# Intelligent Identification of Structural Damage Based on the Curvature Mode and Wavelet Analysis Theory

Authors: Longsheng Bao; Yue Cao; Xiaowei Zhang
Journal: Advances in Civil Engineering
 (2021)

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## Abstract

Structural health monitoring is extensively used in new and old structures. During the process of monitoring, a large amount of data is generated. The selection of the appropriate methodology for the analysis of these data constitutes a major problem for maintenance personnel. Therefore, the purpose of this study is to programme data according to the curvature mode and wavelet transform theory to achieve automatic identification of structural damage and explore its applicability. First, the damage model is established with finite element software, and the applicability of the theory is verified by analysing the wavelet coefficients before and after structural damage. Thereafter, a programme is written to achieve the automatic output of the structural damage location based on the finite element results and basic theory. Data fitting is then performed to estimate the degree of structural damage. To evaluate the effects of the practical application of the programme, experimental verification is conducted. The experimental results demonstrate that the programme can automatically output the damage location and avoid the occurrence of calculation errors.


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## Body

## 1. Introduction

Multiple damage areas emerge during the service period of a structure. These areas may be caused by improper maintenance or environmental influences. The occurrence of damage can reduce the local stiffness of the structure directly, and a considerable part of the damage is neither visible to the naked eye nor to visualisation instruments. If the problem is not detected, some hidden dangers to the structure will emerge over time that may potentially constitute a threat to people’s properties and lives. Therefore, increasing attention has been paid to structural safety. Additionally, damage identification technology has developed rapidly in recent years. Some examples include the safety assessment of structures using techniques that range from traditional local nondestructive testing to global health monitoring [1, 2], as well as the development of techniques that span local ultrasonic testing to real-time acquisitions of the dynamic characteristic parameters with prearranged sensors. To achieve an overall damage assessment, many large bridges have been equipped with corresponding sensors for long-term health monitoring in recent years [3, 4]. In general, damage identification can be classified into theoretical research, laboratory verification, and structural health monitoring [5–10]. Most of the damage identification of actual structures relies on structural health monitoring. Whether the damage can be accurately identified depends on the correct analysis of the dynamic characteristic signals [11, 12]. Modern finite element software and the accuracy of various sensors are constantly improving, and signal processing technology is changing continually. Damage identification technology for damage responses based on structural health monitoring has gradually become a research focus at home and abroad [13, 14].At present, the most popular damage identification methods include experimental modal analysis methods that combine system identification, vibration theory, vibration testing technology, signal acquisition and analysis, and other interdisciplinary techniques [15]. Typically, the dynamic characteristic parameters pertaining to structural damage include the natural frequency and the displacement and curvature modes [16]. A large amount of data has proved that the curvature mode is more sensitive than damage indicators, such as the natural frequency [17, 18]. Additionally, the curvature mode is relatively easy to obtain and has good sensitivity; hence, it is the most cost-effective damage index [19, 20]. Tomaszewska [21] studied the relationship between the change in curvature mode and damage based on calculations. Dawari and Vesmawala and Dawari [22] performed similar calculations and obtained the curvature mode based on the difference operation of the displacement modes. Based on past and ongoing in-depth research studies, scholars have found that the perceived curvature mode has a poor recognition effect on the damage at the edges of the structure and when the structure has minor damage. Accordingly, it is necessary to develop a method to solve these problems.In view of its “adaptability” and “mathematical characteristic”’ [23], wavelet analysis has gradually revealed its advantages in signal processing technology. Wavelet transform relies on the wavelet’s telescopic translation. This transform possesses several advantages and overcomes the shortcomings of the Fourier transform. It is an excellent mathematical tool for analysing non-steady-state signals. It has been extensively applied to various structures for damage identification [24–28]. Hou et al. used the Daubechies wavelet to transform the acceleration response of the structural dynamic model with wavelet transform and identified the loss position according to the sudden signal point changes [29, 30]. Pereira et al. studied a continuous wavelet transform (CWT) and applied it to the fault identification of gears connected to motors and generators to identify accurately the tooth on which the fault occurred [31].Herein, structural damage identification technology is studied based on curvature mode normalization and wavelet transform theory. It is proved that the curvature mode data can be used as structural damage identification index data after the wavelet transform. The corresponding structural damage identification program is programmed in MATLAB and verified by finite element analysis and experimental measurements. Compared with the manual analysis and calculation, the program can automatically output the damage location and extent and yields a better recognition effect. It can also replace manual data analysis and processing to avoid the occurrence of calculation errors and other situations.


## 2. Basic Theory and Assumptions

### 2.1. Curvature Mode Theory

As a modal parameter, the curvature mode is a unique inherent deformation mode of the bending vibration of a bending structure. Because the curvature mode is the deformation mode of the neutral surface of the structure, it is relatively sensitive to local changes in the structure and can reflect changes in its local characteristics. Therefore, this theory is introduced into the damage identification of bending members.When the beam is bent, the curvature of the neutral axis is calculated as follows:(1)ρ=MEI,where E is the elastic modulus of the material, I is the moment of inertia of the section, and M is the bending moment.It can be inferred from equation (1) that the curvature of a certain point on the beam is inversely proportional to the corresponding structural stiffness; that is, the change in the stiffness of the structure can be reflected by the curvature [32].Considering that the general structure service period is in the range of linear elasticity, from the point-of-view of material mechanics, the curvature of the component is(2)ρ=δ″1+δ′23/2,where δ is the displacement. In the case of small deformations, equation (2) can be transformed into(3)ρ=δ″.After introducing the definition of the curvature mode,ρ is the second derivative of δ, ρ is the curvature mode, and δ is the displacement formation.In finite element analysis, the vibration modes obtained via modal analysis are generally displacement matrices, and the curvature modes can be easily obtained by calculating their variation laws using the central difference method.In the actual structural health monitoring process, structural vibration conditions can be collected using preset global positioning system sensors and displacement sensors in cooperation with corresponding acquisition systems [33]. The maximum number of sensors should be deployed. The overall displacement matrix, δ, of the structure can be obtained via calculation based on the displacement, δxi, of the measurement point on the bridge at a specific moment. The relevant expression is as follows [34]:(4)δ=δx1δx2δx3⋯δxi⋯δxn−1δxn,where i is the number of sensors.When the actual sensor arrangement is sparse, the spline curve can be used for interpolation.The curvature mode,ρxi, can be obtained using the central difference method of the displacement matrix as follows:(5)ρxi=δxi−1−2δxi+δxi+1li−1,i,li,i+1,where li−1,i is the distance from sensors i−1 to i and li,i+1 is the distance from sensors i to i+1.The structural damage curvature mode can directly reflect the stiffness change during structural damage. If the damage to the structure is very small, the curvature mode can be normalised using the maximum normalisation method. Combined with the wavelet transform theory, the damage location and degree of damage of the structure become more prominent.


### 2.2. Wavelet Transform Theory

Once the structure is damaged, the local stiffness will decrease accordingly. Some characteristic parameters of the structure (such as displacement, modal formation, and modal curvature) will irregularly change or abruptly change following the damage. This sudden change contains a specific damage signal. These or other sudden changes usually correspond to the modulus maxima or zero-crossing points of the wavelet transform coefficients in the wavelet variation domain, and the degree of signal singularity corresponds to the change rule of the maximum scale of the wavelet transform coefficients. Chang and Chen [35] discussed the relationship between the wavelet transform modulus maximum (or zero-crossing) point and the signal point.Supposeψx∈L2RL2R represents a square-integrable real number space, that is, a signal space with limited capabilities, and its Fourier transform is ψ^ω.When functionψ^ω satisfies the following admissibility condition,(6)Cψ=∫−∞+∞ψ^ω2ωdω<∞,then ψx is called a wavelet basis function, and the integral transformation can be defined as follows:(7)Wψfa,b=a−1/2∫fxψx−ba¯dx,fx∈L2R.In other words, the wavelet change ofWψfa,b is based on ψx, which is obtained after the expansion and contraction of scale a and the translation of b.The aforementioned integral transformation tofx is an integral CWT based on ψx, wherein a is a scale factor that represents the expansion and contraction with frequency, and b is a time translation factor.In simple terms, the process of CWT involves the calculation of the wavelet coefficients by getting as close as possible to the known signals based on the selected wavelet bases. The larger the obtained wavelet coefficient is, the greater the similarity between the wavelet base and the known signal. The signal can also be reconstructed according to the selected wavelet base and the wavelet coefficient.Based on the above theory, the process of structural damage identification in this study is shown in Figure1.Figure 1
Flow chart of damage identification.


## 2.1. Curvature Mode Theory

As a modal parameter, the curvature mode is a unique inherent deformation mode of the bending vibration of a bending structure. Because the curvature mode is the deformation mode of the neutral surface of the structure, it is relatively sensitive to local changes in the structure and can reflect changes in its local characteristics. Therefore, this theory is introduced into the damage identification of bending members.When the beam is bent, the curvature of the neutral axis is calculated as follows:(1)ρ=MEI,where E is the elastic modulus of the material, I is the moment of inertia of the section, and M is the bending moment.It can be inferred from equation (1) that the curvature of a certain point on the beam is inversely proportional to the corresponding structural stiffness; that is, the change in the stiffness of the structure can be reflected by the curvature [32].Considering that the general structure service period is in the range of linear elasticity, from the point-of-view of material mechanics, the curvature of the component is(2)ρ=δ″1+δ′23/2,where δ is the displacement. In the case of small deformations, equation (2) can be transformed into(3)ρ=δ″.After introducing the definition of the curvature mode,ρ is the second derivative of δ, ρ is the curvature mode, and δ is the displacement formation.In finite element analysis, the vibration modes obtained via modal analysis are generally displacement matrices, and the curvature modes can be easily obtained by calculating their variation laws using the central difference method.In the actual structural health monitoring process, structural vibration conditions can be collected using preset global positioning system sensors and displacement sensors in cooperation with corresponding acquisition systems [33]. The maximum number of sensors should be deployed. The overall displacement matrix, δ, of the structure can be obtained via calculation based on the displacement, δxi, of the measurement point on the bridge at a specific moment. The relevant expression is as follows [34]:(4)δ=δx1δx2δx3⋯δxi⋯δxn−1δxn,where i is the number of sensors.When the actual sensor arrangement is sparse, the spline curve can be used for interpolation.The curvature mode,ρxi, can be obtained using the central difference method of the displacement matrix as follows:(5)ρxi=δxi−1−2δxi+δxi+1li−1,i,li,i+1,where li−1,i is the distance from sensors i−1 to i and li,i+1 is the distance from sensors i to i+1.The structural damage curvature mode can directly reflect the stiffness change during structural damage. If the damage to the structure is very small, the curvature mode can be normalised using the maximum normalisation method. Combined with the wavelet transform theory, the damage location and degree of damage of the structure become more prominent.


## 2.2. Wavelet Transform Theory

Once the structure is damaged, the local stiffness will decrease accordingly. Some characteristic parameters of the structure (such as displacement, modal formation, and modal curvature) will irregularly change or abruptly change following the damage. This sudden change contains a specific damage signal. These or other sudden changes usually correspond to the modulus maxima or zero-crossing points of the wavelet transform coefficients in the wavelet variation domain, and the degree of signal singularity corresponds to the change rule of the maximum scale of the wavelet transform coefficients. Chang and Chen [35] discussed the relationship between the wavelet transform modulus maximum (or zero-crossing) point and the signal point.Supposeψx∈L2RL2R represents a square-integrable real number space, that is, a signal space with limited capabilities, and its Fourier transform is ψ^ω.When functionψ^ω satisfies the following admissibility condition,(6)Cψ=∫−∞+∞ψ^ω2ωdω<∞,then ψx is called a wavelet basis function, and the integral transformation can be defined as follows:(7)Wψfa,b=a−1/2∫fxψx−ba¯dx,fx∈L2R.In other words, the wavelet change ofWψfa,b is based on ψx, which is obtained after the expansion and contraction of scale a and the translation of b.The aforementioned integral transformation tofx is an integral CWT based on ψx, wherein a is a scale factor that represents the expansion and contraction with frequency, and b is a time translation factor.In simple terms, the process of CWT involves the calculation of the wavelet coefficients by getting as close as possible to the known signals based on the selected wavelet bases. The larger the obtained wavelet coefficient is, the greater the similarity between the wavelet base and the known signal. The signal can also be reconstructed according to the selected wavelet base and the wavelet coefficient.Based on the above theory, the process of structural damage identification in this study is shown in Figure1.Figure 1
Flow chart of damage identification.


## 3. Results

### 3.1. Simulation Results and Wavelet Analysis

To establish a finite element analysis model for simply supported T-beams, the following parameters are set: beam lengthL = 20 m, elastic modulus E = 32500 MPa, density γ = 2549 kg/m³, moment of inertia I = 1.62 × 10−1 m4, and Poisson’s ratio υ = 0.2. The damage locations are distributed according to the working conditions and distributed at different sections for simulation. The degree of damage was simulated according to the damage and the stiffness of the section (estimated as the product of the modulus of elasticity and the moment of inertia of the section). In the simulation, the beam is first divided into 40 sections (as shown in Figure 2), the length of each section is 0.5 m, and the type of element is the beam element in the software Midas civil (2019). The constraint conditions are left-hinged and right sliding supports.Figure 2
Structural layout of simply supported T-beam.First, the structure is analysed to obtain the vibration modes of the damage-free model and the damage model for each node. Second, according to equation (5), the curvature mode is obtained and then normalised. Thereafter, the Daubechies 2 wavelet transform is selected in MATLAB (R2016b, MathWorks, Natick, MA, USA), and the damage-free model and wavelet coefficients are obtained. Finally, the above process is coded in MATLAB. In the general practical structural dynamic test process, low-frequency signals are easily collected accurately, and the high-frequency signal of the structure is not easily obtained accurately. Thus, the numerical simulation test used in this study uses the first-order mode of the structure in the analysis process. The structure’s diagram is shown in Figure 2.


### 3.2. Damage Location Identification

To evaluate the applicability of this method and procedure in structural damage identification, three conditions were set up in this study for analyses. The specific working conditions are listed in Table1.Table 1
List of working conditions used in the study.
Working conditionDamage location (m)Section numberDegree of damage (%)Working condition 14.2595, 6, 10, 15, 20Working condition 24.25, 9.25, 16.759, 19, 345, 6, 10, 15, 20Working condition 34.25, 9.25, 16.759, 19, 345, 6, 10After calculation, the frequency of the structure was obtained at different working conditions, which are presented in Table2.Table 2
Frequency calculation values of each working condition (cycles/s).
Degree of damage (%)Working conditionWorking condition 1Working condition 2Working condition 356.5607916.5504046.54620566.5600716.547485106.5570336.535200156.5528376.518331——206.5481256.499508——The set of damage levels in working condition 1 are 5%, 6%, 10%, 15%, and 20%. The damage location was set in section 9. The output single-damage wavelet coefficient difference diagrams based on the programme calculation are presented in Figures3–7.Figure 3
Wavelet coefficient difference graph for 5% damage in section 9.Figure 4
Wavelet coefficient difference graph for 6% damage in section 9.Figure 5
Wavelet coefficient difference graph for 10% damage in section 9.Figure 6
Wavelet coefficient difference graph for 15% damage in section 9.Figure 7
Wavelet coefficient difference graph for 20% damage in section 9.Figures3–7 show that the position of the output damage is consistent with the preset damage position. Moreover, waveform analysis reveals that the waveform amplitude associated with the damaged area will be significantly increased as the degree of damage increases, and the amplitude of the undamaged position waveform is close to zero.Working condition 2 constitutes the set of multidamage conditions with damage locations in sections 9, 19, and 34, and the damage degree is the same at the three locations. The five damage levels of 5%, 6%, 10%, 15%, and 20% are analysed. The output multidamage wavelet coefficient difference diagrams obtained through the programme calculation are presented in Figures8–12.Figure 8
Wavelet coefficient difference for 5% damage in sections 9, 19, and 34.Figure 9
Wavelet coefficient difference for 6% damage in sections 9, 19, and 34.Figure 10
Wavelet coefficient difference for 10% damage in sections 9, 19, and 34.Figure 11
Wavelet coefficient difference for 15% damage in sections 9, 19, and 34.Figure 12
Wavelet coefficient difference for 20% damage in sections 9, 19, and 34.It can be observed (from Figures8–12) that when multiple points of damage of the same degree occur in the structure, an obvious waveform protrusion will occur at each damage level, and the output damage location will be consistent with the preset damage location. The extent of protrusion of the waveform will also increase as the degree of damage increases.Working condition 3 is also a multidamage condition. It is a condition in which there are multiple points of damage of different degrees to the structure. In particular, 5% damage occurs in section 9, 6% damage occurs in section 19, and 10% damage occurs in section 34. The output multidamage wavelet coefficient difference diagrams obtained after programme calculation is presented in Figure13.Figure 13
Wavelet coefficient differences of 5%, 6%, and 10% for damage in sections 9, 19, and 34, respectively.As shown in Figure13, when several degrees of structural damage occurs, the procedure can also accurately identify the location of the damage, and the effect of waveform recognition increases as the degree of damage becomes more profound.Based on the above analysis, it can be observed that the programme can accurately output the location of the damage, regardless of whether single or multiple points of damage occur on the structure. Moreover, the recognition effect increases as the degree of damage becomes more profound.


### 3.3. Identification of Degree of Damage

The identification of the degree of structural damage is based on working condition 1, which has been discussed previously. A single-damage wavelet coefficient difference waveform is placed in the same coordinate system to generate a three-dimensional surface graph for analysis when the structural damage occurs at the levels of 5%, 6%, 10%, 15%, and 20%, as shown in Figure14.Figure 14
Three-dimensional curved surface of the single-damage wavelet coefficient in working condition 2.It can be observed from Figure14 that the peak at the damage point of the structure increases as the degree of damage increases. The programme’s output peak point is then used to fit the curve, as shown in Figure 15.Figure 15
Fitting curve for structure with single damage.From Figure15, it can be observed that the curve fitting effect is very good, and the regression equation is formulated according to the following equation:(8)y=1.965e−06x3+8.011e−07x2+0.005187x−0.0004157,where x is the peak of the wavelet coefficient difference. In other words, the degree of damage to the structure can be estimated according to the wavelet coefficient difference obtained by equation (8).When the structure has different degrees of damage in different sections, the five wavelet coefficient difference waveforms are placed in the same coordinate system to generate a three-dimensional surface map for analysis, as shown in Figure16.Figure 16
Three-dimensional surface of the wavelet coefficients of multiple points of damage in working condition 2.The output peak fitting curve is shown in Figure17.Figure 17
Fitted curves at multiple damage levels. Multidamage fittings for sections (a) 9, (b) 19, and (c) 34.
(a)(b)(c)As shown in Figure17, the three curve fitting effects are still very good, and the regression equation can be obtained as shown in the following equation:(9)y=3.35×10−4x3−0.0001167x2+0.006311x−0.005057,y=6.731×10−5x3−2.884×10−3x2+0.0023527x−0.002761,y=7.816×10−6x3+2.011×10−3x2+0.004552x+0.000659,where y1,y2,y3 denote the degrees of damages of the three damage points and x1,x2,x3 are the peak values of the wavelet coefficient differences of the three damage points.In other words, when there are multiple points of damage to the structure, the peak value of the wavelet coefficient difference obtained via the fitting formula and calculation can also be used to evaluate the degree of damage to the structure.


### 3.4. Experimental Verification

To verify the feasibility of the intelligent recognition programme further, six groups of I-shaped steel beams made of Q235 were set up. One group has a reference nondamaged steel beam, and five groups have damaged steel beams. Single and multiple damage are set to simulate the extent of damage by reducing the section size. The boundary condition is a hinged support condition on one side and sliding support on the other. The test was conducted using the force hammer multipoint excitation and the single-point response method. The acceleration sensor is arranged at the No. 4 node with a frequency response of 0.57000 Hz, an axial sensitivity of 100 mV/g, and a measurement range of ±50 g. Each parameter meets the data acquisition of the test beam. Before the beginning of data collection, the test beam was pretested, and the predivided joints of the I-shaped steel beams were knocked with a force hammer. Official acquisition begins after good data repeatability is achieved. Data from the same node are collected repeatedly, and the final data are obtained multiple times. The experimental field layout is shown in Figure18.Figure 18
Experimental layout.The structural sketch and I-shaped steel beam cross-sections are shown in Figure19. Affected by processing technology, the minimum degree of damage to the test beam is set at 5%. The parameters of the test beam are listed in Table 3.Figure 19
Diagrams of structure and cross section.Table 3
List of working conditions.
Beam numberDamage location (mm)Damage sectionDegree of damage (%)No. 1 beam———No. 2 beam900–1000105No. 3 beam900–1000106No. 4 beam900–10001010No. 5 beam900–10001020No. 6 beam400–500, 900–1000, 1400–15005, 10, 155, 6, 10Considering that the first-order frequency is easier to obtain in practical engineering applications, the first-order modal data are associated with the intelligent identification programme, and the output wavelet coefficient difference diagrams are presented in Figures20–22.Figure 20
Wavelet coefficient difference for 10% damage in section 10.Figure 21
Wavelet coefficient difference for 20% damage in section 10.Figure 22
Wavelet coefficient difference for 20% damage in section 10.Figures21, 23, and 24 show that when single damage occurs to the structure, the waveform intensity at the damaged area will increase significantly. However, the waveform at the undamaged area also fluctuates to some extent, whereas the finite element calculation results are relatively flat. The programme can still output the same abscissa as the preset damage location. However, it will be difficult to identify the location of the structural damage if very minor damage occurs at other locations.Figure 23
Wavelet coefficient difference for 5% damage in section 10.Figure 24
Wavelet coefficient difference for 6% damage in section 10.As shown in Figure24, the location of the damage can be identified when there are multiple structural points of damage, but it is difficult to determine the degree of damage if these are similar. When minor damage occurs, the location of the damage cannot be determined; hence, the fitting effect of the damage degree is not good. However, when the structure size increases and the section partition density increases, the recognition effect will be improved considerably.The fitting curves of experimental beams No. 2 to No. 5 are output by the programme, and the regression equation of the single-damage case is derived as shown in the following equation:(10)y=6.064×10−6x3−0.00105x2+0.04068x+0.005135.As shown in Figure25, the trend of the fitted curve of the test data is generally similar to that of the finite element simulation data, and the actual damage can also be evaluated by the peak value of the wavelet coefficient.Figure 25
Fitted curve for single damage.


## 3.1. Simulation Results and Wavelet Analysis

To establish a finite element analysis model for simply supported T-beams, the following parameters are set: beam lengthL = 20 m, elastic modulus E = 32500 MPa, density γ = 2549 kg/m³, moment of inertia I = 1.62 × 10−1 m4, and Poisson’s ratio υ = 0.2. The damage locations are distributed according to the working conditions and distributed at different sections for simulation. The degree of damage was simulated according to the damage and the stiffness of the section (estimated as the product of the modulus of elasticity and the moment of inertia of the section). In the simulation, the beam is first divided into 40 sections (as shown in Figure 2), the length of each section is 0.5 m, and the type of element is the beam element in the software Midas civil (2019). The constraint conditions are left-hinged and right sliding supports.Figure 2
Structural layout of simply supported T-beam.First, the structure is analysed to obtain the vibration modes of the damage-free model and the damage model for each node. Second, according to equation (5), the curvature mode is obtained and then normalised. Thereafter, the Daubechies 2 wavelet transform is selected in MATLAB (R2016b, MathWorks, Natick, MA, USA), and the damage-free model and wavelet coefficients are obtained. Finally, the above process is coded in MATLAB. In the general practical structural dynamic test process, low-frequency signals are easily collected accurately, and the high-frequency signal of the structure is not easily obtained accurately. Thus, the numerical simulation test used in this study uses the first-order mode of the structure in the analysis process. The structure’s diagram is shown in Figure 2.


## 3.2. Damage Location Identification

To evaluate the applicability of this method and procedure in structural damage identification, three conditions were set up in this study for analyses. The specific working conditions are listed in Table1.Table 1
List of working conditions used in the study.
Working conditionDamage location (m)Section numberDegree of damage (%)Working condition 14.2595, 6, 10, 15, 20Working condition 24.25, 9.25, 16.759, 19, 345, 6, 10, 15, 20Working condition 34.25, 9.25, 16.759, 19, 345, 6, 10After calculation, the frequency of the structure was obtained at different working conditions, which are presented in Table2.Table 2
Frequency calculation values of each working condition (cycles/s).
Degree of damage (%)Working conditionWorking condition 1Working condition 2Working condition 356.5607916.5504046.54620566.5600716.547485106.5570336.535200156.5528376.518331——206.5481256.499508——The set of damage levels in working condition 1 are 5%, 6%, 10%, 15%, and 20%. The damage location was set in section 9. The output single-damage wavelet coefficient difference diagrams based on the programme calculation are presented in Figures3–7.Figure 3
Wavelet coefficient difference graph for 5% damage in section 9.Figure 4
Wavelet coefficient difference graph for 6% damage in section 9.Figure 5
Wavelet coefficient difference graph for 10% damage in section 9.Figure 6
Wavelet coefficient difference graph for 15% damage in section 9.Figure 7
Wavelet coefficient difference graph for 20% damage in section 9.Figures3–7 show that the position of the output damage is consistent with the preset damage position. Moreover, waveform analysis reveals that the waveform amplitude associated with the damaged area will be significantly increased as the degree of damage increases, and the amplitude of the undamaged position waveform is close to zero.Working condition 2 constitutes the set of multidamage conditions with damage locations in sections 9, 19, and 34, and the damage degree is the same at the three locations. The five damage levels of 5%, 6%, 10%, 15%, and 20% are analysed. The output multidamage wavelet coefficient difference diagrams obtained through the programme calculation are presented in Figures8–12.Figure 8
Wavelet coefficient difference for 5% damage in sections 9, 19, and 34.Figure 9
Wavelet coefficient difference for 6% damage in sections 9, 19, and 34.Figure 10
Wavelet coefficient difference for 10% damage in sections 9, 19, and 34.Figure 11
Wavelet coefficient difference for 15% damage in sections 9, 19, and 34.Figure 12
Wavelet coefficient difference for 20% damage in sections 9, 19, and 34.It can be observed (from Figures8–12) that when multiple points of damage of the same degree occur in the structure, an obvious waveform protrusion will occur at each damage level, and the output damage location will be consistent with the preset damage location. The extent of protrusion of the waveform will also increase as the degree of damage increases.Working condition 3 is also a multidamage condition. It is a condition in which there are multiple points of damage of different degrees to the structure. In particular, 5% damage occurs in section 9, 6% damage occurs in section 19, and 10% damage occurs in section 34. The output multidamage wavelet coefficient difference diagrams obtained after programme calculation is presented in Figure13.Figure 13
Wavelet coefficient differences of 5%, 6%, and 10% for damage in sections 9, 19, and 34, respectively.As shown in Figure13, when several degrees of structural damage occurs, the procedure can also accurately identify the location of the damage, and the effect of waveform recognition increases as the degree of damage becomes more profound.Based on the above analysis, it can be observed that the programme can accurately output the location of the damage, regardless of whether single or multiple points of damage occur on the structure. Moreover, the recognition effect increases as the degree of damage becomes more profound.


## 3.3. Identification of Degree of Damage

The identification of the degree of structural damage is based on working condition 1, which has been discussed previously. A single-damage wavelet coefficient difference waveform is placed in the same coordinate system to generate a three-dimensional surface graph for analysis when the structural damage occurs at the levels of 5%, 6%, 10%, 15%, and 20%, as shown in Figure14.Figure 14
Three-dimensional curved surface of the single-damage wavelet coefficient in working condition 2.It can be observed from Figure14 that the peak at the damage point of the structure increases as the degree of damage increases. The programme’s output peak point is then used to fit the curve, as shown in Figure 15.Figure 15
Fitting curve for structure with single damage.From Figure15, it can be observed that the curve fitting effect is very good, and the regression equation is formulated according to the following equation:(8)y=1.965e−06x3+8.011e−07x2+0.005187x−0.0004157,where x is the peak of the wavelet coefficient difference. In other words, the degree of damage to the structure can be estimated according to the wavelet coefficient difference obtained by equation (8).When the structure has different degrees of damage in different sections, the five wavelet coefficient difference waveforms are placed in the same coordinate system to generate a three-dimensional surface map for analysis, as shown in Figure16.Figure 16
Three-dimensional surface of the wavelet coefficients of multiple points of damage in working condition 2.The output peak fitting curve is shown in Figure17.Figure 17
Fitted curves at multiple damage levels. Multidamage fittings for sections (a) 9, (b) 19, and (c) 34.
(a)(b)(c)As shown in Figure17, the three curve fitting effects are still very good, and the regression equation can be obtained as shown in the following equation:(9)y=3.35×10−4x3−0.0001167x2+0.006311x−0.005057,y=6.731×10−5x3−2.884×10−3x2+0.0023527x−0.002761,y=7.816×10−6x3+2.011×10−3x2+0.004552x+0.000659,where y1,y2,y3 denote the degrees of damages of the three damage points and x1,x2,x3 are the peak values of the wavelet coefficient differences of the three damage points.In other words, when there are multiple points of damage to the structure, the peak value of the wavelet coefficient difference obtained via the fitting formula and calculation can also be used to evaluate the degree of damage to the structure.


## 3.4. Experimental Verification

To verify the feasibility of the intelligent recognition programme further, six groups of I-shaped steel beams made of Q235 were set up. One group has a reference nondamaged steel beam, and five groups have damaged steel beams. Single and multiple damage are set to simulate the extent of damage by reducing the section size. The boundary condition is a hinged support condition on one side and sliding support on the other. The test was conducted using the force hammer multipoint excitation and the single-point response method. The acceleration sensor is arranged at the No. 4 node with a frequency response of 0.57000 Hz, an axial sensitivity of 100 mV/g, and a measurement range of ±50 g. Each parameter meets the data acquisition of the test beam. Before the beginning of data collection, the test beam was pretested, and the predivided joints of the I-shaped steel beams were knocked with a force hammer. Official acquisition begins after good data repeatability is achieved. Data from the same node are collected repeatedly, and the final data are obtained multiple times. The experimental field layout is shown in Figure18.Figure 18
Experimental layout.The structural sketch and I-shaped steel beam cross-sections are shown in Figure19. Affected by processing technology, the minimum degree of damage to the test beam is set at 5%. The parameters of the test beam are listed in Table 3.Figure 19
Diagrams of structure and cross section.Table 3
List of working conditions.
Beam numberDamage location (mm)Damage sectionDegree of damage (%)No. 1 beam———No. 2 beam900–1000105No. 3 beam900–1000106No. 4 beam900–10001010No. 5 beam900–10001020No. 6 beam400–500, 900–1000, 1400–15005, 10, 155, 6, 10Considering that the first-order frequency is easier to obtain in practical engineering applications, the first-order modal data are associated with the intelligent identification programme, and the output wavelet coefficient difference diagrams are presented in Figures20–22.Figure 20
Wavelet coefficient difference for 10% damage in section 10.Figure 21
Wavelet coefficient difference for 20% damage in section 10.Figure 22
Wavelet coefficient difference for 20% damage in section 10.Figures21, 23, and 24 show that when single damage occurs to the structure, the waveform intensity at the damaged area will increase significantly. However, the waveform at the undamaged area also fluctuates to some extent, whereas the finite element calculation results are relatively flat. The programme can still output the same abscissa as the preset damage location. However, it will be difficult to identify the location of the structural damage if very minor damage occurs at other locations.Figure 23
Wavelet coefficient difference for 5% damage in section 10.Figure 24
Wavelet coefficient difference for 6% damage in section 10.As shown in Figure24, the location of the damage can be identified when there are multiple structural points of damage, but it is difficult to determine the degree of damage if these are similar. When minor damage occurs, the location of the damage cannot be determined; hence, the fitting effect of the damage degree is not good. However, when the structure size increases and the section partition density increases, the recognition effect will be improved considerably.The fitting curves of experimental beams No. 2 to No. 5 are output by the programme, and the regression equation of the single-damage case is derived as shown in the following equation:(10)y=6.064×10−6x3−0.00105x2+0.04068x+0.005135.As shown in Figure25, the trend of the fitted curve of the test data is generally similar to that of the finite element simulation data, and the actual damage can also be evaluated by the peak value of the wavelet coefficient.Figure 25
Fitted curve for single damage.


## 4. Conclusions

Based on the curvature mode and wavelet transform theory, this study used MATLAB to edit the structural damage intelligent identification programme and verified its feasibility based on numerical simulations and experimental data. The method proposed in this study has been used for damage identification of simply supported beam systems. In the future, we will continue to study the application of this method in continuous beam systems or more complex bridge systems. The following are the conclusions we obtained:(1)
When single damage occurs in the structure, the small programme can accurately output the damage location, and the peak fitting formula of the wavelet coefficient difference can be used to estimate the degree of damage to the structure.(2)
When multiple points of damage occur in the structure, the programme can output the damage location. If multiple very small points of damage occur, this method may not be effective in identifying them. Considering that the stiffness of the structure usually decreases to some extent when the actual structure is damaged, this method is considered to be feasible.(3)
The vibration modes identified by the analysis system used in this test can be calculated as accurately as the last two decimal points. If the calculation accuracy can be improved further, the effect of damage identification will improve considerably. In addition, the components used in this experiment were small and had increased stiffness. If applied to the actual bridge structure, the experimental effect will be better. If the division accuracy of the structural sections is improved, it will also be helpful for the improvement of the effect of damage identification.(4)
The programme can be applied to bridge health monitoring systems in the future. It can read the vibration mode data in real-time and output the structural damage location in real-time. In this respect, the structural damage identification technology tends to be intelligent.



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*Source: 8847524-2021-02-26.xml*