CN104535901B - A kind of aircraft cable fault localization method based on aircraft cable distributed information database - Google Patents
A kind of aircraft cable fault localization method based on aircraft cable distributed information database Download PDFInfo
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- CN104535901B CN104535901B CN201510039309.6A CN201510039309A CN104535901B CN 104535901 B CN104535901 B CN 104535901B CN 201510039309 A CN201510039309 A CN 201510039309A CN 104535901 B CN104535901 B CN 104535901B
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Abstract
The present invention provides the aircraft cable fault localization method based on aircraft cable distributed information database, the aircraft cable fault combined according to Aircraft Wiring Manual and comparison of wave shape algorithm diagnoses localization method, including：Reflectance factor based on the aircraft cable data generation different type cable in Aircraft Wiring Manual；Based on WDM and the test lead being manually entered, cable network subdata base of the generation comprising cable composition structure and branch's situation；The reflection configuration during cable network serviceable condition is generated according to cable network subdata base；Utilize waveform generator and the tested cable network reflection configuration of data collecting card collection；Tested cable network and reflection configuration during cable network serviceable condition are contrasted using comparison of wave shape algorithm, realize cable network fault diagnosis and location, realize that the fault type of optional position and abort situation judge in two branches, four connector cable network structure, its fault diagnosis error is less than 0.02 meter, maximum 200 meters of length of measurement.
Description
Technical field
The invention belongs to fault diagnosis field, more particularly to a kind of aircraft based on aircraft cable distributed information database
Cable fault localization method.
Background technology
Aircraft cable refers to the hardware unit for providing power source and transmission of control signals for electrical system aboard, by
Numerous device compositions such as connecting wire, connector, are that power supply, electromechanical equipment, electronic equipment and control system are connected on aircraft
The important energy source and information channel of system, play the role of flight control and flight safety etc. vital.
Aircraft cable fault is possible to occur in aircraft manufacturing assembling process, becomes aircraft cable integrity test
An important process during aircraft general assembly.During aircraft manufacturing, after aircraft cable laying installation, in airborne equipment
, it is necessary to be tested using test system all cables of aircraft before installation, verify whether all aircraft cables correctly connect,
Determine whether there is connecting fault and line fault in aircraft cable, integrity checking is carried out to aircraft cable, to avoid due to line
Cable reason and increase airborne equipment debugging difficulty.Can also ensure that costliness will not be damaged because of the failure mistake of cable at the same time
Airborne equipment, it is ensured that each systemic-function of aircraft is normal, it is often more important that can remove a hidden danger, it is ensured that flight safety.
If in aircraft cable, there are failure, it is necessary to is not removing a large amount of aircraft cable fixers and aircraft interlayer
Under the premise of, using advanced aircraft cable fault location technology in numerous and diverse aircraft cable network fast searching abort situation,
And it can be found that some intermittent defects in aircraft cable, in order to repair and replace.Examined in existing aircraft cable fault
In survey method, reflection detection method is a kind of common measuring technology.The principle of method for reflection is to launch one to one end of cable
A low pressure high frequency pulsed reference signal, since cable fault can cause its impedance to change, reference signal then can be at failure
Reflect.Reflected signal is detected in signal incidence end, can be calculated using the time delay of incoming signal and reflected signal
Cable fault position, the amplitude of reflected signal and direction may determine that the type of failure.
Modern aircraft develops to more electric aircraft directions, and electronics, the electrical equipment of use are more and more, the cable used
Also increase therewith.In aircraft general assembly cable assembling process, once occur that cable fault faced is exactly one and has more points
The cable network of branch and more adapters.If fault location can only be carried out to single cable, then just need according to test procedure
Fault location could be carried out, it is necessary to spend the time more by dismantling multiple jointings, seriously affect work efficiency.
For this reason, adapter can be overcome for multiple-limb and more adapter aircraft cable network fault-location problems, design
The reference signal of signal attenuation, reducing noise signal influences fault location system, studies cable network signal multiple reflection phenomenon,
Exploitation can realize that the equipment of fault fast positioning just becomes a certainty in multiple-limb and more adapter aircraft cable networks
Development trend.
The content of the invention
For problem present in above-mentioned technology, the object of the present invention is to provide one kind to be based on aircraft cable distributed intelligence number
According to the aircraft cable fault localization method in storehouse, by the fault detection analysis to reflected signal, and coordinate what is pre-established
The distributed intelligence of aircraft cable and cable network database, can carry out aircraft cable fault accurately to position and fail result is shown
Show, for improving aircraft manufacturing assembly work efficiency, eliminate aircraft electrical line fault hidden danger, improve aircraft manufacturing assembling and make
With maintenance efficiency, ensure that aircraft safety is respectively provided with significance.
To achieve the above object, the technical solution adopted in the present invention is to propose that one kind is based on aircraft cable distributed intelligence number
According to the aircraft cable fault localization method in storehouse, this method is to build aircraft cable network database using Aircraft Wiring Manual,
And aircraft cable network fault location is completed based on the database, by the use of the cable type in WDM handbooks and length known to
Condition, high-frequency pulse signal is produced using waveform generator, and the reflection of such cable is obtained using one in a certain type cable
Coefficient, obtains the reflectance factor of other types cable, with reference to the aircraft needed for Aircraft Wiring Manual structure fault diagnosis positioning
Cable network database；Using aircraft cable network database realizing to path query, normal condition is drawn with reference to searching route
The reflection configuration of lower cable network；The reflection configuration of tested cable network is obtained using time domain reflectometry at the same time；Pass through waveform ratio
Compared with the corresponding sampling of the algorithm comparison wave crest and trough of the reflection configuration of cable network and actual reflection configuration under normal circumstances
The difference of point, is determined as abort situation if difference is more than given threshold；Utilize sampled point, reflectance factor and cable network structure
Calculate position of the trouble point in tested cable；The realization of this method is built upon on the basis of industrial personal computer, utilizes Labview
Virtual instrument software is configured signal transmission cards realization and specifies waveform output, while the number collected to data collecting card
According to being handled, and the interpretation of result and display of gathered data are realized by Labview virtual instrument softwares；This method is specifically wrapped
Include following steps：
1) cable type in aircraft cable network database is sorted out, and a sample line is chosen to each type
Cable, determines the type and length of input cable, passes through Labview virtual instrument software setting signal transmission cards and signal acquisition
Card, the burst pulse that transmitting width is 1/200M, which is used as, refers to signal, and gathers reflected signal using data collecting card and calculate hair
Penetrate signal and launch the sampling number between signal, the ratio of reflection sampled point and length of cable is calculated, as going out all kinds of cables
Reflectance factor；
2) the wire list in the WDM handbooks of Boeing 777 correlation type are searched, choose wire list harness Bundle
No, wire size Wire No, group number Farm, length FT-IN, slave device end From Equip, including the pin number at slave device end or right
Answer type, to equipment end To Equip, including pin number or corresponding types to equipment end, with reference in Boeing 777 aircraft model
The multiple-branching construction of Bandaid block or aircraft component intraconnection equipment composition, while include the reflectance factor of all kinds of cables before
Cable type (TY) with wire list, in Labview virtual instrument softwares, utilizes what is write based on ADO technologies
LabVIEW database access bags LabSQL sorts out above- mentioned information, finally constitutes aircraft cable network overall distribution information
Database；
3) when measuring beginning, input the wire size of tested cable and the cable is tested and holds pin or hole in Aviation Connector corresponding
(PIN) is numbered as selected starting point and includes the oriented starting point of a direction extension to selected starting point, by cable grid
The query generation of the network distributed information database thus corresponding aircraft cable network subdata base of oriented starting point；
4) on the industrial personal computer cable network subdata base is realized using ADO technologies in Labview virtual instrument softwares
Calling, using length of cable in database, reflectance factor and corresponding cable network connection relation, it is intact to calculate tested cable
Reflection configuration under state, so as to provide canonical reference waveform for cable network fault diagnosis；
5) using arbitrary waveform generator transmission frequency 100M, amplitude 1V square-wave signals, and it is real to obtain tested cable network
Border reflection configuration, judges whether tested aircraft cable sub-network breaks down with this waveform, and judges it is short circuit or open circuit event
Barrier；
6) pulsewidth 1/200M pulse signals are sent using waveform generator, and obtains the actual back wave of tested cable network
Shape, and carry out noise reduction process and waveform standard using signal processing module in the Labview virtual instrument software platforms of industrial personal computer
Change is handled；
7) reflection configuration under the actual reflection configuration after standardization and serviceable condition is subjected to comparison of wave shape,
If through comparison of wave shape find there are the larger point of difference, you can determine be corresponding sampled point wave crest or trough exist change, i.e.,
It is not inconsistent with the cable network structure under normal condition, and illustrates the tested cable network there are failure, then failure definition occurs
Place sampled point is trouble point, and thus judges the branch where occurring of being out of order；
8) branch where sampled point occurs using trouble point and failure, by calling all cables of guilty culprit branch
Cable reflectance factor and length of cable, determine position of the cable fault in the fault branch；
9) the Labview virtual instrument test platforms system of database and industrial personal computer is connected by interface protocol；
10) behaviour that virtual instrument test platform is inquired about to database reflected waves graphic data, adds, deletes, changes
Make.
It is described from an equipment end From Equip, include the pin number or corresponding types at slave device end, to another equipment end
To Equip, including pin number or corresponding types to equipment end, utilize from an equipment end and referring to another equipment end on aircraft
The port at each position, wherein includes many pins, each pin is right on the aircraft of Aviation Connector connection in each connector of Aviation Connector
One in the aircraft cable answered is, it is necessary to indicate that corresponding pin or hole reference numeral and corresponding types refer to that the equipment end connects
The device type connect.
The middle Bandaid block refers to that each pin or Kong Junyu on the connector of the Boeing 777 airplane type interconnected should
The structure that other pins or hole on block are attached.
The present invention effect be：Established and flown using the reflectance factor of aircraft cable reference books and different type aircraft cable
Machine cable overall distribution information database, carries out fault detect to aircraft cable by reflection detection method, will detect failure knot
Failure and relevant aircraft cable information is accurately positioned compared with corresponding aircraft cable ideal distribution information in fruit.Utilize this hair
It is bright that the fault type of optional position and abort situation judgement, its fault diagnosis in two branches, four connector cable network structure can be achieved
Error is less than 0.02 meter, maximum 200 meters of length of measurement.
Brief description of the drawings
Fig. 1 is aircraft cable network Fault Locating Method flow chart；
Fig. 2 reflects detection fault location test system with aircraft cable for aircraft cable distributed information database and is connected pass
System；
Fig. 3 is example aircraft cable network structure.
Embodiment
A kind of aircraft cable fault positioning side based on aircraft cable distributed information database with reference to attached drawing to the present invention
Method is described in detail in.
Fig. 1 is the bulk flow of the aircraft cable fault localization method of the invention based on aircraft cable distributed information database
Journey, including：Cable type in aircraft cable network database is sorted out, and a sample line is chosen to each type
Cable, determines the type and length of input cable, by calculating the ratio of reflection sampled point and length of cable, calculates all kinds of cables
Reflectance factor.The wire list in the WDM handbooks of Boeing 777 correlation type are searched, choose the harness number in wire list
Bundle No., wire size Wire No., group number Farm, length FT-IN, From Equip i.e. from an equipment end, including from
Which pin or corresponding types of equipment end, To Equip i.e. to another equipment end, including which pin to equipment end or
It is corresponding types, wherein referring to utilize Aviation Connector on aircraft from an equipment end From Equip and another To Equip equipment ends
Include many pins in the port at each position on the aircraft of connection, the wherein each connector of Aviation Connector, the corresponding aircraft of each pin
One in cable, it is necessary to indicate corresponding pin or hole reference numeral, wherein corresponding types refer to that what the equipment end connected sets
Standby type.With reference to Bandaid block in aircraft, i.e., a kind of connector of interconnected is other on each pin or Kong Junyu block thereon
Pin or hole are attached or the multiple-branching construction of aircraft component intraconnection equipment composition, while by the anti-of all kinds of cables before
Penetrate coefficient with the cable type TY in wire list to be sorted out, finally constitute aircraft cable network overall distribution information data
Storehouse, this database intrinsic parameter and attribute are once to generate in advance, are only consistent with aircraft maintenance handbook.When measuring beginning,
Pin or the corresponding numbering PIN in hole be as oriented starting point in the device number and Aviation Connector of the tested cable of input, selected starting point and
Including being which direction extension to the point, pass through the thus oriented starting point of the query generation to cable network distributed information database
Corresponding aircraft cable network subdata base, aircraft cable network subdata base are aircraft cable network overall distribution information datas
The part in storehouse；The step for each Circuit fault diagnosis is required for first carrying out before starting, the difference of oriented starting point, generation
Aircraft cable network subdata base also can be different.Utilize the length of cable in the corresponding aircraft cable network subdata base of oriented starting point
The reflectance factor and data cable network connection relation of degree, corresponding cable, extrapolate the reflection under tested cable serviceable condition
Waveform, so as to provide canonical reference waveform for cable network fault diagnosis.
First with waveform generator transmission frequency 100M, amplitude 1V square-wave signals, and it is actually anti-to obtain tested cable network
Ejected wave shape；Judge whether tested aircraft cable sub-network breaks down with this waveform, and judge it is short circuit or open circuit fault.Afterwards
Pulsewidth 1/200M pulse signals are sent using waveform generator, and obtain the actual reflection configuration of tested cable network, and are dropped
Make an uproar processing and waveform standardization；By the reflection configuration under the actual reflection configuration after standardization and serviceable condition
Carry out comparison of wave shape, if through comparison of wave shape find there are the larger point of difference, you can determine be corresponding sampled point wave crest or ripple
There is change in paddy, i.e., be not inconsistent with the cable network structure under normal condition, and illustrates the tested cable network there are failure, then
Sampled point where failure definition occurs is trouble point, and thus judges the branch where occurring of being out of order.Using trouble point and
Branch where sampled point occurs for failure, is grown by the cable reflectance factor and cable that call all cables of guilty culprit branch
Degree, determines position of the cable fault in the fault branch.By interface protocol by database and virtual instrument test platform system
System connection.
As shown in Fig. 2, database has been arrived in use during cable Network Fault Detection with positioning.LabVIEW is in itself
It can not directly access the database, it is necessary to be attached by External Program Interface and database software, wherein ADO is using most
For extensive technology.Utilize the LabVIEW database access bags LabSQL write based on ADO technologies.Pass through LabSQL, Yong Huke
Access and operation to database are realized in directly again LabVIEW in a manner of calling sub- VI.In virtual instrument test platform
In, aircraft cable network overall distribution database can be operated by LabView, inquire about, add, delete, change.
Data explanation analysis is carried out with reference to example：
All cable networks are as shown in Figure 3 in existing cable network database：
As shown in Figure 3：By inputting oriented starting point W10, C10, select with inferior division：
If during fault-free, i.e., include W10, W11, W12, W13 without short circuit and open circuit fault, display circuit one in whole network
Normally, circuit two includes W10, W14, W15, and W16 is normal.
Following failure is now set to be verified：
1) when setting open circuit fault at C16, display circuit one includes W10, and W11, W12, W13 is normal, and circuit two wraps
Include W10, W14, W15, W16 is abnormal, and open circuit fault occurs for circuit, and position W16 occurs for failure, and set at the 0m of C16 ends
Failure is consistent.
2) when nearby setting open circuit fault among W15, display circuit one includes W10, and W11, W12, W13 is normal, line
Road two includes W10, W14, W15, and W16 is abnormal, and open circuit fault occurs for circuit, and position W15 occurs for failure, at the 10.18m of C15 ends,
It is consistent with set failure.
3) when setting short trouble at C16, display circuit one includes W10, and W11, W12, W13 is normal, and circuit two includes
W10, W14, W15, W16 are abnormal, and short trouble occurs for circuit, and position W16 occurs for failure, and set at the 0.20m of C16 ends
Failure it is consistent.
4) when nearby setting short trouble among W15, display circuit one includes W10, and W11, W12, W13 is normal, line
Road two includes W10, W14, W15, and W16 is abnormal, and short trouble occurs for circuit, and position W15 occurs for failure, at the 10.19m of C15 ends,
It is consistent with set failure.
Claims (3)
1. a kind of aircraft cable fault localization method based on aircraft cable distributed information database, this method is to utilize aircraft line
Road figure handbook (WDM) builds aircraft cable network database, and completes aircraft cable network fault location, profit based on the database
By the use of the cable type in WDM handbooks and length as known conditions, high-frequency pulse signal is produced using waveform generator, utilizes certain
One in one type line cable obtains such cable reflectance factor, the reflectance factor of other types cable is obtained, with reference to WDM handbooks
Build the aircraft cable network database needed for fault diagnosis positioning；Path is looked into using aircraft cable network database realizing
Ask, the reflection configuration of cable network under normal circumstances is drawn with reference to searching route；Obtained at the same time using time domain reflectometry by survey line
The reflection configuration of cable network；Pass through waveform comparison the algorithm comparison reflection configuration of cable network and actual back wave under normal circumstances
The difference of the wave crest of shape and the corresponding sampled point of trough, is determined as abort situation if difference is more than given threshold；Using adopting
The position of sampling point, reflectance factor and cable network Structure Calculation trouble point in tested cable；The realization of this method is to establish
On the basis of industrial personal computers, using Labview virtual instrument softwares signal transmission cards are configured with realization and specifies waveform output,
The data collected at the same time to data collecting card are handled, and realize gathered data by Labview virtual instrument softwares
Interpretation of result and display；This method specifically includes following steps：
1) cable type in aircraft cable network database is sorted out, and a sample cable is chosen to each type,
Determine the type and length of input cable, pass through Labview virtual instrument software setting signal transmission cards and data acquisition card, hair
Burst pulse that width is 1/200M is penetrated as refer to signal, and using data collecting card collection reflected signal and calculates transmitting signal
Sampling number between transmitting signal, calculates the ratio for reflecting sampled point and length of cable, makes the reflection system of all kinds of cables
Number；
2) (the wire list) in the WDM handbooks of Boeing 777 correlation type is searched, is chosen in cable list (wire list)
Harness number (Bundle No), wire size (Wire No), group number (Farm), length FT-IN, from an equipment end (From Equip),
Pin number or corresponding types including slave device end, to another equipment end (To Equip), including to equipment end pin number or
Corresponding types, the multiple-branching construction formed with reference to Bandaid block in Boeing 777 aircraft model or aircraft component intraconnection equipment,
The reflectance factor of all kinds of cables and the cable type (TY) in (wire list) including before at the same time, in Labview virtual instruments
In software, above- mentioned information is sorted out using the LabVIEW database access bags LabSQL write based on ADO technologies, finally
Form aircraft cable network overall distribution information database；
3) when measuring beginning, input the wire size of tested cable and the cable is tested the corresponding numbering of pin or hole in the Aviation Connector of end
(PIN) as selecting starting point and including the oriented starting point of a direction extension to selected starting point, by cable network point
The query generation of the cloth information database thus corresponding aircraft cable network subdata base of oriented starting point；
4) tune of cable network subdata base is realized using ADO technologies in Labview virtual instrument softwares on the industrial personal computer
With, utilize length of cable in database, reflectance factor and correspond to cable network connection relation, the tested cable serviceable condition of calculating
Under reflection configuration, so as to provide canonical reference waveform for cable network fault diagnosis；
5) using arbitrary waveform generator transmission frequency 100M, amplitude 1V square-wave signals, and it is actually anti-to obtain tested cable network
Ejected wave shape, judges whether tested aircraft cable sub-network breaks down with this waveform, and judges it is short circuit or open circuit fault；
6) pulsewidth 1/200M pulse signals are sent using waveform generator, and obtains the actual reflection configuration of tested cable network, and
Carried out using signal processing module in the Labview virtual instrument software platforms of industrial personal computer at noise reduction process and waveform standardization
Reason；
7) reflection configuration under the actual reflection configuration after standardization and serviceable condition is subjected to comparison of wave shape, if through
Comparison of wave shape find there are the larger point of difference, you can determine be corresponding sampled point wave crest or trough exist change, i.e., with just
Cable network structure under normal state is not inconsistent, and illustrates the tested cable network there are failure, then where failure definition occurs
Sampled point is trouble point, and thus judges the branch where occurring of being out of order；
8) branch where sampled point occurs using trouble point and failure, by the line for calling all cables of guilty culprit branch
Cable reflectance factor and length of cable, determine position of the cable fault in the fault branch；
9) the Labview virtual instrument test platforms system of database and industrial personal computer is connected by interface protocol；
10) operation for being inquired about to database reflected waves graphic data in virtual instrument test platform, adding, delete, changing.
A kind of 2. aircraft cable fault positioning side based on aircraft cable distributed information database according to claim 1
Method, it is characterized in that：It is described to include the pin number or corresponding types at slave device end from an equipment end (From Equip), to another
Equipment end (To Equip), including pin number or corresponding types to equipment end, slave device end and refer on aircraft sharp to equipment end
With the port at each position on the aircraft of Aviation Connector connection, spininess wherein is included in each connector of Aviation Connector, each pin is right
One in the aircraft cable answered is, it is necessary to indicate that corresponding pin or hole reference numeral and corresponding types refer to that the equipment end connects
The device type connect.
A kind of 3. aircraft cable fault positioning side based on aircraft cable distributed information database according to claim 1
Method, it is characterized in that：The middle Bandaid block refers to each pin or Kong Jun on the connector of the Boeing 777 airplane type interconnected
The structure being attached with other pins on the block or hole.
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| CN105388397B (en) * | 2015-12-02 | 2018-07-17 | 山东康威通信技术股份有限公司 | A kind of branched structure cable fault positioning device and method |
| CN107843787A (en) * | 2017-10-31 | 2018-03-27 | 中国民航大学 | Aero-engine electric wiring integrity test apparatus testing method based on database-driven |
| CN108535605A (en) * | 2018-04-18 | 2018-09-14 | 南京南瑞继保电气有限公司 | A kind of impulse waveform comparative approach for the monitoring of direct current grounding pole line fault |
| CN109033522B (en) * | 2018-06-25 | 2023-04-18 | 中国民航大学 | Device and method for evaluating wiring scheme of multi-electric-aircraft electric circuit interconnection system |
| CN112433126B (en) * | 2020-09-22 | 2022-05-10 | 成都飞机工业（集团）有限责任公司 | Digital model-based quick positioning method for spatial position of fault after wiring harness installation |
| CN113281617B (en) * | 2021-06-08 | 2022-09-27 | 中国民航大学 | Weak fault diagnosis method for airplane cable |
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