CN103399256B - The method and apparatus realizing breakdown of conducting wires location - Google Patents
The method and apparatus realizing breakdown of conducting wires location Download PDFInfo
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- CN103399256B CN103399256B CN201310304149.4A CN201310304149A CN103399256B CN 103399256 B CN103399256 B CN 103399256B CN 201310304149 A CN201310304149 A CN 201310304149A CN 103399256 B CN103399256 B CN 103399256B
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Abstract
The present invention relates to a kind of method realizing breakdown of conducting wires location.The method includes extracting the first test signal from wire to be measured；First test signal is carried out time delay processing, thus obtains the second test signal；The 3rd test signal reflected at abort situation to be measured by receive first test signal and the second test signal input multiplier and according to the second test signal and the 3rd test signal output the 4th test signal；4th test signal is integrated computing, to obtain the second test signal and the correlation function operation result of the 3rd test signal；And pair correlation function operation result carries out peakvalue's checking, to determine the abort situation of wire.The advantage of the method is to design specifically tests signal, and using the noise in wire or existing signal as test signal, the signal transmission of wire to be measured can not affected, it is thus able to ensure the data integrity of aircraft wire, is the Perfected process of on-line checking wire multiple-limb network failure.
Description
Technical field
The invention belongs to fault diagnosis field, particularly relate to one and utilize noise territory bounce technique
The method realizing breakdown of conducting wires location.
Background technology
Aircraft wire is to provide the hard of power source and transmission of control signals for Aircraft Electrical System
Part device, is to connect power supply, electromechanical equipment, electronic equipment and control system on aircraft
Important energy source and communication channel.Along with the growth in aircraft machine age, aircraft wire is for a long time complicated
Environment works, the fault such as wearout, aging, corrosion easily occurs, ultimately results in and fly
The short circuit of machine wire and open circuit, work the mischief for flight safety.Examine in existing aircraft wire fault
In survey method, Time Domain Reflectometry detection method is a kind of general measuring technology.Time domain reflection method
Principle be that a low pressure high frequency pulsed reference signal is launched in one end of guiding line, due to wire therefore
Barrier can cause its impedance to change, and reference signal then can reflect at fault.At signal
Incidence end detects reflected signal, utilizes to count the time delay of incoming signal and reflected signal
Calculating breakdown of conducting wires position, the amplitude of reflected signal and direction may determine that the type of fault.Frequency domain
Method for reflection measuring principle is that swept-frequency signal is input to wire to be measured, and by its reflected signal
Measurement data is converted to time-domain information through inverse fast Fourier transform, according to the counterpropagate of wire
Speed changes just can calculate abort situation with the difference of the dielectric material of cable.These methods
Measurement result is more accurate, but need to launch specially and specifically test signal, and test signal is likely
The useful signal of aircraft wire transmission is interfered, it is often more important that due to aircraft working environment
Complexity, is likely mixed into noise signal in reflected signal, cause aircraft wire Weak fault to be difficult to
Diagnosis, and it is not suitable for on-line testing.Spread spectrum technique is the most prominent to on-line testing effect,
Its principle is to launch binary system pseudo noise code or the PN code letter through sine wave modulation to cable under test
Number, the incoming signal of the reflected signal detected Yu delay is carried out related operation, correlator is defeated
Go out to reach maximum, so that it is determined that the time delay of signal, calculate breakdown of conducting wires position with this.This
The method of kind may be used on, in aircraft on-line testing, i.e. also to hold wire in aircraft flight
Continuous test.Although spread spectrum approach can carry out on-line monitoring to aircraft wire, but still needs to send out
Penetrate PN code as test signal, affect the transmission of aircraft wire data, and multiple-limb network is tied
The wire of structure is difficult to detect.
Summary of the invention
In order to solve the problems referred to above, the present invention proposes one and utilizes noise territory bounce technique to realize
Aircraft wire multiple-limb network failure location method, utilize any noise signal in wire or
The arbitrary signal of transmission, as test signal, calculates test signal and the relevant letter postponing signal
Number, obtains the moment corresponding to peak point, it is judged that aircraft wire multiple-limb network failure position.
In order to achieve the above object, it is fixed that what a first aspect of the present invention provided realizes breakdown of conducting wires
The method of position comprises the following steps:
-from wire to be measured, extract the first test signal；
-described first test signal is carried out time delay processing, thus obtain the second test signal；
-the described first test signal received is reflected at abort situation to be measured
The 3rd test signal and described second test signal input multiplier by described multiplier root
According to described second test signal and described 3rd test signal output the 4th test signal；
-described 4th test signal is integrated computing, to obtain described second test letter
Number and described 3rd test signal correlation function operation result；
-described correlation function operation result is carried out peakvalue's checking, to determine described wire
Abort situation.
According to one embodiment of the present of invention, described first test signal is noise signal
Or the either signal transmitted in described wire.
According to one embodiment of the present of invention, described wire is aircraft wire.
Additionally, a second aspect of the present invention also proposed a kind of dress realizing breakdown of conducting wires location
Putting, described device includes:
-extraction element, it extracts the first test signal from wire to be measured；
-the first processing means, its by described first test signal carry out time delay processing, thus
Obtain the second test signal；
-receiving device, it is anti-at abort situation to be measured that it receives described first test signal
The 3rd test signal being emitted back towards；
-the second processing means, it is with described second test signal and described 3rd test signal
As input and it is carried out multiplying and integral operation, to obtain described second test signal
Correlation function operation result with described 3rd test signal；
-determining device, it carries out peakvalue's checking to described correlation function operation result, with really
The abort situation of fixed described wire.
According to one embodiment of the present of invention, described wire to be measured is aircraft wire.
According to one embodiment of the present of invention, described extraction element is data collecting card.
According to one embodiment of the present of invention, described first test signal is noise signal
Or the either signal transmitted in described wire.
The noise territory bounce technique that the present invention provides is a kind of on-line checking aircraft wire multiple-limb net
The method of network fault, utilizes the arbitrary signal of any noise signal in wire or transmission as survey
Trial signal, carries out regular hour delay by test signal, and by aircraft wire abort situation
The signal being reflected back is sent into multiplier together with the delay signal of test signal and is carried out computing, to taking advantage of
Musical instruments used in a Buddhist or Taoist mass output is integrated computing, obtains the correlation function computing knot tested signal with postpone signal
Really, it is analyzed by pair correlation function output data, takes the moment corresponding to peak point, sentence
Disconnected aircraft wire multiple-limb network failure position.The advantage of noise territory bounce technique is to design spy
Fixed test signal, and using the noise in wire or existing signal as test signal, permissible
The most do not affect the signal transmission of wire to be measured.Therefore, noise territory bounce technique is to ensure that aircraft is led
Line data integrity, the Perfected process of on-line checking wire multiple-limb network failure.
Accompanying drawing explanation
The following detailed description to non-limiting example is read by referring to accompanying drawing,
The other features, objects and advantages of the present invention will become more apparent upon:
The noise territory bounce technique that utilizes that Fig. 1 provides for the present invention realizes on-line checking aircraft wire
The method flow diagram of multiple-limb network failure；
The noise territory bounce technique that utilizes that Fig. 2 provides for the present invention realizes on-line checking aircraft wire
The method of multiple-limb network failure is embodied as block diagram.
Detailed description of the invention
The noise territory bounce technique that utilizes that Fig. 1 provides for the present invention realizes on-line checking aircraft wire
Method flow Figure 100 of multiple-limb network failure.As it is shown in figure 1, first extract aircraft to be measured
In noise in wire or wire, the signal of transmission is as noise domain test signal (step
S10), test signal is carried out regular hour delay (step S20), and aircraft is led
The signal being reflected back at line abort situation sends into multiplier together with the delay signal of test signal
Carry out computing (step S30), multiplier output is integrated computing, obtain testing signal
With the correlation function operation result (step S40) of delay signal, exported by pair correlation function
Data are analyzed, and take the moment corresponding to peak point, it is judged that the event of aircraft wire multiple-limb network
Barrier position (step S50).
If there is fault in network of conductors structure, then at breakdown of conducting wires, characteristic impedance there will be change
Change, therefore, reflected signal can be produced at network of conductors structure failure, reflected signal can with enter
Penetrate signal superposition somewhere.Owing to correlation function can reflect depending on of incoming signal and reflected signal
The relation of relying, therefore in the abort situation of aircraft wire multiple-limb network structure, utilizes correlation function
Calculating may determine that abort situation exists kurtosis, determine the kurtosis correspondence moment, utilize letter
Spread speed number in wire is multiplied by peak hour, can be calculated the event in network of conductors
Barrier position.If the abort situation of detection is different from known network conductor structure, then can determine that wire
There is fault in network somewhere.
Putting it briefly, the method realizing breakdown of conducting wires location provided by the present invention includes following
Step:
-from wire to be measured, extract the first test signal (step S10)；
-the first test signal is carried out time delay processing, thus obtain the second test signal (step
Rapid S20)；
-the receive first test signal is reflected at abort situation to be measured the
Three test signals and the second test signal input multiplier and by multiplier according to the second test letter
Number and the 3rd test signal output the 4th test signal (step S30)；
-the 4th test signal is integrated computing, to obtain the second test signal and the 3rd
The correlation function operation result (step S40) of test signal；
-pair correlation function operation result carries out peakvalue's checking, to determine the abort situation of wire
(step S50).
According in one embodiment of the present of invention, the first test signal be noise signal or
The either signal transmitted in wire.
More specifically, it is aircraft wire that method proposed by the invention is primarily adapted for use in wire
Aircraft wire multiple-limb network abort situation detection.
The noise territory bounce technique that utilizes that Fig. 2 provides for the present invention realizes on-line checking aircraft wire
The method of multiple-limb network failure is embodied as block diagram 200.As in figure 2 it is shown, build noise territory
Reflecting experimental platform, the noise territory utilizing data collecting card 210 to obtain at aircraft wire fault is anti-
Penetrate signal, the delay signal of this reflected signal with test signal is carried out correlation function computing, will
The output of correlator sends into computer by an analog-digital converter (ADC in 240) sampling
And it is depicted as delay function, record the correlation peak of each time delay, find out the maximum related value moment,
Utilizing fault location computing module, the time value corresponding with maximum related value by spread speed is taken advantage of
Amass and calculate trouble point.Next introduction is realized breakdown of conducting wires location according to of the present invention
Device, this device includes:
-extraction element 210, it extracts the first test signal from wire to be measured；
-the first processing means 220, its by first test signal carry out time delay processing, thus
Obtain the second test signal；
-receiving device, it receives the first test signal and is reflected back at abort situation to be measured
The 3rd test signal come；
-the second processing means, it tests signal as input using the second test signal and the 3rd
And it is carried out multiplying and integral operation, to obtain the second test signal and the 3rd test letter
Number correlation function operation result；
-determining device 250, its pair correlation function operation result carries out peakvalue's checking, with really
Determine the abort situation of wire.
More specifically, wire to be measured is aircraft wire.
Preferably, extraction element is data collecting card 210.
It is particularly preferred that the first test signal is appointing of being transmitted in noise signal or wire
One signal.
The noise territory bounce technique that the present invention provides is a kind of on-line checking aircraft wire multiple-limb net
The method of network fault, utilizes the arbitrary signal of any noise signal in wire or transmission as survey
Trial signal, carries out regular hour delay by test signal, and by aircraft wire abort situation
The signal being reflected back is sent into multiplier together with the delay signal of test signal and is carried out computing, to taking advantage of
Musical instruments used in a Buddhist or Taoist mass output is integrated computing, obtains the correlation function computing knot tested signal with postpone signal
Really, it is analyzed by pair correlation function output data, takes the moment corresponding to peak point, sentence
Disconnected aircraft wire multiple-limb network failure position.The advantage of noise territory bounce technique is to design spy
Fixed test signal, and using the noise in wire or existing signal as test signal, permissible
The most do not affect the signal transmission of wire to be measured.Therefore, noise territory bounce technique is to ensure that aircraft is led
Line data integrity, the Perfected process of on-line checking wire multiple-limb network failure.
Those skilled in the art will be understood that above-described embodiment is all illustrative and not restrictive
's.The different technologies feature occurred in different embodiments can be combined, useful to obtain
Effect.Those skilled in the art research accompanying drawing, specification and claims on the basis of,
Will be understood that and realize other embodiments changed of disclosed embodiment.At claims
In, term " includes " being not precluded from other devices or step；Indefinite article " one " do not arrange
Except multiple；Term " first ", " second " are used for indicating title not for representing any spy
Fixed order.Any reference in claim is all understood not to protection domain
Limit.Some technical characteristic occurs in that be not meant in different dependent claims can not be by
These technical characteristics are combined obtaining beneficial effect.This patent covers on literal or is waiting
All methods, device and the product of scope of the following claims is fallen into principle.
Claims (7)
1. the method (100) realizing breakdown of conducting wires location, described method includes following step
Rapid:
-from wire to be measured, extract the first test signal (S10)；
-described first test signal is carried out time delay processing, thus obtain the second test signal
(S20)；
-the described first test signal received is reflected at abort situation to be measured
The 3rd test signal and described second test signal input multiplier by described multiplier root
According to described second test signal and described 3rd test signal output the 4th test signal (S30)；
-described 4th test signal is integrated computing, to obtain described second test signal
Correlation function operation result (S40) with described 3rd test signal；
-described correlation function operation result is carried out peakvalue's checking, to determine the event of described wire
Barrier position (S50).
Method the most according to claim 1, wherein, described first test signal is for making an uproar
The either signal transmitted in acoustical signal or described wire.
Method the most according to claim 1, wherein, described wire is aircraft wire.
4. the device (200) realizing breakdown of conducting wires location, described device includes:
-extraction element (210), it extracts the first test signal from wire to be measured；
-the first processing means (220), its by described first test signal carry out time delay processing,
Thus obtain the second test signal；
-receiving device, it receives described first test signal and reflects at abort situation to be measured
The 3rd test signal returned；
-the second processing means, it is made with described second test signal and described 3rd test signal
For input and it is carried out multiplying and integral operation, with obtain described second test signal and
The correlation function operation result of described 3rd test signal；
-determining device (250), it carries out peakvalue's checking to described correlation function operation result,
To determine the abort situation of described wire.
Device the most according to claim 4, it is characterised in that described wire to be measured is
Aircraft wire.
Device the most according to claim 4, it is characterised in that described extraction element (210)
For data collecting card.
Device the most according to claim 4, it is characterised in that described first test letter
Number by the either signal transmitted in noise signal or described wire.
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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 |
| CN111693861B (en) * | 2020-06-24 | 2022-08-05 | 中电科思仪科技股份有限公司 | Switch matrix channel fault diagnosis method and system |
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