CN103471799B - Impact identification conflict resolution method during digital radio impact monitoring system networking - Google Patents
Impact identification conflict resolution method during digital radio impact monitoring system networking Download PDFInfo
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- CN103471799B CN103471799B CN201310374168.4A CN201310374168A CN103471799B CN 103471799 B CN103471799 B CN 103471799B CN 201310374168 A CN201310374168 A CN 201310374168A CN 103471799 B CN103471799 B CN 103471799B
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Abstract
The invention discloses impact identification conflict resolution method during a kind of digital radio impact monitoring system networking, belong to technical field of aviation health monitoring.The method is passed throughIndividual digital radio impact monitoring system on same structure networking monitoring time, when occurring in a certain system monitoring region according to impact, there is the feature that position is nearest in the sensor distance impact in this region, the high level number of the digital sequence array after extraction sensor response signal conversionization and rising edge number are as characteristic parameter, then the characteristic parameter carrying out discrimination method is chosen, by comparing the characteristic parameter of different digital shock zone monitoring system, select the monitoring system of maximum characteristic parameter as the correct system of identification, the response of shielding other system, avoid producing erroneous judgement.The present invention is with a wide range of applications in terms of the multizone Impact monitoring of large aerospace structure.
Description
Technical field
The present invention relates to impact identification conflict resolution method during a kind of digital radio impact monitoring system networking, belong to
Technical field of aviation health monitoring.
Background technology
It is more and more wider that composite has the advantage application in each field such as specific strength is high, specific stiffness is big, performance can design
General, especially large aerospace structure.The carbon fibre composite of the large-scale seating plane of Air Passenger A380 and A350-XWB in Europe is used
Amount has respectively reached the 25% and 53% of structure gross weight, and the B787 large-scale seating plane composite consumption of Boeing is that structure is total
The 50% of weight, but, Test of Laminate Composites under arms during inevitably to bear various impact, easily cause compound
The internal injury of material structure also causes its mechanical property degradation, and bearing capacity reduces.Therefore composite structure is rushed
Hit monitoring, it is ensured that the stability of structure and safety are to have urgent application demand.
Miniature digital formula is wireless, and impact monitoring system meets the requirement of miniaturization and low-power consumption, by external piezo electric sensor
Array is directly connected with intrasystem comparator array, and the impulse response signal array of piezoelectric sensor array output is through comparing
Device array is converted to digital sequence array later, realizes location and the warning of shock zone according to digital sequence array, thus saves
The data acquisition and the signal that have omited conventional passive structure health monitoring systems amplify the hardware nursed one's health, and have a wide range of applications feelings
Scape.
In practical engineering application, particularly large aerospace structure, its monitored area area is big, comprise wing, fuselage and
Multiple monitoring such as vertical fin position, needs the networking using multiple system to monitor.But when multiple digital radio Impact monitoring system
System is on same structure during networking monitoring, and impact can cause the response of multiple digital radio monitoring system, as without effective punching
Hit identification conflict resolution method, generation is judged by accident.
Summary of the invention
The present invention proposes impact identification conflict resolution method during a kind of digital radio impact monitoring system networking, for
Multiple digital radio impact monitoring systems provide one impact identification conflict resolution method on same structure during networking monitoring,
Make it on the basis of existing shock zone positioning function, it is achieved the impact networking monitoring of large aerospace structure.The present invention is greatly
The multizone Impact monitoring aspect of type aeronautic structure is with a wide range of applications.
The present invention solves that its technical problem adopts the following technical scheme that
A kind of impact identification conflict resolution method during digital radio impact monitoring system networking, whenIndividual digital nothing
Line impact monitoring system is on same structure during networking monitoring, and foundation is impacted when occurring in a certain system monitoring region, this district
There is the feature that position is nearest in the sensor distance impact in territory, extracts the digital sequence array after sensor response signal conversionization
High level number and rising edge number choose as characteristic parameter, the characteristic parameter then carrying out discrimination method, by comparing
The characteristic parameter of different digital shock zone monitoring system, selects the monitoring system of maximum characteristic parameter to be just strictly as identification
System, the response of shielding other system, it is to avoid produce erroneous judgement, describedFor the natural number more than 1.
The characteristic parameter of described discrimination method has chosen following three kinds of methods:
1. chooseThe one-dimensional characteristic parameter high level number composition characteristic vector of individual numeral shock zone monitoring system；
2. chooseThe one-dimensional characteristic parameter rising edge number composition characteristic vector of individual numeral shock zone monitoring system；
3. chooseThe two dimensional character parameter high level number of individual numeral shock zone monitoring system and rising edge array
Become two-dimensional feature vector；DescribedFor the natural number more than 1.
Beneficial effects of the present invention is as follows:
The present invention isIndividual digital radio impact monitoring system provides one impact on same structure during networking monitoring
Identification conflict resolution method, eliminates and works asIndividual digital radio impact monitoring system during networking monitoring, impacts on same structure
Can causeThe response of individual digital wireless monitor system and the impact identification conflict that causes.
The present invention is to be applicable to airborne digital radio impact monitoring system to provide a kind of impact identification conflict resolution
Method so that it is on the basis of existing shock zone positioning function, it is possible to realize the impact group of large aerospace composite structure
Net is monitored and is occurred without impact erroneous judgement.
Accompanying drawing explanation
The implementing procedure figure of impact identification conflict resolution method when Fig. 1 is digital radio impact monitoring system networking.
Fig. 2 large aerospace structure multisystem networking monitoring schematic diagram.
Fig. 3 is that impact event occurs schematic diagram in No. 2 system monitoring regions.
Fig. 4 digital sequence array one-dimensional characteristic vectorWithScattergram.
Fig. 5 digital sequence array one-dimensional characteristic vectorWithScattergram.
Fig. 6 digital sequence array two-dimensional feature vectorWithScattergram.
Detailed description of the invention
Below in conjunction with the accompanying drawings the invention is described in further details.
The present invention a kind of digital shock zone monitoring system group network time impact identification conflict resolution method concrete
Implementing procedure is as shown in Figure 1.
It is located on same structure layoutIndividual digital radio impact monitoring system formsIndividual monitored area；Each system
AccessThe piezoelectric sensor array of individual layout piezoelectric transducer composition Impact monitoring structurally, each piezoelectric transducer
Have with inside digital radio impact monitoring systemOne comparator of the comparator array of individual comparator connects, and impact is sent out
Time raw, each system can obtainThe Serial No. of individual passage.If digital radio impact monitoring system gathers Serial No.
Sample rate be, the sampling length of Serial No. is。
(1) in large aerospace structure multisystem networking as shown in Figure 2 is monitored, monitored area is worked asIn rushed by outside
When hitting, firstIndividual digital radio impact monitoring system obtains digital sequence array when impact occurs respectively, then calculates
ObtainThe high level number of individual system and rising edge number, as characteristic parameter, finally upload characteristic parameter.
(2) center system is used to acceptThe characteristic parameter structural feature vector of individual system, the side of structural feature vector
Method has following three kinds:
1. chooseThe one-dimensional characteristic parameter high level number structure of individual system digits sequence alignmentIndividual characteristic vector,...,。
2. chooseThe one-dimensional characteristic parameter rising edge number structure of individual system digits sequence alignmentIndividual characteristic vector,...,。
3. chooseThe two dimensional character parameter high level number of individual system digits sequence alignment and rising edge number structure two
Dimensional feature vector,...,。
(3) reality chooses any one in above-mentioned three feature vectors in applying, and uses pattern recognition classifier device pair
Individual characteristic vector carries out classifying and export the System Number that maximal eigenvector is corresponding.In order to reduce amount of calculation, pattern recognition divides
Class device can use the linear discrimination classification device of routine, such as grader based on Fisher linear decision rule, based onNeighbour
The grader of estimation criterion.
(4) according to the System Number that pattern recognition classifier device output maximal eigenvector is corresponding, determineNumber monitoring system
Unite as the correct system of identification, the response of shielding other system, it is to avoid produce erroneous judgement.
In order to the tool that impact identification conflict resolution method during digital radio impact monitoring system networking is better described
Body implements step, uses unmanned plane composite wing structures that the specific implementation process of this method is described.
Unmanned plane composite wing a size of 1200mm × 2000mm, arranges 36 piezoelectricity intelligence altogether in airfoil inner surface
Energy interlayer sensor, every four piezoelectric transducers, one Impact monitoring subregion of composition, subregion area is 170mm × 150mm,
Composition 20 monitoring subregion altogether, the gross area that system can be monitored is 850mm × 600mm, the most structurally arranges
2 Impact monitoring regions of 2 digital radio impact monitoring systems compositions；36 piezoelectric SMART layer sensors are divided into two
Group, the system access of each monitored area 18 arranges the piezoelectric sensing of piezoelectric transducer composition Impact monitoring structurally
Device array, the monitored area of each system is made up of 10 sub regions.Piezoelectric transducer and digital radio impact monitoring system
Internal comparator array connects；The each system of impact event can obtain the digital sequence array of 18 passages every time.System is adopted
Integrating the sample rate of Serial No. as 200KHz, the sampling length of Serial No. is 1000.
(1) use impulsive force hammer, apply altogether in the monitored area of No. 2 systems 20 times on unmanned plane wing as shown in Figure 3
Impact, applies 5 times in its 4 sub regions respectively.2 digital radio impact monitoring systems obtain the numeral of every Secondary Shocks respectively
Sequence alignment, and the in real time characteristic parameter high level number of upload digital sequence alignment and rising edge number.
(2) characteristic parameter of 2 systems that every Secondary Shocks obtains is used, according to above-mentioned three kinds of constructing tactics characteristic vector squares
Battle array:
1. one-dimensional characteristic parameter high level number 2 characteristic vectors of structure of 2 system digits sequence alignment are chosen,.After having obtained the one-dimensional characteristic parameter high level of digital sequence array of 1 to 20 Secondary Shocks, build characteristic of correspondence
Vector matrix: [,...,],: [,...,]。
2. one-dimensional characteristic parameter rising edge number 2 characteristic vectors of structure of 2 system digits sequence alignment are chosen,.After having obtained the one-dimensional characteristic parameter rising edge number of digital sequence array of 1 to 20 Secondary Shocks, build correspondence
Eigenvectors matrix: [,...,],: [,...,]。
3. two dimensional character parameter high level number and the rising edge number structure two dimension of 2 system digits sequence alignment are chosen
Characteristic vector.Obtained 2 system 1 to 20 Secondary Shocks digital sequence array two dimensional character parameter high level number and
After rising edge number, build characteristic of correspondence vector matrix: [,...,],: [,...,]。
(3) in order to verify the feasibility of three feature vectors Constructing Policies, choose based on Fisher linear decision rule
Linear discrimination classification device, the most rightWith、WithAndWithClassifying, classification results divides
The most as shown in Figure 4,5, 6, wherein Fig. 4 is one-dimensional characteristic vectorWithScattergram, Fig. 5 be one-dimensional characteristic vectorWithScattergram, Fig. 6 is two-dimensional feature vectorWithScattergram.Scattergram by three feature vectors
Understanding, the System Number that characteristic vector maximum is corresponding is all 2, i.e. impact occurs in the monitored area of No. 2 systems, and this is with real
Border coincide.
(4) determine that No. 2 monitoring systems, as the correct system of identification, shield the response of No. 1 system, thus avoid producing by mistake
Sentence.
Claims (1)
1. an impact identification conflict resolution method during digital radio impact monitoring system networking, it is characterised in that when
Individual digital radio impact monitoring system during networking monitoring, occurs in a certain system monitoring region according to impact on same structure
Time interior, there is the feature that position is nearest in the sensor distance impact in this region, extracts the number after sensor response signal conversionization
The high level number of word sequence alignment and rising edge number, as characteristic parameter, then carry out the characteristic parameter choosing of discrimination method
Take, by comparing the characteristic parameter of different digital shock zone monitoring system, select the monitoring system conduct of maximum characteristic parameter
The correct system of identification, the response of shielding other system, it is to avoid produce erroneous judgement；The characteristic parameter of described discrimination method has been chosen following
Three kinds of methods:
1. chooseThe one-dimensional characteristic parameter high level number composition characteristic vector of individual numeral shock zone monitoring system；
2. chooseThe one-dimensional characteristic parameter rising edge number composition characteristic vector of individual numeral shock zone monitoring system；
3. chooseThe two dimensional character parameter high level number of individual numeral shock zone monitoring system and rising edge number composition two
Dimensional feature vector；DescribedFor the natural number more than 1.
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| CN104215528B (en) * | 2014-09-09 | 2016-08-17 | 南京航空航天大学 | Composite structure shock zone localization method based on energy weighter factor |
| CN108169037B (en) * | 2017-12-15 | 2019-03-29 | 南京航空航天大学 | Continuous heterogeneous large area Impact monitoring network and shock zone localization method |
Citations (4)
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| TW200846644A (en) * | 2007-05-22 | 2008-12-01 | Jen-Tsan Kuan | Method of estimating shock wave parameter |
| CN101701880A (en) * | 2009-08-05 | 2010-05-05 | 南京航空航天大学 | Embedded health monitoring system for active and passive structure of aeroplane |
| WO2010115022A2 (en) * | 2009-04-01 | 2010-10-07 | Purdue Research Foundation | Identification of loads acting on an object |
| CN102889896A (en) * | 2012-09-24 | 2013-01-23 | 南京航空航天大学 | Two-stage noise reduction method for impact monitoring digital sequence of composite structure |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TW200846644A (en) * | 2007-05-22 | 2008-12-01 | Jen-Tsan Kuan | Method of estimating shock wave parameter |
| WO2010115022A2 (en) * | 2009-04-01 | 2010-10-07 | Purdue Research Foundation | Identification of loads acting on an object |
| CN101701880A (en) * | 2009-08-05 | 2010-05-05 | 南京航空航天大学 | Embedded health monitoring system for active and passive structure of aeroplane |
| CN102889896A (en) * | 2012-09-24 | 2013-01-23 | 南京航空航天大学 | Two-stage noise reduction method for impact monitoring digital sequence of composite structure |
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