CN104181230B - Composite material plate structure damage monitoring method - Google Patents
Composite material plate structure damage monitoring method Download PDFInfo
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Abstract
The invention discloses a composite material plate structure damage monitoring method, and belongs to the technical field of composite material plate structure damage monitoring. The method is designed for solving the problems of low efficiency, low precision, and no simultaneous identification of many damages of present methods. The composite material plate structure damage monitoring method is a damage monitoring method based on a piezoelectric element and a Lamb wave. The method comprises the following steps: predetermining the damage position of a composite material plate structure to be monitored by using a damage factor technology, and imaging the area which is predetermined to be damaged in order to determine the accurate position of the damage. The composite material plate structure damage monitoring method can save a lot of monitoring time, improves the monitoring efficiency, can realize multi-damage positioning, and enhances the determination accuracy of the number and the position of the damages.
Description
Technical field
The present invention relates to a kind of damage monitoring method of composite panel structure.
Background technology
Composite panel is because the advantages of its specific strength is high, specific stiffness is big, anti-fatigue performance is good and material property can design
And extensively apply in the engineering fields such as Aeronautics and Astronautics, automobile.But, relatively low interlaminar shear strength and vertical plane direction
Tensile strength make to be susceptible to MDI vector in composite panel.Delamination can make compressive strength and rigidity be remarkably decreased,
Bearing capacity is led to reduce.
In order to be identified to the various damages in composite panel, position to predict structural life-time, to carry out structural maintenance,
The methods such as conventionally used percussion, ultrasonic, X-ray, current vortex ray, potential measurement and stress field have and are difficult to take
Real time on-line monitoring under labour environment, the problems such as the professional standing and experience of testing staff is had high demands.And it is based on embedment or viscous
Be attached to surface piezoelectric element Active Lamb Wave method then have the advantages that sensitive to Small loss and can in real time, on-line monitoring.
Existing based on the hardened structure damage monitoring method of piezoelectric element and Lamb wave be extract ripple reach the time carry out damaging fixed
Position, is easily subject to environment noise, Acquisition Error, labyrinth form（Such as hole or reinforcement）, and material properties etc. shadow
Ring it is impossible to accurate extract the time of advent damaging scattered wave bag.It is additionally, since the impact of border reflection, occur leaning on when damaging
When proximal border position, border reflected signal makes scattered wave bag cannot carry the time of advent with the aliasing damaging reflected signal
Take.In addition, existing damage monitoring method and imaging method shorter mention to identification while multiple damage and position, and
The calculated for pixel values of each point of whole monitored area seriously reduces the efficiency of damage monitoring.
Content of the invention
It is an object of the invention to proposing a kind of damage monitoring method of composite panel structure in hgher efficiency.
Another object of the present invention is to propose a kind of composite panel structure more accurate to damage quantity judgement
Damage monitoring method.
Another object of the present invention is to propose a kind of damage prison of the more accurate composite panel structure of damage reason location
Survey method.
For reaching this purpose, the present invention employs the following technical solutions：
A kind of damage monitoring method of composite panel structure, methods described is the damage based on piezoelectric element and Lamb wave
Monitoring method, methods described carries out the pre- judgement of damage position using damage factor method to composite panel structure to be monitored, so
The region that afterwards anticipation be there are with damage is imaged to determine the accurate location of damage.
Particularly, the pre- judgement carrying out damage position to composite panel structure to be monitored comprises the steps：
Step S1, gather and store healthy Lamb wave signal H (t) of composite panel structure to be monitored；
Step S2, N number of subregion Q to be monitored will be divided on composite panel structure to be monitored, N is more than or equal to 1
Positive integer；I is entered as 1；
Monitoring Lamb wave signal D (t) of step S3, Real-time Collection composite panel to be monitored structure；
Step S4, judge whether there is damage in i-th subregion Qi using damage factor method, not damaged then goes to step
S5；Having damage then to record i-th subregion Qi is the subregion Qs containing damage, goes to step S5；
Step S5, judge that whether i is more than or equal to N, be to go to step S6；Otherwise i is entered as i+1, goes to step S4；
Step S6, judge that each contains the damage damaging in subregion Qs and whether is located on the border in region successively, be to sentence
Breaking, whether it forms fusion subregion with adjacent subarea domain；Otherwise it is judged to independent subregion；
Step S7, end.
Particularly, under judging in step S6 that the subregion Qs containing damage includes as the method merging subregion or independent subregion
State step：
Step S61, compare containing damaging the position that in subregion Qs, through wave band damage factor maximum occurs, when described
When big value Max-Qs occurs in the excitation/sensing passage of diagonal D, judge that the described subregion Qs containing damage, as independent subregion, turns
To step S65；When described maximum Max-Qs occurs in the excitation/sensing passage of boundary B, go to step S62；
Step S62, judge to occur described maximum Max-Qs boundary B be whether composite panel structure to be monitored side
Boundary, is then to judge that the described subregion Qs containing damage, as independent subregion, goes to step S65；Otherwise go to step S63；
Step S63, check and have in the subregion Qx of described boundary B jointly and whether contain containing damaging subregion Qs with described
Damage, be to go to step S64；Otherwise judge that the described subregion Qs containing damage, as independent subregion, goes to step S65；
In step S64, judgement subregion Qx, whether through wave band damage factor maximum Max-Qx occurs in son containing damage
At the common boundary of region Qs and subregion Qx, it is then to judge the subregion Qs and subregion Qx containing damage as fusion subregion；No
Then judge that the described subregion Qs containing damage, as independent subregion, goes to step S65；
Step S65, end.
Particularly, include merging subregion and including the quantity of independent subregion of damage and for be monitored of damage
Damage sum in composite panel structure.
Particularly, in step s 4, set threshold value Y judging to damage, when damage factor numerical value >=threshold value Y, judge i-th
There is damage in sub-regions Qi；When damage factor numerical value ＜ threshold value Y, judge not damaged in i-th subregion Qi.
Particularly, described damage factor numerical value is the damage of all through wave bands of excitation/sensing passage in every sub-regions
Factor average.
Particularly, it is imaged using the region that fusion of imaging method cumulative during difference there are damage to anticipation.
Particularly, anticipation be there are damage region be imaged after using weighted mean method determine damage accurate position
Put.
The damage monitoring method of composite panel structure of the present invention be anticipation be there are damage region be imaged with
Determine the accurate location damaging, the substantial amounts of time can be saved with respect to the method for direct imaging, improve efficiency and accuracy.
For occurring the borderline damage in region to determine whether, judge whether it is formed with adjacent subarea domain and merge sub-district
Domain is so that the judgement damaging quantity is more accurate.Anticipation be there are damage region be imaged after using weighted mean method
Determine the accurate location damaging, eliminate the interference each other of poly-injury scattered signal and spread speed anisotropy pair
The interference of positioning, accuracy is higher.
Brief description
Fig. 1 is that the damage monitoring method that the preferred embodiment of the present invention one provides implements view；
Fig. 2 is excitation/sensing passage schematic diagram in the preferred embodiment of the present invention one；
Fig. 3 is the pre- decision flow chart of damage position that the preferred embodiment of the present invention one provides；
Fig. 4 is the preferred embodiment of the present invention one waveform input signal figure；
Fig. 5 is the oscillogram of the health signal of a pair of corner channel of the preferred embodiment of the present invention；
Fig. 6 is the oscillogram of the monitoring signals of diagonal channels shown in Fig. 5；
Fig. 7 is the oscillogram of the difference signal obtaining after health signal normalization shown in monitoring signals shown in Fig. 6 and Fig. 5；
Fig. 8 is the signal wave bag schematic diagram of difference signal shown in Fig. 7；
Fig. 9 be the preferred embodiment of the present invention one poor when cumulative fusion of imaging method schematic diagram；
Figure 10 is the imaging results schematic diagram of the preferred embodiment of the present invention one；
Figure 11 is the damage position and actual damage position versus schematic diagram that imaging results according to Figure 10 judge；
Figure 12 is the imaging results schematic diagram of the preferred embodiment of the present invention two；
Figure 13 is the damage position and actual damage position versus schematic diagram that imaging results according to Figure 12 judge.
In figure is labeled as：
1st, the first subregion；2nd, the second subregion；3rd, the 3rd subregion；4th, the 4th subregion；11st, monitoring device table top；
12nd, composite panel；13rd, piezoelectric element.
Specific embodiment
Further illustrate technical scheme below in conjunction with the accompanying drawings and by specific embodiment.
Preferred embodiment one：
This preferred embodiment provides a kind of damage monitoring side of the composite panel structure based on piezoelectric element and Lamb wave
Method.The method carries out the pre- judgement of damage position using damage factor method to composite panel structure to be monitored, then to anticipation
The region that there are damage is imaged to determine the accurate location of damage.
Because need not be imaged to not damaged region, save the substantial amounts of monitoring time, in hgher efficiency, accuracy is more
High.
As shown in figure 1, the method is that composite panel 12 to be monitored is fixed on monitoring device table top 11, compound
Multiple piezoelectric elements 13 are fixed on plate of material 12.Piezoelectric element 13 can be arranged in variously-shaped it is preferred that by four piezoelectricity units
Part 13 surrounds rectangular area.When damaging more in larger, the to be monitored area of composite panel 12 area, multiple piezoelectricity can be used
Element 13 surrounds many sub-regions.In this preferred embodiment, mark off four rectangle to be monitored using nine piezoelectric elements 13
Region, is the first subregion 1, the second subregion 2, the 3rd subregion 3 and the 4th subregion 4 respectively.
As shown in Fig. 2 in every sub-regions, four piezoelectric element 13 combination of two form six excitation/sensing passages,
Specifically, including four edges circle B excitation/sensing passage and two diagonal D excitation/sensing passages.Monitoring signals pass through this six
Excitation/sensing passage carrys out transmission-reception, to judge to damage the presence or absence of A and accurate location.
As shown in figure 3, the pre- judgement carrying out damage position to composite panel structure to be monitored comprises the steps：
Step S1, monitoring composite panel structure dispatch from the factory or come into operation at the beginning of, gather and store its healthy Lamb
Ripple signal H (t), for subsequent calculations damage factor and/or damage imaging.
Step S2, four subregion Q to be monitored will be divided on composite panel structure to be monitored；I is entered as 1.
Monitoring Lamb wave signal D (t) of step S3, Real-time Collection composite panel to be monitored structure.Input signal is to adjust
Make five crest sinusoidal signals, its waveform is as shown in Figure 4.Fig. 5 to Fig. 8 is respectively the health signal of diagonal channels in this subregion
The oscillogram of difference signal that obtains after oscillogram, the oscillogram of monitoring signals, monitoring signals and health signal normalization and poor
The signal envelope curve of signal.
Step S4, judge whether there is damage A in i-th subregion Qi using damage factor method, not damaged then goes to step
S5；Having damage A then to record i-th subregion Qi is the subregion Qs containing damage, goes to step S5.
Specifically, calculate damage factor DI (H, D) using following formula：
Wherein, t1Represent the initial time that direct wave reaches, t2Represent the end time that direct wave reaches, H (t) represents strong
Health Lamb wave signal, D (t) represents monitoring Lamb wave signal.
When not damaging in damaging away from excitation/sensing passage or structure, monitoring signals are essentially identical with health signal,
Calculated damage factor value is close to 0；If damage occurred exactly on excitation/sensing passage or when near it, calculate
To damage factor value can level off to 1.
According to this principle, set threshold value Y judging to damage, such as Y=0.5.When six excitation/biographies in every sub-regions
During damage factor average >=threshold value Y of the through wave band of sense passage, judge there is damage in this subregion Qi；When six in every sub-regions
During damage factor average ＜ threshold value Y of the through wave band of bar excitation/sensing passage, judge not damaged in this subregion Qi.
Step S5, judge that whether i is more than or equal to 4, be to go to step S6；Otherwise i is entered as i+1, goes to step S4.
Step S6, judge that each contains the damages A damaging in subregion Qs whether in the boundary B in region successively, be then
Judge whether it is formed with adjacent subarea domain and merge subregion；Otherwise it is judged to independent subregion.
Specifically determination methods are：
The position that in step S61, comparison subregion Qs containing damage, through wave band damage factor maximum occurs, when this maximum
When value Max-Qs occurs in the excitation/sensing passage of diagonal D, judge that this contains damage subregion Qs as independent subregion, go to step
Rapid S65；When this maximum Max-Qs occurs in the excitation/sensing passage of boundary B, go to step S62.
Step S62, judge that whether boundary B maximum Max-Qs is the border of composite panel structure to be monitored,
It is to judge that this contains damage subregion Qs as independent subregion, go to step S65；Otherwise go to step S63.
Step S63, check with this contain damage subregion Qs have in the subregion Qx of common boundary B whether contain damage,
It is to go to step S64；Otherwise judge that this contains damage subregion Qs as independent subregion, go to step S65.
In step S64, judgement subregion Qx, whether through wave band damage factor maximum Max-Qx occurs in son containing damage
At the common boundary of region Qs and subregion Qx, it is then to judge the subregion Qs and subregion Qx containing damage as fusion subregion；No
Then judge that this contains damage subregion Qs as independent subregion, go to step S65；Include the fusion subregion of damage and include
The quantity of independent subregion damaged and for the damage sum in composite panel structure to be monitored.
Step S65, judge to terminate as the method merging subregion or independent subregion containing damaging subregion Qs.
Step S7, the pre- judgement carrying out damage position to composite panel structure to be monitored terminate.
After pre- judgement terminates, the region that anticipation be there are with damage is carried out using fusion of imaging method cumulative during difference to pre-
Sentence and there are the region of damage and be imaged, and determine the accurate location damaging after imaging using weighted mean method.
Comprise the following steps that：
The first step：The damage position of multiple hypothesis is set in each region to be imaged, is calculated every health signal
The expectation t time of advent of the scattered Lamb waves signal of damage position is assumed at each in passageij(x,y).
As shown in figure 9, picture point W is the damage position assumed, the coordinate of this point is (x, y).Lamb wave damages scattering letter
Number from coordinate be (xi,yi) piezoelectric element（Exciting element）Pi reaches piezoelectric element through picture point W（Sensing element）The expectation of Pj
The time of advent tij(x, y) is：
Wherein, the group velocity that c propagates for Lamb wave, can be obtained by measurement；toffFor the pumping signal moment.
Second step：Calculate the envelope E of the ripple bag of difference signal of monitoring signals and health signalij=env(H-D).Wherein, env
For asking for the envelope of difference signal ripple bag, this value can be calculated.
The envelope of the difference signal ripple bag on each excitation/sensing passage is all according to the first step calculated time of advent
tijWhen (x, y) is differed from, then the width of the ripple bag envelope when correspondence of the difference signal of all passages differs from the monitored subregion that adds up
Value, obtains imaging energy value E (x, y) of each locus:
By superposition during the signal difference of plurality of passages, you can obtain merging damages energy in monitored sub-district domain space
Distribution.The amplitude of scattered signal due in ripple bag envelope is bigger, and energy is bigger, represents and damages the probability occurring herein relatively
Height, can judge the position damaged accordingly.
3rd step：Repeat the first step and second step, all hypothesis damage positions in imaging region are treated with the spacing setting
Calculated, obtained the overall energy value distribution situation of this monitoring subregion.Whole energy values can be corresponded to into different face
Color, as intuitively image, as shown in Figure 10.In Fig. 10, each sub-regions are divided into multiple different energy by curve
Scope, the numeral of in figure has indicated the energy value in the range of this respectively.
Number and the position of damage directly can be judged according to imaging contexts, i.e. extract the maximum point of energy value and judge
For damage position.In view of poly-injury scattered signal there is interference each other and the anisotropy of spread speed is deposited to positioning
In interference, more accurate damage position decision method is that imaging is weighted averagely.
Select and damage the subregion interior energy value occurring more than maximum energy value 70% in this region（Can be as the case may be
Set percent value）Position, using its corresponding energy value as weights, its position as variable, judge to damage according to following formula
Position P：
Wherein, K is more than the number of the point of maximum energy value 70%, E for energy valueiIt is more than maximum energy value 70% for energy value
Point energy value, PiIt is more than the coordinate of the point of maximum energy value 70% for energy value.
As shown in figure 11, the damage position that triangular representation judges, cross（×）Represent damage position.To the quantity damaged
And the judgement of position is all very accurate, speed is also fast a lot of than prior art.
Preferred embodiment two：
This preferred embodiment provides a kind of damage monitoring side of the composite panel structure based on piezoelectric element and Lamb wave
Method.The method carries out the pre- judgement of damage position using damage factor method to composite panel structure to be monitored, then to anticipation
The region that there are damage is imaged to determine the accurate location of damage.
The concrete steps of the method do not limit, and the region enabling to there are damage just for anticipation is imaged to determine damage
The accurate location of wound；Selected damage factor and imaging method are not limited to example given in preferred embodiment one,
Other damage factors and imaging method also may be used；This subregion can not be judged when the subregion comprising damage is less whether
Formed with adjacent subarea domain and merge subregion.
Figure 12 is the image of this preferred embodiment, and four sub-regions are divided into multiple different energy ranges by curve,
The numeral of in figure has indicated the energy value in the range of this respectively.Figure 13 is the result of determination being obtained according to Figure 12, triangle table
Show the damage position of judgement, cross（×）Represent that damage position, the quantity of damage and the judgement of position are all very accurate.
Claims (6)
1. a kind of damage monitoring method of composite panel structure, methods described is the damage prison based on piezoelectric element and Lamb wave
Survey method is it is characterised in that methods described carries out damage position using damage factor method to composite panel structure to be monitored
Pre- judgement, the region that then anticipation be there are with damage is imaged to determine the accurate location of damage；
The pre- judgement carrying out damage position to composite panel structure to be monitored comprises the steps：
Step S1, gather and store healthy Lamb wave signal H (t) of composite panel structure to be monitored；
Step S2, N number of subregion Q to be monitored will be divided on composite panel structure to be monitored, N more than or equal to 1 is just
Integer；I is entered as 1；
Monitoring Lamb wave signal D (t) of step S3, Real-time Collection composite panel to be monitored structure；
Step S4, judge whether there is damage in i-th subregion Qi using damage factor method, not damaged then goes to step S5；Have
Damaging and then recording i-th subregion Qi is the subregion Qs containing damage, goes to step S5；
Step S5, judge that whether i is more than or equal to N, be to go to step S6；Otherwise i is entered as i+1, goes to step S4；
Step S6, judge that each contains the damage damaging in subregion Qs and whether is located on the border in region successively, be to judge it
Whether formed with adjacent subarea domain and merge subregion；Otherwise it is judged to independent subregion；
Step S7, end；
Wherein, judge in step S6 that the subregion Qs containing damage includes following steps as the method merging subregion or independent subregion
Suddenly：
The position that in step S61, comparison subregion Qs containing damage, through wave band damage factor maximum occurs, when described maximum
When Max-Qs occurs in the excitation/sensing passage of diagonal D, judge that the described subregion Qs containing damage, as independent subregion, goes to step
Rapid S65；When described maximum Max-Qs occurs in the excitation/sensing passage of boundary B, go to step S62；
Step S62, judge to occur described maximum Max-Qs boundary B be whether composite panel structure to be monitored border,
It is then to judge that the described subregion Qs containing damage, as independent subregion, goes to step S65；Otherwise go to step S63；
Step S63, check and have in the subregion Qx of described boundary B jointly whether containing damaging containing damaging subregion Qs with described
Wound, is to go to step S64；Otherwise judge that the described subregion Qs containing damage, as independent subregion, goes to step S65；
In step S64, judgement subregion Qx, whether through wave band damage factor maximum Max-Qx occurs in the subregion containing damage
At the common boundary of Qs and subregion Qx, it is then to judge the subregion Qs and subregion Qx containing damage as fusion subregion；Otherwise sentence
The fixed described subregion Qs containing damage is independent subregion, goes to step S65；
Step S65, end.
2. the damage monitoring method of composite panel structure according to claim 1 is it is characterised in that include damage
Merge subregion and include the quantity of independent subregion of damage and for the damage sum in composite panel structure to be monitored.
3. the damage monitoring method of composite panel structure according to claim 1 is it is characterised in that in step s 4,
Set threshold value Y judging to damage, when damage factor numerical value >=threshold value Y, judge there is damage in i-th subregion Qi；Work as damage
During factor value ＜ threshold value Y, judge not damaged in i-th subregion Qi.
4. the damage monitoring method of composite panel structure according to claim 3 is it is characterised in that described damage factor
Numerical value is the damage factor average of all through wave bands of excitation/sensing passage in every sub-regions.
5. the damage monitoring method of composite panel structure according to claim 1 is it is characterised in that use cumulative during difference
The region that fusion of imaging method there are damage to anticipation is imaged.
6. the damage monitoring method of composite panel structure according to claim 1 is it is characterised in that there are to anticipation
The region damaged determines, using weighted mean method, the accurate location damaging after being imaged.
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| CN105806943B (en) * | 2016-03-09 | 2018-10-19 | 西安交通大学 | Composite material beam construction damage positioning method and system based on discrete wavelet |
| CN107014668A (en) * | 2016-04-22 | 2017-08-04 | 北京航空航天大学 | A kind of fatigue crack integrated monitoring based on piezoelectricity and smart coat sensor |
| CN107870205A (en) * | 2016-09-22 | 2018-04-03 | 淮阴师范学院 | A kind of damage of composite materials detection detection method based on wavelet analysis |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7925455B2 (en) * | 2008-01-24 | 2011-04-12 | The Boeing Company | Method and system for the determination of damage location |
| CN102043016A (en) * | 2010-11-05 | 2011-05-04 | 上海交通大学 | Lamb wave-based autonomous damage identification imaging method |
| CN102353718A (en) * | 2011-07-11 | 2012-02-15 | 南京航空航天大学 | Lamb wave damage probability imaging method for damage monitoring of composite plate structure |
| CN103217478A (en) * | 2013-04-16 | 2013-07-24 | 南京航空航天大学 | Reference-free damage identification method for composite material plate-shaped structure |
-
2014
- 2014-04-21 CN CN201410158828.XA patent/CN104181230B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7925455B2 (en) * | 2008-01-24 | 2011-04-12 | The Boeing Company | Method and system for the determination of damage location |
| CN102043016A (en) * | 2010-11-05 | 2011-05-04 | 上海交通大学 | Lamb wave-based autonomous damage identification imaging method |
| CN102353718A (en) * | 2011-07-11 | 2012-02-15 | 南京航空航天大学 | Lamb wave damage probability imaging method for damage monitoring of composite plate structure |
| CN103217478A (en) * | 2013-04-16 | 2013-07-24 | 南京航空航天大学 | Reference-free damage identification method for composite material plate-shaped structure |
Non-Patent Citations (2)
| Title |
|---|
| 630. Combination of time reversal process and ultrasonic tomography approaches for baseline-free damage diagnosis;Yongming Feng等;《Vibroengineering.Journal of Vibroengineering》;20110630;第13卷(第2期);253-268页 * |
| Probability of the presence of damage estimated from an active sensor network;Dong Wang 等;《Composites Science and Technology》;20081114;2054-2063页 * |
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