CN104535901A - Airplane cable fault positioning method based on airplane cable distribution information databank - Google Patents
Airplane cable fault positioning method based on airplane cable distribution information databank Download PDFInfo
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Abstract
The invention provides an airplane cable fault positioning method based on an airplane cable distribution information databank. With the combination of an airplane route manual and a waveform comparison algorithm, the airplane cable fault positioning method comprises the following steps: generating reflection coefficients of different types of cables according to airplane cable data in the airplane route manual; generating a cable network sub-databank including the cable constituting structures and branch situations of cables on the basis of WDM and a testing end for manual input; generating reflection waveforms of the cable network in a complete state according to the cable network sub-databank; acquiring the reflection waveforms of the cable network by using a waveform generator and a data acquisition card; comparing reflection waveforms of the tested cable network and the cable network in the complete state by using a waveform comparison algorithm, thereby achieving cable network fault diagnosis and positioning, and achieving fault type and fault position judgment on any position inside a two-branch four-connector cable network structure. Therefore, the fault diagnosis error is smaller than 0.02m, and the maximum measurement length is 200m.
Description
Technical field
The invention belongs to fault diagnosis field, particularly relate to a kind of aircraft cable fault localization method based on aircraft cable distributed information database.
Background technology
Aircraft cable refers to aboard for electrical system provides the hardware unit of power source and transmission of control signals, be made up of numerous device such as connection wire, connector etc., be the important energy source and the information channel that aircraft connect power supply, electromechanical equipment, electronic equipment and control system, control flight and flight safety etc. serves vital effect.
Aircraft cable fault just likely occurs in aircraft manufacturing assembling process, makes the integrity test of aircraft cable become an important process in the total process of assembling of aircraft.In aircraft manufacturing process, after the laying installation of aircraft cable, before airborne equipment is installed, need to utilize all cables of test macro to aircraft to test, verify all aircraft cables whether exact connect ion, determine whether to have in aircraft cable and connect fault and line fault, integrity checking is carried out to aircraft cable, increases airborne equipment debugging difficulty to avoid due to cable reason.Can also ensure to damage expensive airborne equipment because of the fault mistake of cable simultaneously, guarantee that each systemic-function of aircraft is normal, the more important thing is and can remove a hidden danger, guarantee flight safety.
If there is fault in aircraft cable, just need under the prerequisite of not removing a large amount of aircraft cable fixer and aircraft interlayer, utilize advanced aircraft cable fault location technology fast searching abort situation in numerous and diverse aircraft cable network, and some intermittent defects in aircraft cable can be found, so that maintenance and replacing.In existing aircraft cable fault detection method, reflection detection method is a kind of conventional measuring technology.Reflection side ratio juris launches a low pressure high frequency pulsed reference signal to one end of cable, and because cable fault can cause its impedance to change, reference signal then can reflect at fault place.Reflected signal detected in signal incidence end, utilize to calculate cable fault position the time delay of incoming signal and reflected signal, the amplitude of reflected signal and direction can the types of failure judgement.
Present generation aircraft is to how electric aircraft future development, and electronics, the electrical equipment of employing get more and more, and the cable of use also increases thereupon.In aircraft general assembly cable assembling process, once occur cable fault faced by be exactly a cable network with multiple-limb and many adapters.If localization of fault can only be carried out to single cable, so take multiple jointing with regard to needs apart according to test procedure and just can carry out localization of fault, need spended time more, have a strong impact on work efficiency.
For this reason, for multiple-limb and many adapters aircraft cable network fault-location problem, design can overcome the reference signal of adapter signal attenuation, reduce noise signal to affect fault location system, research cable network signal multiple reflection phenomenon, develops the development trend that the equipment that can realize fault fast positioning in multiple-limb and many adapters aircraft cable network just becomes a certainty.
Summary of the invention
For Problems existing in above-mentioned technology, the object of this invention is to provide a kind of aircraft cable fault localization method based on aircraft cable distributed information database, by the fault detection analysis to reflected signal, and coordinate the distributed intelligence of aircraft cable and cable network database set up in advance, can locate accurately aircraft cable fault and fail result display, for raising aircraft manufacturing assembly work efficiency, eliminate aircraft electrical line fault hidden danger, improve aircraft manufacturing assembling and use and maintenance efficiency, ensure that aircraft safety is all significant.
For achieving the above object, the technical solution adopted in the present invention proposes a kind of aircraft cable fault localization method based on aircraft cable distributed information database, the method utilizes Aircraft Wiring Manual to build aircraft cable network database, and complete aircraft cable network localization of fault based on this database, utilize cable type in WDM handbook and length as known conditions, waveform generator is utilized to produce high-frequency pulse signal, one in a certain type cable is utilized to obtain such cable reflection coefficient, obtain the reflection coefficient of other types cable, the aircraft cable network database needed for fault diagnosis location is built in conjunction with Aircraft Wiring Manual, utilize aircraft cable network database realizing to path query, draw the reflection configuration of cable network under normal circumstances in conjunction with searching route, utilize time domain reflectometry to obtain the reflection configuration of tested cable network simultaneously, by the difference of sampled point corresponding to waveform comparison the method comparison under normal circumstances reflection configuration of cable network and the crest of actual reflection configuration and trough, if difference is greater than setting threshold value, be judged to be abort situation, utilize sampled point, reflection coefficient and the cable network Structure Calculation trouble spot position in tested cable, the realization of this method is based upon on the basis of industrial computer, utilize Labview virtual instrument software to arrange signal transmission cards to realize specifying wave form output, the data that data collecting card collects are processed simultaneously, and realize interpretation of result and the display of image data by Labview virtual instrument software, the method specifically comprises the 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 the length that input cable, by Labview virtual instrument software signalization transmission cards and data acquisition card, launching width is that the burst pulse of 1/200M is as reference signal, and utilize data collecting card to gather reflected signal and calculate the sampling number between transmitting and transmitting, the ratio of computational reflect sampled point and length of cable, as the reflection coefficient going out all kinds of cable;
2) the wire list that Boeing 777 is correlated with in the WDM handbook of type is searched, choose wire list wire harness Bundle No, wire size Wire No, group number Farm, length FT-IN, from equipment end FromEquip, comprise the pin number from equipment end or corresponding types, to equipment end To Equip, be included in pin number or the corresponding types of equipment end, in conjunction with Bandaid block in Boeing 777 airplane type or the multiple-branching construction of aircraft component intraconnection equipment composition, cable type (TY) before simultaneously comprising in the reflection coefficient of all kinds of cable and wirelist, in Labview virtual instrument software, the LabVIEW database access bag LabSQL write based on ADO technology is utilized to sort out above-mentioned information, final formation aircraft cable network overall distribution information database,
3) when measuring beginning, inputting numbering (PIN) corresponding to pin in the wire size of tested cable and this cable tested end Aviation Connector or hole as selected starting point comprises the oriented starting point that a direction to selected starting point extends, by the query generation aircraft cable network subdata base that oriented starting point is corresponding thus to cable network distributed information database;
4) on described industrial computer, utilize ADO technology in Labview virtual instrument software to realize calling of cable network subdata base, utilize length of cable in database, reflection coefficient and corresponding cable network annexation, calculate the reflection configuration under tested cable serviceable condition, thus provide canonical reference waveform for cable network fault diagnosis;
5) utilize AWG (Arbitrary Waveform Generator) transmission frequency 100M, amplitude 1V square-wave signal, and obtain the actual reflection configuration of tested cable network, judge whether tested aircraft cable sub-network breaks down with this waveform, and judge it is short circuit or open circuit fault;
6) utilize waveform generator to send pulsewidth 1/200M pulse signal, and obtain the actual reflection configuration of tested cable network, and utilize signal processing module in the Labview virtual instrument software platform of industrial computer to carry out noise reduction process and waveform standardization;
7) the actual reflection configuration after standardization and the reflection configuration under serviceable condition are carried out comparison of wave shape, if find to there is the larger point of difference through comparison of wave shape, can determine it is that the crest of corresponding sampled point or trough exist change, namely be not inconsistent with the cable network structure under normal condition, and illustrate that this tested cable network exists fault, so place sampled point occurs failure definition is trouble spot, and judges that the branch at place occurs fault thus;
8) utilizing the branch at trouble spot and fault generation sampled point place, by calling cable reflection coefficient and the length of cable of all cables of guilty culprit branch, determining the position of cable fault in this fault branch;
9) by interface protocol, database is connected with the Labview virtual instrument test platform system of industrial computer;
10) virtual instrument test platform operation that database reflected waves graphic data is inquired about, added, deletes, revises.
Described from an equipment end From Equip, comprise the pin number from equipment end or corresponding types, to another equipment end To Equip, be included in pin number or the corresponding types of equipment end, from an equipment end and the port referring to each position on the aircraft that aircraft utilizes Aviation Connector to be connected to another equipment end, wherein comprise a lot of pin in each joint of Aviation Connector, one in the aircraft cable that each pin is corresponding, need to indicate corresponding pin or hole reference numeral and corresponding types and refer to the device type that described equipment end connects.
Described middle Bandaid block refers to that each pin on the joint of described Boeing 777 airplane type interconnected or other pin on this block of Kong Junyu or hole carry out the structure connected.
Effect of the present invention is: utilize the reflection coefficient of aircraft cable reference books and dissimilar aircraft cable to set up aircraft cable overall distribution information database, by reflection detection method, fault detect is carried out to aircraft cable, detection failure result is compared with corresponding aircraft cable ideal distribution information, accurate localizing faults and relevant aircraft cable information.Utilize the present invention can realize fault type and the abort situation judgement of optional position in two branch four joint cable network structures, its fault diagnosis error is less than 0.02 meter, maximum measurement length 200 meters.
Accompanying drawing explanation
Fig. 1 is aircraft cable network Fault Locating Method process flow diagram;
Fig. 2 is that aircraft cable distributed information database and aircraft cable reflect detection failure positioning testing system annexation;
Fig. 3 is example aircraft cable network structure.
Embodiment
By reference to the accompanying drawings a kind of aircraft cable fault localization method based on aircraft cable distributed information database of the present invention is described in detail.
Fig. 1 is the overall flow of the aircraft cable fault localization method that the present invention is based on aircraft cable distributed information database, comprise: the cable type in aircraft cable network database is sorted out, and a sample cable is chosen to each type, determine the type and the length that input cable, by the ratio of computational reflect sampled point and length of cable, calculate the reflection coefficient of all kinds of cable.Search the wire list that Boeing 777 is correlated with in the WDM handbook of type, choose the wire harness Bundle No. in wire list, wire size Wire No., group number Farm, length FT-IN, From Equip is namely from an equipment end, comprising from which pin of equipment end or corresponding types, namely To Equip arrives another equipment end, comprising which pin or the corresponding types that arrive equipment end, the port at each position on the aircraft that aircraft utilizes Aviation Connector to be connected wherein is referred to from an equipment end From Equip and another To Equip equipment end, wherein comprise a lot of pin in each joint of Aviation Connector, one in the aircraft cable that each pin is corresponding, need to indicate corresponding pin or hole reference numeral, wherein corresponding types refers to the device type that this equipment end connects.In conjunction with Bandaid block in aircraft, i.e. a kind of joint of interconnected, other pin on each pin on it or this block of Kong Junyu or hole carry out connecting or the multiple-branching construction of aircraft component intraconnection equipment composition, cable type TY in the reflection coefficient of all kinds of cable before and wire list is sorted out simultaneously, final formation aircraft cable network overall distribution information database, this database intrinsic parameter and attribute once generate in advance, is only consistent with aircraft maintenance handbook.When measuring beginning, input pin in the device number of tested cable and Aviation Connector or numbering PIN corresponding to hole as oriented starting point, selected starting point and to comprise be which direction to this point extends, by the query generation aircraft cable network subdata base that oriented starting point is corresponding thus to cable network distributed information database, aircraft cable network subdata base is a part for aircraft cable network overall distribution information database; All need before each Circuit fault diagnosis starts first to perform this step, the difference of oriented starting point, the aircraft cable network subdata base of generation also can be different.The length of cable, the reflection coefficient of corresponding cable and data cable network connection relation in the aircraft cable network subdata base utilizing oriented starting point corresponding, extrapolate under tested cable serviceable condition reflection configuration, thus provide canonical reference waveform for cable network fault diagnosis.
First utilize waveform generator transmission frequency 100M, amplitude 1V square-wave signal, and obtain the actual reflection configuration of tested cable network; Judge whether tested aircraft cable sub-network breaks down with this waveform, and judge it is short circuit or open circuit fault.After utilize waveform generator to send pulsewidth 1/200M pulse signal, and obtain the actual reflection configuration of tested cable network, and carry out noise reduction process and waveform standardization; Actual reflection configuration after standardization and the reflection configuration under serviceable condition are carried out comparison of wave shape, if find to there is the larger point of difference through comparison of wave shape, can determine it is that the crest of corresponding sampled point or trough exist change, namely be not inconsistent with the cable network structure under normal condition, and illustrate that this tested cable network exists fault, so place sampled point occurs failure definition is trouble spot, and judges that the branch at place occurs fault thus.Utilizing the branch at trouble spot and fault generation sampled point place, by calling cable reflection coefficient and the length of cable of all cables of guilty culprit branch, determining the position of cable fault in this fault branch.By interface protocol, database is connected with virtual instrument test platform system.
As shown in Figure 2, in the process of cable Network Fault Detection and location, database has been used.LabVIEW itself can not direct accessing database, and need to be connected with database software by External Program Interface, wherein ADO is the most widely used technology.Utilize the LabVIEW database access bag LabSQL write based on ADO technology.By LabSQL, user directly can realize access to database and operation in the mode calling sub-VI in LabVIEW again.In virtual instrument test platform, can be operated aircraft cable network overall distribution database by LabView, inquiry, interpolation, deletion, amendment.
Carry out data below in conjunction with example and analysis be described:
In existing cable network database, all cable networks are as shown in Figure 3:
As shown in Figure 3: by inputting oriented starting point W10, C10, select with inferior division:
If during non-fault, namely in whole network without short circuit and open circuit fault, circuit one comprises W10, and W11, W12, W13 are normal, and circuit two comprises W10, and W14, W15, W16 are normal.
Now arrange following fault to verify:
1) when arranging open circuit fault at C16 place, circuit one comprises W10, and W11, W12, W13 are normal, and circuit two comprises W10, and W14, W15, W16 are abnormal, circuit generation open circuit fault, and position W16 occurs fault, holds 0m place apart from C16, consistent with set fault.
2) when arranging open circuit fault near W15 centre, circuit one comprises W10, and W11, W12, W13 are normal, circuit two comprises W10, and W14, W15, W16 are abnormal, circuit generation open circuit fault, there is position W15 in fault, holds 10.18m place apart from C15, consistent with set fault.
3) when arranging short trouble at C16 place, circuit one comprises W10, and W11, W12, W13 are normal, circuit two comprises W10, and W14, W15, W16 are abnormal, circuit is short-circuited fault, and position W16 occurs fault, holds 0.20m place apart from C16, consistent with set fault.
4) when arranging short trouble near W15 centre, circuit one comprises W10, and W11, W12, W13 are normal, circuit two comprises W10, and W14, W15, W16 are abnormal, circuit is short-circuited fault, and position W15 occurs fault, holds 10.19m place apart from C15, consistent with set fault.
Claims (3)
1. the aircraft cable fault localization method based on aircraft cable distributed information database, the method utilizes Aircraft Wiring Manual (WDM) to build aircraft cable network database, and complete aircraft cable network localization of fault based on this database, utilize cable type in WDM handbook and length as known conditions, waveform generator is utilized to produce high-frequency pulse signal, one in a certain type cable is utilized to obtain such cable reflection coefficient, obtain the reflection coefficient of other types cable, the aircraft cable network database needed for fault diagnosis location is built in conjunction with WDM handbook, utilize aircraft cable network database realizing to path query, draw the reflection configuration of cable network under normal circumstances in conjunction with searching route, utilize time domain reflectometry to obtain the reflection configuration of tested cable network simultaneously, by the difference of sampled point corresponding to waveform comparison the method comparison under normal circumstances reflection configuration of cable network and the crest of actual reflection configuration and trough, if difference is greater than setting threshold value, be judged to be abort situation, utilize sampled point, reflection coefficient and the cable network Structure Calculation trouble spot position in tested cable, the realization of this method is based upon on the basis of industrial computer, utilize Labview virtual instrument software to arrange signal transmission cards to realize specifying wave form output, the data that data collecting card collects are processed simultaneously, and realize interpretation of result and the display of image data by Labview virtual instrument software, the method specifically comprises the 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 the length that input cable, by Labview virtual instrument software signalization transmission cards and data acquisition card, launching width is that the burst pulse of 1/200M is as reference signal, and utilize data collecting card to gather reflected signal and calculate the sampling number between transmitting and transmitting, the ratio of computational reflect sampled point and length of cable, as the reflection coefficient going out all kinds of cable;
2) search (wire list) that Boeing 777 is correlated with in the WDM handbook of type, choose the wire harness number (Bundle No) in cable list (wire list), wire size (Wire No), group number (Farm), length FT-IN, from an equipment end (From Equip), comprise the pin number from equipment end or corresponding types, to another equipment end (To Equip), be included in pin number or the corresponding types of equipment end, in conjunction with Bandaid block in Boeing 777 airplane type or the multiple-branching construction of aircraft component intraconnection equipment composition, the reflection coefficient of all kinds of cable and the cable type (TY) in (wire list) before comprising simultaneously, in Labview virtual instrument software, the LabVIEW database access bag LabSQL write based on ADO technology is utilized to sort out above-mentioned information, final formation aircraft cable network overall distribution information database,
3) when measuring beginning, inputting numbering (PIN) corresponding to pin in the wire size of tested cable and this cable tested end Aviation Connector or hole as selected starting point comprises the oriented starting point that a direction to selected starting point extends, by the query generation aircraft cable network subdata base that oriented starting point is corresponding thus to cable network distributed information database;
4) on described industrial computer, utilize ADO technology in Labview virtual instrument software to realize calling of cable network subdata base, utilize length of cable in database, reflection coefficient and corresponding cable network annexation, calculate the reflection configuration under tested cable serviceable condition, thus provide canonical reference waveform for cable network fault diagnosis;
5) utilize AWG (Arbitrary Waveform Generator) transmission frequency 100M, amplitude 1V square-wave signal, and obtain the actual reflection configuration of tested cable network, judge whether tested aircraft cable sub-network breaks down with this waveform, and judge it is short circuit or open circuit fault;
6) utilize waveform generator to send pulsewidth 1/200M pulse signal, and obtain the actual reflection configuration of tested cable network, and utilize signal processing module in the Labview virtual instrument software platform of industrial computer to carry out noise reduction process and waveform standardization;
7) the actual reflection configuration after standardization and the reflection configuration under serviceable condition are carried out comparison of wave shape, if find to there is the larger point of difference through comparison of wave shape, can determine it is that the crest of corresponding sampled point or trough exist change, namely be not inconsistent with the cable network structure under normal condition, and illustrate that this tested cable network exists fault, so place sampled point occurs failure definition is trouble spot, and judges that the branch at place occurs fault thus;
8) utilizing the branch at trouble spot and fault generation sampled point place, by calling cable reflection coefficient and the length of cable of all cables of guilty culprit branch, determining the position of cable fault in this fault branch;
9) by interface protocol, database is connected with the Labview virtual instrument test platform system of industrial computer;
10) in the operation that virtual instrument test platform is inquired about database reflected waves graphic data, added, deletes, revises.
2. a kind of aircraft cable fault localization method based on aircraft cable distributed information database according to claim 1, it is characterized in that: described from an equipment end (From Equip), comprise the pin number from equipment end or corresponding types, to another equipment end (To Equip), be included in pin number or the corresponding types of equipment end, from equipment end and the port referring to each position on the aircraft that aircraft utilizes Aviation Connector to be connected to equipment end, wherein comprise spininess in each joint of Aviation Connector, one in the aircraft cable that each pin is corresponding, need to indicate corresponding pin or hole reference numeral and corresponding types and refer to the device type that described equipment end connects.
3. a kind of aircraft cable fault localization method based on aircraft cable distributed information database according to claim 1, is characterized in that: described middle Bandaid block refers to that each pin on the joint of described Boeing 777 airplane type interconnected or other pin on this block of Kong Junyu or hole carry out the structure connected.
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Effective date of registration: 20160105 Address after: 200120 Zhang Yang Road, Shanghai, Pudong New Area, No. 25 Applicant after: Commercial Aircraft Corporation of China, Ltd. Applicant after: Shanghai Aircraft Manufacturing Co., Ltd. Address before: 200436 Shanghai Road, Zhabei District, No. 3115 Applicant before: Shanghai Aircraft Manufacturing Co., Ltd. |
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