CN108169037A - Continuous heterogeneous large area Impact monitoring network and shock zone localization method - Google Patents
Continuous heterogeneous large area Impact monitoring network and shock zone localization method Download PDFInfo
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Abstract
The invention discloses a kind of continuous heterogeneous large area Impact monitoring network and shock zone localization methods, belong to aerospace Smart Structure Teehnology field.Continuous heterogeneous large area Impact monitoring network is alternately arranged and is formed by line style piezoelectric transducer continuous series array and the discrete independent array of line style piezoelectric transducer, and entire monitoring network is embedded in inside aircraft composite structure or is arranged in body structure surface and forms smart skins.When structure is impacted by external object, monitoring network output impulse response signal, impulse response signal is judged the position of impact generation by shock zone localization method after digitlization.The present invention can greatly reduce data acquisition channel number needed for sensor lead quantity required during aircraft smart skins large area Impact monitoring and impact monitoring system, impact monitoring system processor complexity can be reduced and reduce the power consumption required when calculating impact position, so as to improve impact monitoring system reliability.
Description
Technical field
The present invention relates to a kind of continuous heterogeneous large area Impact monitoring network and shock zone localization methods, belong to aviation
Space flight Smart Structure Teehnology field.
Background technology
The basic thought of aircraft Intelligent Skin Technology is to cover a large amount of sensing/driving element and microprocessor with main body
Skin structure is integrated into an entirety, passes through the letters such as environment, working condition, the health status of a large amount of sensing element monitoring of structures
Breath forms control excitation, changes shape, movement, stress of structure etc. after processing.Intelligent Skin Technology causes covering knot
Structure has the abilities such as self diagnosis, adaptive, self study, selfreparing in itself.Therefore, aircraft Intelligent Skin Technology is that raising is advanced
The flying quality of aircraft, the important technology guarantee for operating mobility, environment sensing performance and security maintenance performance.
In aircraft smart skins, monitoring structural health conditions and diagnosis are one of Core Features.In recent years, because of composite material
Structure has many advantages, such as that specific stiffness is big, and flexible design strong to fatigue and corrosion resistance, Flight Vehicle Structure, particularly wing
Main force support structures is waited largely to use composite structure.However, for aircraft composite structure, exterior object rushes
It hits, such as bird is hit, hail, rubble, maintenance tool etc., easily causes the interior laminate layer, MATRIX CRACKING and fibre of composite structure
Dimension fracture equivalent damage, leads to declining to a great extent for its mechanical performance, and bearing capacity reduces significantly, whole destruction and failure to structure
Form potential threaten.For Large Scale Space Vehicle, often there are multiple large-sized composite material structures, such as wing, machine
Body and vertical fin etc., therefore there is an urgent need to carry out the large area Impact monitoring of aircraft composite structure.Further, since aircraft
The impact of structure is a kind of random transient affair, needs to be monitored it at the time of impacting and occurring.So Impact monitoring
The sensor network that system and Impact monitoring use, which must be installed in as a kind of airborne equipment on aircraft, to carry out online, even
Continue continual Impact monitoring, and meet airborne and apply to requirements such as the lightweights, low-power consumption, high reliability of system.
Impact monitoring system conventional at present realizes accurate im-pact location and assessment to obtain impact signal, comprising by
Signal amplifier, wave filter and digital analog converter composition analog circuit and support the microprocessor of complicated monitoring algorithm and outer
The digital circuit of peripheral device composition, when carrying out large area monitoring to large-scale structure, required sensing passage number is more in addition, leads
The volume of cause system entirety is big, weight is big and power consumption is big, and reliability is difficult to guarantee, so being extremely difficult to airborne application
It is required that.The it is proposed of miniature digital formula impact monitoring system provides good thinking in order to solve the above problem.The base of the system
This operation principle is the impulse response signal direct digitization for the voltage form for exporting sensor, and passes through field-programmable
Impulse response signal after logic gate array acquisition digitlization realizes the shock zone positioning based on Serial No..Since this is
Micro- place of system undesired signal amplifier, the analog circuit of wave filter and digital analog converter composition and the complicated monitoring algorithm of support
Manage the digital circuit of device and peripheral components composition, thus the system have small, light weight, it is low in energy consumption, can carry out it is online
The characteristics of real-time impact monitors.
But either using conventional impact monitoring system or miniature digital formula impact monitoring system, be required for by
External sensor network real-time response impulse response signal caused by the impact event of structure.In sensor network
Each sensor independently occupies a data acquisition channel of impact monitoring system.If in the Impact monitoring for implementing large area
When, when particularly realizing the aircraft smart skins with Impact monitoring ability, the density of sensor is big, quantity is more, so as to make
Obtaining impact monitoring system needs very more channels large area sensor network to be supported to carry out Impact monitoring.It can at least lead in this way
Cause following the problem of being unfavorable for Impact monitoring sensor network and airborne impact monitoring system：（1）A large amount of sensor needs
A large amount of lead is wanted, increase weight and is unfavorable for cabling aboard；（2）The data acquisition channel number of impact monitoring system
Mesh increases, and the volume, weight and power consumption of impact monitoring system is caused to increase, and reliability reduces.Therefore, urgent need will propose a kind of skill
Art can greatly reduce in aircraft smart skins large area sensor network is not increased in the case of number of sensors
Pin count and impact monitoring system data acquisition channel number needed for sensor network.
Invention content
The present invention for solve aircraft smart skins large area sensor network port number cause more lead impost it is big,
A kind of the problem of impact monitoring system volume, weight and power consumption increase and reliability reduce, it is proposed that continuous heterogeneous large area
Impact monitoring network and shock zone localization method pass when can greatly reduce aircraft smart skins large area Impact monitoring
Sensor network pin count and impact monitoring system data acquisition channel number, can reduce impact monitoring system processor complexity and
Power consumption required during impact position is calculated, so as to improve impact monitoring system reliability.
The present invention is adopted the following technical scheme that solve its technical problem：
A kind of continuous heterogeneous large area Impact monitoring network, includingn×mA piezoelectric transducer, compositionnRow ×mThe piezoelectricity of row
Sensor array, wherein, each piezoelectric transducer has anode and cathode,nWithmIt is the natural number more than 1；It is describednRow ×mRow
Piezoelectric sensor array in, including line style piezoelectric transducer continuous series array and the discrete independent battle array of line style piezoelectric transducer
Row, the line style piezoelectric transducer continuous series array and the discrete independent array of line style piezoelectric transducer are alternately arranged composition,
Concrete structure is as follows：
WhennDuring for odd number,nIn row piezoelectric transducer, odd-numbered linemA piezoelectric transducer composition line style piezoelectric transducer is continuous
Serial array, even number linemA piezoelectric transducer forms the discrete independent array of line style piezoelectric transducer；In line style piezoelectric transducer
In continuous series array, the anode of the 1st piezoelectric transducer is connect with data acquisition channel, the cathode of the 1st piezoelectric transducer
It being connect with the anode of the 2nd piezoelectric transducer, the cathode of the 2nd piezoelectric transducer is connect with the anode of the 3rd piezoelectric transducer,
And so on, lastmThe cathode of a piezoelectric transducer is connect with ground wire；In the discrete independent array of line style piezoelectric transducer,
The anode of each piezoelectric transducer is connect with data acquisition channel, and the cathode of each piezoelectric transducer is connect with ground wire；Above-mentioned
In entire continuous heterogeneous large area Impact monitoring network, comprising (n+1)/2 line style piezoelectric transducer continuous series array and
(n-1)/2 discrete independent array of line style piezoelectric transducer；
WhennDuring for even number,nIn row piezoelectric transducer, odd-numbered line or even number linemA piezoelectric transducer composition line style piezoelectricity passes
Sensor continuous series array, therewith alternate even number line or odd-numbered linemA piezoelectric transducer composition line style piezoelectric transducer from
Dissipate independent array；In line style piezoelectric transducer continuous series array, the anode and data acquisition channel of the 1st piezoelectric transducer
Connection, the cathode of the 1st piezoelectric transducer connect with the anode of the 2nd piezoelectric transducer, the cathode of the 2nd piezoelectric transducer and
The anode connection of 3rd piezoelectric transducer, and so on, last themThe cathode of a piezoelectric transducer is connect with ground wire；In line style
In the discrete independent array of piezoelectric transducer, the anode of each piezoelectric transducer is connect with data acquisition channel, each piezoelectric sensing
The cathode of device is connect with ground wire；In above-mentioned entire continuous heterogeneous large area Impact monitoring network, comprisingn/ 2 line style piezoelectricity
Sensor continuous series array andn/ 2 discrete independent array of line style piezoelectric transducer.
A kind of shock zone localization method of continuous heterogeneous large area Impact monitoring network, includes the following steps：
Step 1：It calculates in line style piezoelectric transducer continuous series array and the discrete independent array of line style piezoelectric transducer, number
The first leading edge position of the impulse response signal of change；
Step 2：It finds out in all discrete independent array of line style piezoelectric transducer, first leading edge position is near preceding the first two
Piezoelectric transducer is denoted as A respectively1And A2；
Step 3：It finds out in all line style piezoelectric transducer continuous series arrays, first leading edge position is near a preceding line
Type piezoelectric transducer continuous series array, and by the line style piezoelectric transducer continuous series array with A1And A2In same row
Two piezoelectric transducers are denoted as B1And B2；
Step 4：The zone location occurred will be impacted by A1、A2、B1、B2It is surrounded by this 4 piezoelectric transducers as vertex
Rectangular configuration region in.
The invention has the advantages that：
（1）When aircraft smart skins includen×mDuring a piezoelectric transducer composition Impact monitoring network, 1+ is neededn×mRoot
Lead（Containing ground wire）, and impact monitoring system needsn×mA data acquisition channel, and use proposed by the present invention continuous different
Configuration large area Impact monitoring network, at most only needs 1+n×(1+m)/2 piece lead（Containing ground wire）, impact monitoring system only needs
It willn×(1+m)/2 data acquisition channel, thus when aircraft smart skins large area Impact monitoring can be significantly reduced pass
Data acquisition channel number needed for the pin count and impact monitoring system of sensor network.
（2）Shock zone localization method proposed by the present invention is very simple, can reduce impact monitoring system processor and answer
It is miscellaneous to spend and reduce the power consumption required when calculating impact position, so as to improve impact monitoring system reliability.
Description of the drawings
Fig. 1 is the continuous heterogeneous large area Impact monitoring network diagram of aircraft smart skins.
Fig. 2 is the continuous heterogeneous large area Impact monitoring network exemplary embodiments schematic diagram of aircraft smart skins.
Fig. 3 is the digitized impulse response signal Waterfall plot obtained after impact occurs.
Specific embodiment
Technical scheme of the present invention is described in detail below in conjunction with the accompanying drawings.
Fig. 1 show the continuous heterogeneous large area Impact monitoring network diagram of typical aircraft smart skins.Entirely
Monitoring network includesn×mA piezoelectric transducer, compositionnRow ×mThe piezoelectric sensor array of row, whereinnFor even number.Entire pressure
Electric transducer array is alternately arranged by line style piezoelectric transducer continuous series array and the discrete independent array of line style piezoelectric transducer
It forms, the 1st row piezoelectric transducer composition line style piezoelectric transducer continuous series array, the 2nd row piezoelectric transducer composition line style pressure
The discrete independent array of electric transducer, and so on, then- 1 row piezoelectric transducer forms line style piezoelectric transducer continuous series battle array
Row, thenRow piezoelectric transducer forms the discrete independent array of line style piezoelectric transducer.In line style piezoelectric transducer continuous series array
In, the anode of the 1st piezoelectric transducer（+）It is connect with the data acquisition channel of impact monitoring system, the 1st piezoelectric transducer
Cathode（-）It is connect with the anode of the 2nd piezoelectric transducer, the cathode and the 3rd piezoelectric transducer of the 2nd piezoelectric transducer are just
Pole connects, and so on, last themThe cathode of a piezoelectric transducer is connect with ground wire；In the discrete independence of line style piezoelectric transducer
In array, the anode of each piezoelectric transducer and the data acquisition channel of impact monitoring system connect, each piezoelectric transducer
Cathode is connect with ground wire；In above-mentioned entire continuous heterogeneous large area Impact monitoring network, comprisingn/ 2 line style piezoelectric sensings
Device continuous series array andn/ 2 discrete independent array of line style piezoelectric transducer.
The present embodiment is by taking the typical regional area of an aircraft skin structure as an example, to the continuous of aircraft smart skins
The specific implementation process of heterogeneous large area Impact monitoring network and shock zone localization method describes in detail.It is wrapped in Fig. 2
Included the typical regional area surface for being arranged in aircraft skin structure continuous heterogeneous large area Impact monitoring network and its
The impact monitoring system being attached thereto.Wherein, continuous heterogeneous large area Impact monitoring network includesn×mA piezoelectric transducer,
Whereinn =4,m= 4.In this 4 row piezoelectric transducer, two line style piezoelectric transducer continuous series arrays and two are included
The discrete independent array of line style piezoelectric transducer, wherein, 4 piezoelectric transducers of the 1st row and the 3rd row separately constitute line style piezoelectricity biography
Sensor continuous series array, the two line style piezoelectric transducer continuous series arrays acquire respectively with the data of impact monitoring system
Channel 1 and 6 connects；4 piezoelectric transducers of the 2nd row and the 4th row separately constitute the discrete independent array of line style piezoelectric transducer, the
Each piezoelectric transducer in one discrete independent array of line style piezoelectric transducer acquires respectively with the data of impact monitoring system
Channel 2,3,4,5 connects, each piezoelectric transducer in second discrete independent array of line style piezoelectric transducer respectively with impact
The data acquisition channel 7,8,9,10 of monitoring system.In line style piezoelectric transducer continuous series array, the 1st piezoelectric transducer
Anode and impact monitoring system data acquisition channel connect, the cathode and the 2nd piezoelectric transducer of the 1st piezoelectric transducer
Anode connection, the cathode of the 2nd piezoelectric transducer connect with the anode of the 3rd piezoelectric transducer, the 3rd piezoelectric transducer
Cathode is connect with the anode of the 4th piezoelectric transducer, and the cathode of the 4th piezoelectric transducer is connect with ground wire.It is passed in line style piezoelectricity
In the discrete independent array of sensor, the anode of each piezoelectric transducer and the data acquisition channel of impact monitoring system connect, each
The cathode of piezoelectric transducer is connect with ground wire.
When aircraft intelligent skin structure is subjected to impact, impact position as shown in Figure 2, continuous heterogeneous large area punching
Monitoring network output impulse response signal is hit, after digitlization, digitized impulse response signal is formed, gives as shown in Figure 3
The impulse response signal of impulse response signal that each data acquisition channel of impact monitoring system obtains after digitlization is gone out.
The position of impact generation is finally judged by shock zone localization method.Shock zone localization method includes following steps：
Step 1：It calculates in line style piezoelectric transducer continuous series array and the discrete independent array of line style piezoelectric transducer, number
The first leading edge position of the impulse response signal of change；
Step 2：It finds out in all discrete independent array of line style piezoelectric transducer, first leading edge position is near preceding the first two
Piezoelectric transducer is denoted as A respectively1And A2.The head of channel 2 and the digitized impulse response signal corresponding to channel 3 in figure 3
A leading edge position is leaned on than the first leading edge position of the digitized impulse response signal corresponding to channel 4,5,7,8,9,10
Before, so A1And A2Corresponding two piezoelectric transducers are as shown in Figure 2；
Step 3：It finds out in all line style piezoelectric transducer continuous series arrays, first leading edge position is near preceding line style pressure
Electric transducer continuous series array, and by the line style piezoelectric transducer continuous series array with A1And A2At two of same row
Piezoelectric transducer is denoted as B1And B2.The first leading edge position of digitized impulse response signal corresponding to channel 1 in figure 3
The first leading edge position of digitized impulse response signal corresponding to than channel 6 is forward, so B1And B2Corresponding two pressures
Electric transducer is as shown in Figure 2；
Step 4：The zone location occurred will be impacted by A1、A2、B1、B2It is surrounded by this 4 piezoelectric transducers as vertex
Rectangular configuration region in.
In the present embodiment, if using conventional Impact monitoring network and shock zone localization method, 16 piezoelectricity pass
Sensor needs 17 leads（1 ground wire shared containing 16 piezoelectric transducers）, the 16 data acquisitions of impact monitoring system needs
Channel；And if using continuous heterogeneous large area Impact monitoring network proposed by the present invention and shock zone localization method, only
Need 11 leads（Containing ground wire）, impact monitoring system only needs 10 data acquisition channels.
Claims (2)
1. a kind of continuous heterogeneous large area Impact monitoring network, it is characterised in that：Includingn×mA piezoelectric transducer, compositionn
Row ×mThe piezoelectric sensor array of row, wherein, each piezoelectric transducer has anode and cathode,nWithmIt is the nature more than 1
Number；It is describednRow ×mIn the piezoelectric sensor array of row, passed including line style piezoelectric transducer continuous series array and line style piezoelectricity
The discrete independent array of sensor, the line style piezoelectric transducer continuous series array and the discrete independent array of line style piezoelectric transducer are handed over
For rearranging, concrete structure is as follows：
WhennDuring for odd number,nIn row piezoelectric transducer, odd-numbered linemA piezoelectric transducer composition line style piezoelectric transducer is continuous
Serial array, even number linemA piezoelectric transducer forms the discrete independent array of line style piezoelectric transducer；In line style piezoelectric transducer
In continuous series array, the anode of the 1st piezoelectric transducer is connect with data acquisition channel, the cathode of the 1st piezoelectric transducer
It being connect with the anode of the 2nd piezoelectric transducer, the cathode of the 2nd piezoelectric transducer is connect with the anode of the 3rd piezoelectric transducer,
And so on, lastmThe cathode of a piezoelectric transducer is connect with ground wire；In the discrete independent array of line style piezoelectric transducer,
The anode of each piezoelectric transducer is connect with data acquisition channel, and the cathode of each piezoelectric transducer is connect with ground wire；Above-mentioned
In entire continuous heterogeneous large area Impact monitoring network, comprising (n+1)/2 line style piezoelectric transducer continuous series array and
(n-1)/2 discrete independent array of line style piezoelectric transducer；
WhennDuring for even number,nIn row piezoelectric transducer, odd-numbered line or even number linemA piezoelectric transducer composition line style piezoelectricity passes
Sensor continuous series array, therewith alternate even number line or odd-numbered linemA piezoelectric transducer composition line style piezoelectric transducer from
Dissipate independent array；In line style piezoelectric transducer continuous series array, the anode and data acquisition channel of the 1st piezoelectric transducer
Connection, the cathode of the 1st piezoelectric transducer connect with the anode of the 2nd piezoelectric transducer, the cathode of the 2nd piezoelectric transducer and
The anode connection of 3rd piezoelectric transducer, and so on, last themThe cathode of a piezoelectric transducer is connect with ground wire；In line style
In the discrete independent array of piezoelectric transducer, the anode of each piezoelectric transducer is connect with data acquisition channel, each piezoelectric sensing
The cathode of device is connect with ground wire；In above-mentioned entire continuous heterogeneous large area Impact monitoring network, comprisingn/ 2 line style piezoelectricity
Sensor continuous series array andn/ 2 discrete independent array of line style piezoelectric transducer.
2. a kind of shock zone localization method of continuous heterogeneous large area Impact monitoring network according to claim 1,
It is characterised in that it includes following steps：
Step 1：It calculates in line style piezoelectric transducer continuous series array and the discrete independent array of line style piezoelectric transducer, number
The first leading edge position of the impulse response signal of change；
Step 2：It finds out in all discrete independent array of line style piezoelectric transducer, first leading edge position is near preceding the first two
Piezoelectric transducer is denoted as A respectively1And A2；
Step 3：It finds out in all line style piezoelectric transducer continuous series arrays, first leading edge position is near a preceding line
Type piezoelectric transducer continuous series array, and by the line style piezoelectric transducer continuous series array with A1And A2In same row
Two piezoelectric transducers are denoted as B1And B2；
Step 4：The zone location occurred will be impacted by A1、A2、B1、B2It is surrounded by this 4 piezoelectric transducers as vertex
In rectangular configuration region.
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| CN110319955A (en) * | 2018-03-29 | 2019-10-11 | 泰科电子(上海)有限公司 | Piezoelectric membrane detection device and piezoelectric film sensor |
| CN110688705A (en) * | 2018-07-02 | 2020-01-14 | 空中客车简化股份公司 | Aircraft and method for estimating impact parameters on the skin of an aircraft |
| WO2020029512A1 (en) * | 2018-08-10 | 2020-02-13 | 南京航空航天大学 | Smart aircraft skin impact area positioning method based on truncated reverse weighted sum |
| CN113720878A (en) * | 2021-08-16 | 2021-11-30 | 中国飞机强度研究所 | Combined piezoelectric intelligent interlayer and connecting device thereof |
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