilities reduce
40%；Pyatyi fault is huge fault, and component capabilities reduce by more than 50%.
One embodiment of the monitoring arrangement of the aero-engine according to the present invention, further, communicator passes through logical
News bus and airplane synthetic management system, EEC, ground maintenance terminal and ground EHMS carry out data interaction.
One embodiment of the monitoring arrangement of the aero-engine according to the present invention, further, described communicator will
The state parameter of electromotor, exception, fault, described statement-of-health or maintenance suggestion be sent to described airplane synthetic management system,
EEC, ground maintenance terminal or ground EHMS.
One embodiment of the monitoring arrangement of the aero-engine according to the present invention, further, also includes：Data storage
Device, for storing state parameter, exception and the fault log of described electromotor；Described state parameter includes：Electromotor uses
Time parameter, engine behavior parameter and engine operating environments parameter.
The invention solves the problems that a technical problem be the FADEC system that a kind of aero-engine is provided, including as above institute
The monitoring arrangement of the aero-engine stated.
The invention solves the problems that a technical problem be a kind of supervision method that aero-engine is provided, can monitor and start
The state of machine simultaneously carries out health control.
A kind of supervision method of aero-engine, including：The state ginseng of signal pickup assembly Real-time Collection aero-engine
Number, and described state parameter is sent to health controller;Health controller is analyzed in real time to described state parameter
And process, and described state parameter is inputted health forecast model, the health of described aero-engine is assessed in conjunction with historical data
State, and the life-span of engine components is predicted.
One embodiment of the supervision method of the aero-engine according to the present invention, further, described signals collecting dress
Put the sensor signal that Real-time Collection is arranged on aero-engine part, and obtain the state in electronic engine management system
Information, fault message and flight parameter.
One embodiment of the supervision method of the aero-engine according to the present invention, further, described sensor signal
Including：Air-channel system parameter, fuel system parameter, oil system parameter and vibration parameters；Described signal pickup assembly is to described
Sensor signal is filtered, processing and amplifying, and is converted to digital signal.
One embodiment of the supervision method of the aero-engine according to the present invention, further, described health control dress
Put and described sensor signal is carried out with abnormality detection, positioning occurs abnormal sensor, by the signal input fault of Real-time Collection
Diagnostic cast, and with reference to the status information in described electronic engine management system, fault message and flight parameter, be associated
Engine components are carried out fault diagnosis, and according to the ordering rule pre-setting, exception and fault are ranked up by analysis；Or
Person, anomaly parameter is sent to ground maintenance terminal or ground EHMS is analyzed, and obtain analysis result；Described health control
Device carries out the order of severity of real-time assessment fault according to the result that failure diagnosis unit exports, by health forecast model to going out
Existing one or the engine components of secondary failure carry out life appraisal and prediction；Described health controller generates statement-of-health, such as
Fruit exception or fault then sends warning signal, and generates maintenance suggestion for described abnormal or alarm.
One embodiment of the supervision method of the aero-engine according to the present invention, further, the event of engine components
Barrier is divided into Pyatyi, and level fault is miniature fault, and component capabilities reduce by 10%；Secondary failure is mini fault, and component capabilities drop
Low by 20%；Three-level fault is medium-sized fault, and component capabilities reduce by 30%；Level Four fault is large-scale fault, and component capabilities reduce
40%；Pyatyi fault is huge fault, and component capabilities reduce by more than 50%.
One embodiment of the supervision method of the aero-engine according to the present invention, further, described communicator leads to
Cross communication bus and carry out interacting of data with aircraft, EEC, ground maintenance terminal and ground EHMS；Wherein, described communicator will
The state parameter of electromotor, exception, fault, statement-of-health or maintenance suggestion are sent to described aircraft, EEC, ground maintenance terminal
Or ground EHMS.
The monitoring arrangement of the aero-engine of the present invention and method can be monitored in real time to engine behavior, from
Part that dynamic positioning has broken down simultaneously predicts potential fault, submits diagnosis and prediction address to, provides maintenance suggestion, realizes regarding
Feelings are keeped in repair.
Brief description
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
Have technology description in required use accompanying drawing be briefly described it should be apparent that, drawings in the following description are only
Some embodiments of the present invention, for those of ordinary skill in the art, without having to pay creative labor, also
Other accompanying drawings can be obtained according to these accompanying drawings.
Fig. 1 is the schematic diagram of an embodiment of the monitoring arrangement of the aero-engine according to the present invention；
Fig. 2 be the monitoring arrangement of the aero-engine according to the present invention an embodiment in signal pickup assembly signal
Figure；
Fig. 3 be the monitoring arrangement of the aero-engine according to the present invention an embodiment in health controller signal
Figure；
Fig. 4 is the flow chart of an embodiment of the supervision method of the aero-engine according to the present invention；
Fig. 5 is the flow chart of another embodiment of supervision method of the aero-engine according to the present invention.
Specific embodiment
With reference to the accompanying drawings the present invention is described more fully, the exemplary embodiment of the present invention is wherein described.Under
Face, by with reference to the accompanying drawing in the embodiment of the present invention, is clearly and completely described to the technical scheme in the embodiment of the present invention, shows
So, described embodiment is only a part of embodiment of the present invention, rather than whole embodiments.Based on the reality in the present invention
Apply example, the every other embodiment that those of ordinary skill in the art are obtained under the premise of not making creative work, all belong to
In the scope of protection of the invention.
Fig. 1 is the schematic diagram of an embodiment of the monitoring arrangement of the aero-engine according to the present invention.As illustrated, boat
The monitoring arrangement 1 of empty electromotor includes：Signal pickup assembly 11, health controller 12.Signal pickup assembly 11 Real-time Collection
The state parameter of aero-engine, and state parameter is sent to health controller 12.Health controller 12 is joined to state
Number is analyzed in real time and is processed, the health status of assessment aero-engine, and the life-span of engine components is predicted.
According to one embodiment of present invention, health controller 12 can pre-set health forecast model.Strong
Health forecast model can illustrate the relation of the contact, interdependent, change and motion of health forecast object factor associated therewith, is one
Plant the forecast model set up on the basis of there is between more stable structure or phenomenon certain more stable dependency relation, also
It is the information parameter that comprehensive various approach obtain, carry out certain precision, careful predicted estimate.Different starting can be directed to
Machine part sets up multiple health forecast models it is also possible to multiple health forecast model integrated are had unified input, defeated for one
The health forecast model of the engine components of outgoing interface.Enter data into health forecast model, in conjunction with historical data it can be estimated that
The health status of described aero-engine, and the life-span of each part of electromotor is predicted.
Signal pickup assembly 11 collection is arranged on the signal of sensor 2 on aero-engine part, and will collect
Sensor signal is sent to health controller 12 after being converted to the signal of telecommunication.
Health controller 12 is analyzed in real time to state parameter and is processed, and state parameter is inputted health forecast mould
Type, assesses the health status of described aero-engine, and the life-span of engine components is predicted in conjunction with historical data.
According to one embodiment of present invention, communicator 13 and the device outside monitoring arrangement or system carry out data friendship
Mutually.For example, communicator 13 and EEC3 and ground EHMS4 system carry out data interaction.Communicator 13 can also be comprehensive with aircraft
Close management system and carry out data interaction.Communication module 13 can ensure that offer is accurate, monitor data in real time, and electromotor is transported
During row, important state supplemental characteristic, mantenance data etc. are sent to ground EHMS and maintenance system etc..
According to one embodiment of present invention, monitoring arrangement 1 can also include data storage device 14.Data storage device
The state parameter of 14 storage electromotors, exception and fault log.State parameter includes：Electromotor use time parameter, electromotor
Working status parameter and engine operating environments parameter etc..Data storage device 14 passes through Large Copacity NVM（Non-Volatile
Memory：Nonvolatile memory）Real-time storage electromotor health monitoring data, and electromotor health number can be sent as needed
According to.
The monitoring arrangement of the aero-engine of the present invention can be monitored in real time to engine behavior, is automatically positioned
The part that broken down simultaneously predicts potential fault, submits diagnosis and prediction address to, provides maintenance suggestion, realizes regarding feelings dimension
Repair.Using from the related data monitoring sensor special and control system etc., the correlation behavior parameter of electromotor is supervised
Depending on when parameter-beyond-limit occurs, giving a warning to crew in time；The working condition of electromotor is diagnosed, assessment is sent out
The health status of motivation, were predicted to the critical component life-span of electromotor, provided maintenance suggestion in good time.When discovery component working
When exception, inefficacy or fault, before and after record storage dependent event, the service data of electromotor is it is possible to carry as needed earthward
EHMS or Support system send event data and carry out comprehensive analysis.
Fig. 2 be the monitoring arrangement of the aero-engine according to the present invention an embodiment in signal pickup assembly signal
Figure.As shown in Figure 2：Signal pickup assembly 21 includes：Engine signal collecting unit 211 and Signal Pretreatment unit 212.Start
Machine signal gathering unit 211 Real-time Collection is arranged on the sensor signal on aero-engine part, and obtains Motronic control maps
Status information in control system, fault message and flight parameter；Wherein, sensor signal includes：Air-channel system parameter, fuel oil
Systematic parameter, oil system parameter and vibration parameters；Signal Pretreatment unit 212 is filtered to sensor signal, at amplification
Reason, and be converted to digital signal.
According to one embodiment of present invention, signal pickup assembly 21 is by analog input Acquisition Circuit, On-off signal
Acquisition Circuit etc. is constituted.Analog input Acquisition Circuit mainly completes the letter such as the filtering of sensor input analog amount signal, amplification
Number conditioning link, realize the standard handovers of physical signalling, then be acquired by A/D link, being converted to digital processing unit can know
Other quantity of information.Switching value input circuit mainly completes disappearing of On-off signal signal and trembles process, shaping and sampling.Sign is started
The physical signalling of the various state parameter of machine, after filtering, amplify etc. signal condition, conversion after send health control module to.
Fig. 3 be the monitoring arrangement of the aero-engine according to the present invention an embodiment in health controller signal
Figure.As shown in figure 3, health controller 31 includes：Abnormality detecting unit 311, failure diagnosis unit 312, health evaluating unit
313rd, statement-of-health generates and indicating member 414.Abnormality detecting unit 311 carries out abnormality detection to sensor signal.Abnormal inspection
Survey unit 311 can realize to engine air passage, electromotor combustion/oil system, engine luggine parameter the abnormality detection that transfinites.
Failure diagnosis unit 312 is used for the sensor that positioning produces abnormal signal, by the signal input fault of Real-time Collection
Diagnostic cast, and combine status information in electronic engine management system, fault message and flight parameter, is associated point
Engine components are carried out fault diagnosis, and according to the ordering rule pre-setting, exception and fault are ranked up by analysis；Or
Person, anomaly parameter is sent to ground maintenance terminal or ground EHMS is analyzed, and obtain analysis result.
According to one embodiment of present invention, failure diagnosis unit 312 can pre-set fault diagnosis model.Therefore
The barrier diagnostic cast information parameter that comprehensively various approach obtain, carries out certain precision, careful predicted estimate, carries out fault
Diagnosis.Enter data into fault diagnosis model, in conjunction with historical data it can be determined that whether the breaking down of aero-engine.
According to one embodiment of present invention, the fault of engine components is divided into Pyatyi, and level fault is miniature fault, portion
Part performance reduces by 10%, does not affect electromotor overall performance；Secondary failure is mini fault, and component capabilities reduce by 20%, not shadow
Ring electromotor overall performance；Three-level fault is medium-sized fault, and component capabilities reduce by 30%, slight effect electromotor overall performance；
Level Four fault is large-scale fault, and component capabilities reduce by 40%, have a strong impact on electromotor overall performance；Pyatyi fault is huge event
Barrier, component capabilities reduce by more than 50%, lead to electromotor overall performance to be lost.
The order of severity of the result real-time assessment fault that health evaluating unit 313 exports according to failure diagnosis unit, to send out
Motivation part carries out life forecast, and according to the ordering rule pre-setting, exception and fault is ranked up.
According to an embodiment, the result real-time assessment that health evaluating unit 313 exports according to failure diagnosis unit is abnormal
Or fault；Life appraisal and prediction are carried out to the engine components one or secondary failure by health forecast model.According to
One embodiment is it is also possible to carry out biometry and assessment to the fault of other ranks.
According to an embodiment, health evaluating unit 313, can be by communicator from winged when being predicted and assess
Machine total management system, ground EHMS and maintenance system obtain the information such as empirical parameter, historical information, diagnostic cast it is also possible to
The information such as empirical parameter, historical information, diagnostic cast are obtained from data storage device.
Statement-of-health generates and generates statement-of-health with indicating member 314, then sends alarm letter if there is exception or fault
Number, and generate maintenance suggestion for abnormal or alarm.Statement-of-health generates can also provide aircraft cockpit with indicating member 314
Indicate required information（Transfinite alarm）, the statement-of-health checked for attendant and maintenance suggestion can be generated.
According to one embodiment of present invention, health controller 31 is by high-performance CPU and coprocessor control.According to adopting
The information of each part of electromotor collecting, is analyzed in real time according to Gernral Check-up model and is processed, signal is sent announcement to transfiniting
Alert, and the life-span of electromotor critical component is predicted, form statement-of-health, combined analysis historical data provides maintenance in good time
Suggestion.
The monitoring arrangement collection of the aero-engine of the present invention is arranged on the sensor signal on various engine components, with
When read control sensor parameters, fault message and flight parameter from EEC and aircraft related system；To need sensing to be processed
Device collection initial data is processed, Condition Monitoring Unit real-time monitoring and record various state parameters；When noting abnormalities, comprehensive
Other specification confirms or filters to abnormal, and carries out fault diagnosis, finally according to the confidence level of exception and fault, severity, tight
Anxious degree is estimated to the health of each system unit；And generate statement-of-health and submit to aircraft central maintenance computer, press simultaneously
Aircraft requirements, send needing the signal of alarm and state during exception to aircraft alerting system.
According to one embodiment of present invention, the motherboard in the monitoring arrangement of the aero-engine of the present invention realizes each dress
Electric interconnection between putting, because high-frequency digital signal existing in monitoring arrangement has millivolt level analogue signal again, so motherboard sets
Emphasis is answered to consider how to eliminate the interference between various signals during meter.
The control software of monitoring arrangement realizes Power-On Self-Test, Stateful Inspection, warning, fault diagnosis, failure predication, electromotor
The functions such as life-span management, engine rotor equilibrium analyses.
Each device of monitoring arrangement and frame design should carry out rational thermal design according to its heat analysis simulation result, with
Obtain excellent radiating effect.
The printed board of each device of monitoring arrangement carries out structural strengthening design, strengthens printed board non-deformability.According to send out
The electromagnetic environment feature of motivation is to circuit board, structural member carries out electromagnetic Compatibility Design it is ensured that monitoring arrangement is in complicated electromagnetism ring
Reliably working in border；The structural member of monitoring arrangement uses piece of refractory metal material design to monitor dress it is ensured that its refractory temperature is far above
The operating ambient temperature put.
According to one embodiment of present invention, the FADEC of aero-engine（Full Authority Digital
Electronic Control：Full Authority Digital electronic controller）Including aero-engine monitoring arrangement as above.The present invention's
Monitoring arrangement is the course line field-replaceable unit in FADEC system.
Fig. 4 is the flow chart of an embodiment of the supervision method of the aero-engine according to the present invention.As shown in the figure, navigate
The supervision method of empty electromotor includes：
Step 402, the state parameter of signal pickup assembly Real-time Collection aero-engine, and state parameter is sent to strong
Health managing device.
Step 403, health controller is analyzed in real time to state parameter and is processed, the health of assessment aero-engine
State, and the life-span of engine components is predicted.
According to one embodiment of present invention, signal pickup assembly Real-time Collection is arranged on the biography on aero-engine part
Sensor signal, and obtain status information in electronic engine management system, fault message and flight parameter；Wherein, sensor
Signal includes：Air-channel system parameter, fuel system parameter, oil system parameter and vibration parameters；Signal pickup assembly is to sensing
Device signal is filtered, processing and amplifying, and is converted to digital signal.
Fig. 5 is the flow chart of another embodiment of supervision method of the aero-engine according to the present invention.As shown in the figure,
The supervision method of aero-engine includes：
Step 502, the sensor signal of sensor Real-time Collection aero-engine, and state parameter is sent to health pipe
Reason device.
Step 503, judges whether sensor signal is abnormal；Then enter step 504 if there is abnormal, without appearance
Abnormal then normal termination；
Step 504, there is abnormal sensor in positioning, by the signal input fault diagnosis model of Real-time Collection, in conjunction with it
Its status information carries out fault diagnosis to engine components, and according to the ordering rule pre-setting, exception and fault is carried out
Sequence；
Step 505, obtains healthy historical data, by health forecast model to the engine portion one or secondary failure
Part carries out life appraisal and prediction.Life appraisal and prediction can also be carried out to the fault of other ranks；
Step 506, generates statement-of-health, then sends warning signal if there is exception or fault, and for abnormal or announcement
Alert generation keeps in repair suggestion；
According to an embodiment, anomaly parameter can be sent to ground maintenance terminal or ground EHMS by health controller
It is analyzed, and obtain analysis result.
The monitoring arrangement of the aero-engine of the present invention and method can provide perfect health control clothes for aero-engine
Business, realizes real-time supervision, health Evaluation, biometry and the alarm of transfiniting of electromotor health status；Achieve Large Copacity
The real-time storage of electromotor health data；Form electromotor statement-of-health and maintenance suggestion；Improve engine control system reliable
Property；Realize condition maintenarnce, reduce engine maintenance cost.
The method of the present invention and system may be achieved in many ways.For example, can by software, hardware, firmware or
Software, hardware, any combinations of firmware are realizing the method for the present invention and system.Said sequence for the step of method is only
In order to illustrate, the step of the method for the present invention is not limited to order described in detail above, especially says unless otherwise
Bright.Additionally, in certain embodiments, also the present invention can be embodied as recording program in the recording medium, these programs include
For realizing the machine readable instructions of the method according to the invention.Thus, the present invention also covers storage for execution according to this
The recording medium of the program of bright method.
Description of the invention is given for the sake of example and description, and is not exhaustively or by the present invention
It is limited to disclosed form.Many modifications and variations are obvious for the ordinary skill in the art.Select and retouch
Stating embodiment is in order to the principle of the present invention and practical application are more preferably described, and so that those of ordinary skill in the art is managed
The solution present invention is thus design is suitable to the various embodiments with various modifications of special-purpose.
Claims (14)
1. a kind of monitoring arrangement of aero-engine is it is characterised in that include：
Signal pickup assembly, for the state parameter of Real-time Collection aero-engine, and described state parameter is sent to health
Managing device；
Health controller, for being analyzed in real time to described state parameter and being processed, and will be strong for the input of described state parameter
Health forecast model, assesses the health status of described aero-engine, and the life-span of engine components is carried out in conjunction with historical data
Prediction；
Wherein, described health controller includes：
Abnormality detecting unit, for carrying out abnormality detection to sensor signal；Failure diagnosis unit, produces abnormal letter for positioning
Number sensor, by the signal input fault diagnosis model of Real-time Collection, and combine described electronic engine management system in
Status information, fault message and flight parameter, are associated analyzing, carry out fault diagnosis to engine components, and according in advance
The ordering rule of setting is ranked up to exception and fault；Or, anomaly parameter is sent to ground maintenance terminal or ground
EHMS is analyzed, and obtains analysis result.
2. monitoring arrangement as claimed in claim 1 is it is characterised in that described signal pickup assembly includes：
Engine signal collecting unit, is arranged on the sensor signal on aero-engine part for Real-time Collection, and obtains
Status information in electronic engine management system, fault message and flight parameter；
Signal Pretreatment unit, for being filtered to described sensor signal, processing and amplifying, and is converted to digital signal.
3. monitoring arrangement as claimed in claim 2 it is characterised in that：
Described sensor signal includes：Air-channel system parameter, fuel system parameter, oil system parameter and vibration parameters.
4. monitoring arrangement as claimed in claim 2 is it is characterised in that described health controller also includes：
Health evaluating unit, for the result real-time assessment exception that exported according to failure diagnosis unit or fault；Pre- by health
Survey model and life appraisal and prediction are carried out to the engine components one or secondary failure；
Statement-of-health generates and indicating member, for generating statement-of-health, then sends warning signal if there is exception or fault,
And generate maintenance suggestion for described abnormal or alarm.
5. monitoring arrangement as claimed in claim 4 it is characterised in that：
The fault of engine components is divided into Pyatyi, and level fault is miniature fault, and component capabilities reduce by 10%；Secondary failure is little
Type fault, component capabilities reduce by 20%；Three-level fault is medium-sized fault, and component capabilities reduce by 30%；Level Four fault is large-scale event
Barrier, component capabilities reduce by 40%；Pyatyi fault is huge fault, and component capabilities reduce by more than 50%.
6. monitoring arrangement as claimed in claim 4 is it is characterised in that also include：Communicator；
Described communicator carries out data interaction by communication bus with aircraft, EEC, ground maintenance terminal and ground EHMS；
Wherein, the state parameter of electromotor, exception, fault, described statement-of-health or maintenance suggestion are sent by described communicator
To described aircraft, EEC, ground maintenance terminal or ground EHMS.
7. monitoring arrangement as claimed in claim 4 is it is characterised in that also include：Data storage device, for storing described sending out
The state parameter of motivation, exception and fault log；
Wherein, described state parameter includes：Electromotor use time parameter, engine behavior parameter and electromotor building ring
Border parameter.
8. a kind of aero-engine FADEC system it is characterised in that：
Monitoring arrangement including the aero-engine as described in claim 1 to 7 any one.
9. a kind of supervision method of aero-engine is it is characterised in that include：
The state parameter of signal pickup assembly Real-time Collection aero-engine, and described state parameter is sent to health control dress
Put；
Health controller is analyzed in real time to described state parameter and is processed, and described state parameter is inputted health forecast
Model, assesses the health status of described aero-engine, and the life-span of engine components is predicted in conjunction with historical data；
Wherein, described health controller carries out abnormality detection to sensor signal, and positioning occurs abnormal sensor, will in real time
The signal input fault diagnosis model of collection, and with reference to the status information in described electronic engine management system, fault message
And flight parameter, it is associated analyzing, engine components are carried out with fault diagnosis, and according to the ordering rule pre-setting to different
Often it is ranked up with fault；Or, anomaly parameter is sent to ground maintenance terminal or ground EHMS is analyzed, and obtain point
Analysis result.
10. supervision method as claimed in claim 9 it is characterised in that：
Described signal pickup assembly Real-time Collection is arranged on the sensor signal on aero-engine part, and obtains and start electromechanics
Status information in sub-control system, fault message and flight parameter.
11. supervision methods as claimed in claim 10 it is characterised in that：
Described sensor signal includes：Air-channel system parameter, fuel system parameter, oil system parameter and vibration parameters；Described
Signal pickup assembly is filtered to described sensor signal, processing and amplifying, and is converted to digital signal.
12. supervision methods as claimed in claim 10 it is characterised in that：
Described health controller carries out the order of severity of real-time assessment fault according to the result that failure diagnosis unit exports, and leads to
Cross health forecast model and life appraisal and prediction are carried out to the engine components one or secondary failure；Described health control dress
Put generation statement-of-health, then send warning signal if there is exception or fault, and generate maintenance for described abnormal or alarm
Suggestion.
13. supervision methods as claimed in claim 12 it is characterised in that：
The fault of engine components is divided into Pyatyi, and level fault is miniature fault, and component capabilities reduce by 10%；Secondary failure is little
Type fault, component capabilities reduce by 20%；Three-level fault is medium-sized fault, and component capabilities reduce by 30%；Level Four fault is large-scale event
Barrier, component capabilities reduce by 40%；Pyatyi fault is huge fault, and component capabilities reduce by more than 50%.
14. supervision methods as claimed in claim 12 it is characterised in that：
Communicator carries out interacting of data by communication bus with aircraft, EEC, ground maintenance terminal and ground EHMS；Wherein,
Described communicator by the state parameter of electromotor, exception, fault, statement-of-health or maintenance suggestion be sent to described aircraft,
EEC, ground maintenance terminal or ground EHMS.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210389070.1A CN103728965B (en) | 2012-10-15 | 2012-10-15 | Monitoring device and method for aircraft engine and FADEC system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210389070.1A CN103728965B (en) | 2012-10-15 | 2012-10-15 | Monitoring device and method for aircraft engine and FADEC system |
Publications (2)
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