CN108169037B - 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 exports impulse response signal, and impulse response signal judges the position that impact occurs after digitlization, by shock zone localization method.Data acquisition channel number needed for the present invention can greatly reduce sensor lead quantity and impact monitoring system required when aircraft smart skins large area Impact monitoring, impact monitoring system processor complexity can be reduced and reduce the power consumption required when calculating impact position, 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 technique
The basic thought of aircraft Intelligent Skin Technology is to cover a large amount of sensing/driving element and microprocessor and main body
Skin structure is integrated into an entirety, is believed by environment, working condition, health status of a large amount of sensing element monitoring of structures etc.
Breath forms control excitation after processing, changes shape, movement, stress of structure etc..Intelligent Skin Technology makes covering knot
Structure itself has the abilities such as self diagnosis, adaptive, self study, selfreparing.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 functions.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, especially wing
Equal main force support structures largely use composite structure.However, exterior object rushes for aircraft composite structure
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, the 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 on aircraft as a kind of airborne equipment, to carry out online, even
Continue continual Impact monitoring, and meets airborne and apply to the requirement such as lightweight, 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, 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 working 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 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 in size, light weight, it is low in energy consumption, be able to 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, require by
External sensor network real-time response impulse response signal due to 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 especially realizing the aircraft smart skins with Impact monitoring ability, the density of sensor is big, quantity is more, to make
It obtains impact monitoring system and needs very more channels to support large area sensor network to carry out Impact monitoring.It can at least lead in this way
Cause following to be unfavorable for Impact monitoring sensor network and the airborne problem of impact monitoring system: (1) a large amount of sensor needs
A large amount of lead is wanted, weight is increased 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 be greatly reduced in not increasing aircraft smart skins large area sensor network in the case where number of sensors
Pin count needed for sensor network and impact monitoring system data acquisition channel number.
Summary of the invention
The present invention be solve aircraft smart skins large area sensor network port number cause more lead impost it is big,
The problem of impact monitoring system volume, weight and power consumption increase and reliability reduces, proposes a kind of continuous heterogeneous large area
Impact monitoring network and shock zone localization method, biography 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 when impact position is calculated, to improve impact monitoring system reliability.
The present invention is to solve its technical problem to adopt the following technical scheme that
A kind of continuous heterogeneous large area Impact monitoring network, includingn×mA piezoelectric transducer, compositionnRow ×mColumn
Piezoelectric sensor array, wherein each piezoelectric transducer has anode and cathode,nWithmIt is the natural number greater than 1；It is describednRow
×mIn the piezoelectric sensor array of column, including line style piezoelectric transducer continuous series array and line style piezoelectric transducer it is discrete solely
Vertical array, the line style piezoelectric transducer continuous series array and the discrete independent array of line style piezoelectric transducer are alternately arranged group
At specific structure is as follows:
WhennWhen for odd number,nIn row piezoelectric transducer, odd-numbered linemA piezoelectric transducer forms line style piezoelectric transducer
Continuous series array, even number linemA piezoelectric transducer forms the discrete independent array of line style piezoelectric transducer；It is passed in line style piezoelectricity
In sensor continuous series array, the anode of the 1st piezoelectric transducer is connect with data acquisition channel, the 1st piezoelectric transducer
Cathode is connect with the anode of the 2nd piezoelectric transducer, the cathode of the 2nd piezoelectric transducer and the anode of the 3rd piezoelectric transducer
Connection, and so on, last themThe cathode of a piezoelectric transducer is connect with ground wire；In the discrete independent battle array of line style piezoelectric transducer
In column, the anode of each piezoelectric transducer is connect with data acquisition channel, and the cathode of each piezoelectric transducer is connect with ground wire；?
In above-mentioned entire continuous heterogeneous large area Impact monitoring network, comprising (n+1)/2 line style piezoelectric transducer continuous series battle array
Column and (n-1)/2 discrete independent array of line style piezoelectric transducer；
WhennWhen for even number,nIn row piezoelectric transducer, odd-numbered line or even number linemA piezoelectric transducer forms line style pressure
Electric transducer continuous series array, therewith alternate even number line or odd-numbered linemA piezoelectric transducer forms line style piezoelectric sensing
The discrete independent array of device；In line style piezoelectric transducer continuous series array, anode and the data of the 1st piezoelectric transducer are acquired
Channel connection, the cathode of the 1st piezoelectric transducer are connect with the anode of the 2nd piezoelectric transducer, and the 2nd piezoelectric transducer is born
Pole is connect with the anode of the 3rd piezoelectric transducer, and so on, last themThe 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, each piezoelectricity
The cathode of sensor is connect with ground wire；In above-mentioned entire continuous heterogeneous large area Impact monitoring network, includen/ 2 line styles
Piezoelectric transducer 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: calculating in line style piezoelectric transducer continuous series array and the discrete independent array of line style piezoelectric transducer,
The first leading edge position of digitized impulse response signal；
Step 2: it finds out in all discrete independent array of line style piezoelectric transducer, first leading edge position is near preceding
Two piezoelectric transducers, are 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 preceding one
A line style piezoelectric transducer continuous series array, and by the line style piezoelectric transducer continuous series array with A1And A2Same
Two piezoelectric transducers of column are denoted as B1And B2；
Step 4: the zone location that impact is occurred is by A1、A2、B1、B2By this 4 piezoelectric transducers as vertex institute
In the rectangular configuration region surrounded.
The invention has the following advantages:
(1) when aircraft smart skins includen×mWhen a piezoelectric transducer composition Impact monitoring network, 1+ is neededn×mRoot lead (contains ground wire), and impact monitoring system needsn×mA data acquisition channel, and use proposed by the present invention continuous
Heterogeneous large area Impact monitoring network, at most only needs 1+n×(1+m)/2 piece lead (contains ground wire), and impact monitoring system is only
It needsn×(1+m)/2 data acquisition channel, therefore when can be significantly reduced aircraft smart skins large area Impact monitoring
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, and it is multiple can to reduce impact monitoring system processor
Miscellaneous degree simultaneously reduces the power consumption required when calculating impact position, to improve impact monitoring system reliability.
Detailed description of the invention
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 solution of the present invention is described in detail with reference to the accompanying drawing.
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 column, 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 forms line style piezoelectric transducer continuous series array, and the 2nd row piezoelectric transducer forms 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
Column, 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 is connect with the data acquisition channel of impact monitoring system, the 1st piezoelectric transducer
Cathode (-) is connect with the anode of the 2nd piezoelectric transducer, and the cathode and the 3rd piezoelectric transducer of the 2nd piezoelectric transducer are just
Pole connection, 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 is connect with the data acquisition channel of impact monitoring system, each piezoelectric transducer
Cathode is connect with ground wire；In above-mentioned entire continuous heterogeneous large area Impact monitoring network, includen/ 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 continuous heterogeneous large area Impact monitoring network for being arranged in the typical regional area surface of aircraft skin structure 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.It include two line style piezoelectric transducer continuous series arrays and two in this 4 row piezoelectric transducer
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 are acquired with the data of impact monitoring system respectively
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 is acquired with the data of impact monitoring system respectively
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 connect with the data acquisition channel of impact monitoring system, the cathode and the 2nd piezoelectric transducer of the 1st piezoelectric transducer
Anode connection, the cathode of the 2nd piezoelectric transducer connect with the positive 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 is connect with the data acquisition channel of impact monitoring system, 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 to form digitized impulse response signal after digitlization, give 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 including the following steps:
Step 1: calculating in line style piezoelectric transducer continuous series array and the discrete independent array of line style piezoelectric transducer,
The first leading edge position of digitized impulse response signal；
Step 2: it finds out in all discrete independent array of line style piezoelectric transducer, first leading edge position is near preceding
Two piezoelectric transducers, are denoted as A respectively1And A2.The digitized impulse response signal corresponding to channel 2 and channel 3 in Fig. 3
First leading edge position than digitized impulse response signal corresponding to channel 4,5,7,8,9,10 first rising edge position
Before resting against, 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
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.The first rising edge of digitized impulse response signal corresponding to channel 1 in Fig. 3
Position is more forward than the first leading edge position of digitized impulse response signal corresponding to channel 6, so B1And B2Corresponding two
A piezoelectric transducer is as shown in Figure 2；
Step 4: the zone location that impact is occurred is by A1、A2、B1、B2By this 4 piezoelectric transducers as vertex institute
In the rectangular configuration region surrounded.
In the present embodiment, if using conventional Impact monitoring network and shock zone localization method, 16 piezoelectricity are passed
Sensor needs 17 leads (1 ground wire shared containing 16 piezoelectric transducers), and impact monitoring system needs 16 data acquisitions
Channel；And if using continuous heterogeneous large area Impact monitoring network proposed by the present invention and shock zone localization method, only
11 leads (containing ground wire) is needed, 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 column, wherein each piezoelectric transducer has anode and cathode,nWithmIt is the nature greater than 1
Number；It is describednRow ×mIn the piezoelectric sensor array of column, including line style piezoelectric transducer continuous series array and line style piezoelectricity pass
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, specific structure is as follows:
WhennWhen 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；
WhennWhen 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 are 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, includen/ 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 characterized by comprising the following steps:
Step 1: calculating 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: finding out in all line style piezoelectric transducer continuous series arrays, and 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 that impact is occurred is by A1、A2、B1、B2The square that this 4 piezoelectric transducers are surrounded as vertex
In shape structural region.
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| CN110319955B (en) * | 2018-03-29 | 2021-06-18 | 泰科电子(上海)有限公司 | Piezoelectric film detection device and piezoelectric film sensor |
| FR3083215A1 (en) * | 2018-07-02 | 2020-01-03 | Airbus (S.A.S.) | AIRCRAFT EQUIPPED WITH AN IMPACT PARAMETER ESTIMATION SYSTEM |
| CN109159913B (en) * | 2018-08-10 | 2019-08-30 | 南京航空航天大学 | Localization method of aircraft intelligent skin impact area based on truncated reverse weighted sum |
| CN113720878B (en) * | 2021-08-16 | 2024-08-13 | 中国飞机强度研究所 | Combined piezoelectric intelligent interlayer and connecting device thereof |
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| US5911158A (en) * | 1996-02-29 | 1999-06-08 | The United States Of America As Represented By The Secretary Of The Air Force | Piezoelectric strain sensor array |
| US7143654B2 (en) * | 2003-12-11 | 2006-12-05 | Massachusetts Institute Of Technology | Methods and apparatus for detecting the presence, intensity, trajectory or location of a liquid stream |
| FR2901610B1 (en) * | 2006-05-24 | 2009-01-16 | Airbus France Sas | DEVICE FOR NON-DESTRUCTIVE CONTROL OF STRUTURE BY VIBRATION ANALYSIS |
| CN102288346B (en) * | 2011-07-11 | 2013-07-03 | 南京航空航天大学 | Miniaturized digital large-scale sensor array impact monitoring system |
| CN103438794B (en) * | 2013-08-13 | 2016-10-12 | 南京航空航天大学 | A kind of engineering structure impact position based on piezoelectric sensing network determines method |
| CN103471799B (en) * | 2013-08-26 | 2016-08-10 | 南京航空航天大学 | Shock identification and conflict resolution method for digital wireless shock monitoring system networking |
| 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 |
| CN104597126B (en) * | 2015-01-07 | 2017-02-22 | 北京卫星环境工程研究所 | Method for detecting structure health of spacecraft based on acoustic sensor |
| US10155373B2 (en) * | 2015-10-16 | 2018-12-18 | Quest Integrated, Llc | Printed multifunctional skin for aerodynamic structures, and associated systems and methods |
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