CN104636581A - Civil airplane air way part fault diagnosis method - Google Patents
Civil airplane air way part fault diagnosis method Download PDFInfo
- Publication number
- CN104636581A CN104636581A CN201310561023.5A CN201310561023A CN104636581A CN 104636581 A CN104636581 A CN 104636581A CN 201310561023 A CN201310561023 A CN 201310561023A CN 104636581 A CN104636581 A CN 104636581A
- Authority
- CN
- China
- Prior art keywords
- node
- fault
- air path
- path part
- model
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Abstract
The invention provides a civil airplane air way part fault diagnosis method which comprises the steps that an air way part is divided into a plurality of layers from abstraction to concreteness; a fault diagnosis system model is established for each layer in the multiple layers; fault information is received; nodes corresponding to the fault information are found in the fault diagnosis system of the most-abstract layer; a first-level reason node of a fault is tracked from a node corresponding to the fault information, then a node corresponding to the reason node is found in the fault diagnosis model at a secondary-abstract layer, then a second-level reason node is tracked from the node corresponding to the reason node, by parity of reasoning, the most-concrete reason is tracked in the fault diagnosis system model at the most-concrete layer, and the most-concrete reason is reported to a user. A fault part can be located quickly according to the fault information, speed is high, accuracy is high, new faults which cannot be foreseen can be diagnosed, the system structure property can be considered comprehensively, and a large-scale complex system can be processed.
Description
Technical field
The present invention relates to a kind of civil aircraft method for diagnosing faults, particularly relate to a kind of civil aircraft air path part method for diagnosing faults.
Background technology
Civil aircraft air path part has important effect in whole aircraft system, is also one of system that airplane fault Probability is higher simultaneously.The percent of punctuality impact of the fault that this system occurs on flight is very large, can affect the operation benefits of airline greatly.For air path part fault, current universal method is the phenomenon of the failure empirically checking out according to failure-description or the slip-stick artist of unit, carries out troubleshooting in accordance with handbook.This measure is consuming time many, and workload is large, even sometimes can not the reason of accurate localizing faults.Thus, be badly in need of one efficiently, accurately mode auxiliary maintaining personnel carry out fault diagnosis.
Summary of the invention
The shortcoming of prior art in view of the above, the object of the present invention is to provide a kind of civil aircraft air path part method for diagnosing faults, consuming time many for solving in prior art, and workload is large, the problem that localization of fault accuracy is inadequate.
For achieving the above object and other relevant objects, the invention provides a kind of civil aircraft air path part method for diagnosing faults, comprise and air path part is divided into multilayer particularly from being abstracted into; Diagnose System Model is set up to the every one deck in multilayer; Receive failure message; The node corresponding with failure message is found out from the Diagnose System Model of most level of abstraction; From the one-level reason node of the node trace fault corresponding with failure message, the node corresponding with reason node is found again in the fault diagnosis model of secondary level of abstraction, secondary reason node is followed the trail of again from the node corresponding with reason node, by that analogy, until track the most concrete reason in the Diagnose System Model of most specific layer; The most concrete reason is reported to user.
According to preferred embodiment, the fault diagnosis model in the present invention is signed digraph (Signed Directed Graph is called for short SDG) model.
As mentioned above, civil aircraft air path part method for diagnosing faults of the present invention, has following beneficial effect: first, utilizes method of the present invention can according to failure message quick position trouble unit, and speed is fast, and accuracy rate is high.And according to Graph-theoretical Approach Modling model, do not need mathematical models, diagnosable unforeseeable new fault, can consider system architecture characteristic, and can process the system of large-scale complex.In addition, each system is divided into multilayer subsystem according to function and structure, thus diagnostic result is more accurate.
Accompanying drawing explanation
Fig. 1 is shown as civil aircraft air path part method for diagnosing faults process flow diagram of the present invention;
Fig. 2 is shown as civil aircraft air path part source of the gas subsystem structure figure;
Fig. 3 is shown as and schemes civil aircraft air path part system layer SDG according to the preferred embodiment for the present invention;
Fig. 4 is shown as and schemes the SDG of civil aircraft air path part subsystem layer according to the preferred embodiment for the present invention.
Embodiment
Below by way of specific instantiation, embodiments of the present invention are described, those skilled in the art the content disclosed by this instructions can understand other advantages of the present invention and effect easily.The present invention can also be implemented or be applied by embodiments different in addition, and the every details in this instructions also can based on different viewpoints and application, carries out various modification or change not deviating under spirit of the present invention.
Refer to accompanying drawing.It should be noted that, the diagram provided in the present embodiment only illustrates basic conception of the present invention in a schematic way, then only the assembly relevant with the present invention is shown in graphic but not component count, shape and size when implementing according to reality is drawn, it is actual when implementing, and the kenel of each assembly, quantity and ratio can be a kind of change arbitrarily, and its assembly layout kenel also may be more complicated.
First consult Fig. 1, Figure 1 shows that the process flow diagram of an embodiment of civil aircraft air path part method for diagnosing faults of the present invention.In step S1, aircraft air path part system layer, subsystem layer, component layer are divided into.
Step S2 represents and sets up failure system diagnostic model respectively to every one deck.The present invention, in conjunction with airplane fault diagnosis and the feature of troubleshooting, adopts the method establishment model based on graph theory.Method based on graph theory has unique advantage: have find system designer the ability of unforeseeable fault; Do not need mathematical models; There is stronger interpretability; Inference system has stronger system independence.
Step S3 represents reception failure message.Here failure message comprises failure code, failure-description, monitoring parameter collection, operating condition etc., and failure message can by reacting on the control panel after the collection of aircraft inner sensor, also can be pilot rule of thumb, manipulation impression manually input etc.
Step S4-S6 represents and first in the Diagnose System Model of most level of abstraction, finds out the node corresponding with failure message, the reason node of causing trouble is tracked out in this layer, and then in secondary level of abstraction, find out the node that reason node is corresponding therewith, reason node is more specifically found out again in the Diagnose System Model of secondary level of abstraction, by that analogy, until find out the most concrete failure cause to be reported to user in the Diagnose System Model of most specific layer.
In this example, aircraft air path part is divided into three layers, and all establishes Diagnose System Model to every layer, so can be diagnosed step by step by the concrete pattern of high-level abstract patterns to low level.First analysis of failure region, at which subsystem, is carried out the reasoning of subsystem internal, is to the last determined trouble unit in the scope determined.
Application method for diagnosing faults preferred embodiment of the present invention to carry out fault diagnosis working method to civil aircraft air path part is introduced in detail referring to Fig. 2-Fig. 4.
SDG mode is adopted to set up Diagnose System Model to each system of aircraft air path part in the present embodiment, thus simple graphical description can be provided to the cause-effect relationship between process variable and fault propagation path, clearly can describe the local relation of complication system, more be conducive to the detection of fault in system, location and propagate analyzing.It should be noted that, those skilled in the art also can adopt other method based on graph theory to divide each system to set up Diagnose System Model to aircraft gas circuit, such as but not limited to Petri network, possibility cause-and-effect diagram etc.Those skilled in the art also can adopt the standard of other layering to carry out layering to each system, or carry out modeling in different ways to every layer.
According to preferred embodiments of the present invention, first by civil aircraft air path part by from being abstracted into particularly, system layer, subsystem layer and component layer can be divided into.Then Diagnose System Model is set up to every one deck.
Preferably, when setting up fault diagnosis model, every one deck can be divided into some subsystems or parts by function, such as system layer can be divided into air supply system, anti-icing system and air-conditioning system three subsystems; Air supply system is example, again can Further Division.Fig. 2 is the system construction drawing of air supply system after dividing, air supply system is by engine bleed subsystem, APU(Auxiliary Power Unit as shown in Figure 2, auxiliary power unit) bleed subsystem, ground source of the gas bleed, instruction and control system, hand over multiple independently subsystems such as defeated bleed valve to form.
For anti-icing system and air-conditioning system, also can carry out division in a similar manner and Modling model, repeat no more herein.
Next by consulting aircraft maintenance handbook, aircraft principle handbook, line construction handbook etc., also need with reference to historical failure diagnosis, mantenance data if desired, react the characteristic variable of each subsystem or parts in can finding out every layer, and find out the qualitative cause-effect relationship of structure, function and the behavior relation between these characteristic variables.Also need to each characteristic variable according to determining that fault under operating mode occurs and the rule propagated determines normal theoretical value, normal theoretical value is the boundary value basis for estimation obtaining node state in SDG model instantaneous sample.Because actual motion condition of work is changeable, dynamic perfromance is complicated, and normal theoretical value can be the threshold range determined, also can be a function of state.In this example, the Partial Feature variables choice of air supply system is as shown in table 1:
Table 1: air supply system characteristic variable
For simplified illustration, in table 1, only list a part of characteristic variable.Wherein, the variable in control panel is that aircraft maintenance or operating personnel can directly from the information that user interface is read.There are characteristic variable and mutual relationship thereof, just these characteristic variables can be connected in the mode of SDG figure, vector branch between node represents the qualitative effect relation between node, solid arrow represents increment impact, also increases (or minimizing) if i.e. start node increase (or minimizing) has influence on downstream node; Dotted arrow represents decrement impact, has influence on downstream node increase (or minimizing) if namely start node reduces (or increasing).A part of the system-level SDG figure of air supply system as shown in Figure 3.
Can see in Fig. 3, P
pIPSsignal exports C by APU Loading Control valve (APULCV) switch
aPULCV, engine bleed select export C
hPV, PRSOV(Pressure Regulating And Shutoff Valve, pressure governor valve) switch export C
pRV, CBV(Cross Bleed Valve, intersect bleed valve) switch exports C
cBVwith CBV aperture V
cBVincrement impact, simultaneously P
pIPSsignal again decrement affects engine bleed selection output C
hPV.The failure cause node of more abstract subsystem irrespective of size only can be tracked out from the SDG figure of Fig. 3, for more specifically finding out failure cause, the SDG model of subsystem irrespective of size can be set up further, be described for APU subsystem below, for engine bleed subsystem, ground air supply system etc., step can set up Diagnose System Model and tracing trouble as stated above, because principle is similar, repeat no more herein.
Show in fig. 2 the result that APU subsystem divides by function, the Partial Feature variable chosen APU subsystem is as shown in table 2:
Table 2:APU bleed sub-system features variable
According to system-level similar principle, utilize the characteristic variable in table 2, the SDG model of subsystem irrespective of size can be built, as shown in Figure 4, from Fig. 4, can by failure cause specific to parts one-level.So far, the Diagnose System Model of civil aircraft air path part is set up complete.It should be noted that, it will be appreciated by those skilled in the art that for different systems or demand, in various degree abstract is adopted to system, then can obtain more or less level, but these changes does not exceed design of the present invention.
In reality, aircraft all can not arrange inductor to any parts, so large multipart fault indirectly informs staff by some characteristic variables, and variable so under normal circumstances and fault are not one_to_one corresponding, so staff is after learning that certain variable is abnormal, directly trouble unit can not be navigated to.But according to method of the present invention, establish SDG model, after receiving failure message, pass through backward reasoning, oppositely explore possible and independently compatible path from current paid close attention to consequence node (warning node) to possible all reason nodes, namely can realize the diagnosis of concrete trouble unit.
Now suppose IASC(Integrated Air System Controller, air-conditioning system general controller) (be designated as F to short circuit between APU bleed button
iASC4), this fault can cause APU bleed to be lost efficacy, and shows as APULCV switch and exports C
aPULCVabnormal, and C
aPULCUextremely the PIPS(Pack Inlet Pressure Sensor on control panel can be caused further; air-condition assembly inlet pressure sensor) abnormal signal; so the failure message that staff receives is the PIPS abnormal signal on control panel, and can not directly locate concrete trouble unit.But according to the inventive method, staff then can locate concrete trouble unit easily.Particularly, after receiving this failure message, first seeking system level SDG model, is also Fig. 3, can sees and the parameter of PIPS abnormal signal may be caused to be C
hPV, C
pRV, C
aPULCV, V
cBV, C
cBV, so only need to measure these five variablees, and do not need to pay close attention to other variable or parts, the node of measurement result exception should be C
aPULCV.At this moment can continue to check Fig. 4, as can see from Figure 4, affect C
aPULCVthe variable of node has C
aPUFADECand F
iASC4, (APUFADEC, full name is APU Full Authority Digital Electronic Control, auxiliary power unit Full Authority Digital electronic controller) then measures this Two Variables again, finally can obtain F
iASC4abnormal, due to F
iASC4specific to component layer, so localization of fault work completes, can to staff or the concrete trouble unit of user report or failure cause.
It should be noted that, according to another preferred embodiment of the invention, after tentatively setting up the SDG model of each layer, the statistics of historical data can be utilized, revise or upgrade the membership function in quantitative SDG model, realizing the correction to fault diagnosis model with this.Method of the present invention by software or hardware implementation, also manually can be implemented by staff.
Above-described embodiment is illustrative principle of the present invention and effect thereof only, but not for limiting the present invention.Any person skilled in the art scholar all without prejudice under spirit of the present invention and category, can modify above-described embodiment or changes.Therefore, such as have in art usually know the knowledgeable do not depart from complete under disclosed spirit and technological thought all equivalence modify or change, must be contained by claim of the present invention.
Claims (6)
1. a civil aircraft air path part method for diagnosing faults, is characterized in that, comprising:
Air path part be divided into and comprise the 1st grade, the 2nd grade until N level multistage;
To described multistage in every one-level set up Diagnose System Model;
Receive at least one failure message;
The node corresponding with described failure message is found out from the described Diagnose System Model of described 1st grade;
From the reason node of the described node corresponding with failure message trace fault in the Diagnose System Model of described 1st grade, the node corresponding with described reason node is found again in the described fault diagnosis model of described 2nd grade, in the Diagnose System Model of described 2nd grade, reason node is followed the trail of again from the node corresponding with described reason node, by that analogy, until track concrete trouble unit and generate corresponding fault log in the Diagnose System Model of N level;
Described fault log is exported or stores.
2. civil aircraft air path part method for diagnosing faults according to claim 1, is characterized in that, to described multistage in every one-level set up in the step of Diagnose System Model, comprise the steps:
According to function, this level is divided into multiple subsystem or parts;
Choose the characteristic variable of the described each subsystem of reaction or parts according to Aircraft Maintenance Munual, aircraft principle handbook, line construction handbook and historical data, and find out the relation between described characteristic variable;
Described failure system diagnostic model is set up according to described relational database and described characteristic variable.
3. civil aircraft air path part method for diagnosing faults according to claim 1 and 2, is characterized in that, described failure system diagnostic model is Sign Directed Graph Models.
4. civil aircraft air path part method for diagnosing faults according to claim 1, it is characterized in that, described multilayer comprises system layer, subsystem layer, component layer.
5. civil aircraft air path part method for diagnosing faults according to claim 1, it is characterized in that, between the described step every one deck in described multilayer being set up to Diagnose System Model and reception failure message, also comprise the step described Diagnose System Model revised according to historical data.
6. civil aircraft air path part method for diagnosing faults according to claim 1, is characterized in that, described failure message comprises failure code, failure-description, monitoring parameter collection, operating condition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310561023.5A CN104636581A (en) | 2013-11-12 | 2013-11-12 | Civil airplane air way part fault diagnosis method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310561023.5A CN104636581A (en) | 2013-11-12 | 2013-11-12 | Civil airplane air way part fault diagnosis method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104636581A true CN104636581A (en) | 2015-05-20 |
Family
ID=53215322
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310561023.5A Pending CN104636581A (en) | 2013-11-12 | 2013-11-12 | Civil airplane air way part fault diagnosis method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104636581A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105005297A (en) * | 2015-09-09 | 2015-10-28 | 上海中曼石油装备有限公司 | Pneumatic control fault diagnosis system of drilling machine driller room |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102855349A (en) * | 2012-08-06 | 2013-01-02 | 南京航空航天大学 | Quick prototype design method and platform for gas path fault diagnosis for aeroengine |
| CN102945311A (en) * | 2012-10-08 | 2013-02-27 | 南京航空航天大学 | Method for diagnosing fault by functional fault directed graph |
| CN102980771A (en) * | 2012-12-04 | 2013-03-20 | 南京航空航天大学 | Portable failure detection system and method for aero-engine gas path component |
-
2013
- 2013-11-12 CN CN201310561023.5A patent/CN104636581A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102855349A (en) * | 2012-08-06 | 2013-01-02 | 南京航空航天大学 | Quick prototype design method and platform for gas path fault diagnosis for aeroengine |
| CN102945311A (en) * | 2012-10-08 | 2013-02-27 | 南京航空航天大学 | Method for diagnosing fault by functional fault directed graph |
| CN102980771A (en) * | 2012-12-04 | 2013-03-20 | 南京航空航天大学 | Portable failure detection system and method for aero-engine gas path component |
Non-Patent Citations (1)
| Title |
|---|
| 张光明: "航空发动机气路故障诊断技术研究", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105005297A (en) * | 2015-09-09 | 2015-10-28 | 上海中曼石油装备有限公司 | Pneumatic control fault diagnosis system of drilling machine driller room |
| CN105005297B (en) * | 2015-09-09 | 2017-11-21 | 中曼石油天然气集团股份有限公司 | A kind of gas control fault diagnosis system of driller control house |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109829468B (en) | Bayesian network-based civil aircraft complex system fault diagnosis method | |
| CN104149988B (en) | The method for diagnosing bleed air system failure | |
| CN106503746B (en) | A kind of Fault Diagnosis of Aeroengines method based on offset of performance amount | |
| CN106250709A (en) | Gas turbine abnormality detection based on sensors association network and fault diagnosis algorithm | |
| US9376983B2 (en) | Operations support systems and methods with acoustics evaluation and control | |
| CN105808366B (en) | A kind of System Safety Analysis method based on four variate models | |
| US20190026963A1 (en) | Fusion of aviation-related data for comprehensive aircraft system health monitoring | |
| US9091616B2 (en) | Engine operations support systems and methods for reducing fuel flow | |
| CN102945311A (en) | Method for diagnosing fault by functional fault directed graph | |
| TWI731146B (en) | Aircraft malfunction handling system, method for handling aircraft malfunction, and computer equipment using thereof | |
| CN110884687A (en) | Semi-physical real-time simulation verification platform for PHM technology of electromechanical system | |
| CN108089975A (en) | A kind of method of constructing environment Control System Software virtual testing environment | |
| CN113168313A (en) | Computing environment system for monitoring aircraft engines | |
| CN107015486A (en) | A kind of air-conditioner water system regulating valve intelligent fault diagnosis method | |
| CN109795713B (en) | Fault diagnosis method for aileron actuator based on Simulink model | |
| Zhao et al. | Sensor fault diagnosis of aero-engine based on divided flight status | |
| CN104679945A (en) | System comprehensive assessment method based on colored Petri network | |
| CN104636581A (en) | Civil airplane air way part fault diagnosis method | |
| Pan et al. | A model of fuel consumption estimation and abnormality detection based on airplane flight data analysis | |
| CN112182743B (en) | Fault transmission feature matching-based aircraft system fault diagnosis method | |
| Zhao et al. | Remote intelligent expert system for operation state of marine gas turbine engine | |
| CN113050595B (en) | Potential fault analysis method based on PFMEA and HRA method | |
| Edifor et al. | Using simulation to evaluate dynamic systems with weibull or lognormal distributions | |
| Zhang et al. | Fault tree analysis of an airborne refrigeration system based on a hyperellipsoidal model | |
| Jiang et al. | Application of prognostic and health management in avionics system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| EXSB | Decision made by sipo to initiate substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150520 |