CN114923650A - Rapid structural damage identification method based on vibration mode difference ratio matrix and mode matching - Google Patents
Rapid structural damage identification method based on vibration mode difference ratio matrix and mode matching Download PDFInfo
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Abstract
The invention discloses a method for quickly identifying structural damage based on vibration mode difference ratio matrix and pattern matching, which comprises the following steps: analyzing and simulating the damage of the structure under various working conditions by using a finite element of simulation software to obtain inherent frequency and vibration mode data under each damage condition, and constructing a vibration mode difference ratio matrix as an index to construct a damage mode library according to the vibration mode data; collecting structural acceleration data, calculating the response power spectral ratio of the signal, and calculating the relationship between the amplitude of the response power spectral ratio at the pole position and the vibration mode ratio
Constructing a vibration mode difference ratio matrix of the response signal, matching the vibration mode difference ratio matrix with a vibration mode difference ratio matrix in a damage mode library, and obtaining the most similar vibration mode difference ratio matrix in the damage mode libraryThe condition is considered as a damage condition of the structure. The method only needs to obtain a structural response signal, is not influenced by excitation, does not identify modal parameters or perform complex calculation, and can realize the purpose of quickly identifying damage.
Description
Technical Field
The invention relates to the technical field of building structure safety performance evaluation, in particular to a method for quickly identifying structural damage based on vibration mode difference ratio matrix and mode matching.
Background
The method has great significance for quick safety performance evaluation of the building structure in the disaster area after the earthquake, and common vibration mode and frequency methods are insensitive to damage during evaluation. For conventional damage detection methods, for example: most of visual methods, inclination methods and some traditional dynamic fingerprint detection methods can only realize the positioning of structural damage and cannot effectively estimate the structural damage degree, and most methods are closely related to excitation, need a specific excitation mode, are difficult to realize in engineering practice, and cannot quickly estimate the safety performance of the building structure to be detected.
Disclosure of Invention
The invention aims to solve the problems of difficult artificial excitation, complex calculation, various measuring points and the like of a building structure to be measured after a disaster, and provides a structural damage rapid identification method based on vibration mode difference ratio matrix and mode matching, which can rapidly identify the position and degree of the structural damage of the building to be measured, is not influenced by external excitation, does not need to know reference data of the building structure to be measured, and can realize rapid evaluation of the safety performance of the building structure in the disaster area after the earthquake.
The purpose of the invention can be achieved by adopting the following technical scheme:
a method for quickly identifying structural damage based on vibration mode difference ratio matrix and mode matching comprises the following steps:
s1, constructing a mode difference ratio, wherein the mode is as follows:
in the formula: subscripts a, b, c and d respectively represent different layers of the building structure to be tested; subscript r represents the natural frequency of the building structure to be tested in order r;
respectively representVibration mode values of a layer a, a layer b, a layer c and a layer d under the natural frequency of the order r;
s2, carrying out finite element analysis on the simulation software of the building structure to be tested to obtain and store natural frequency and vibration mode data of various damage working conditions;
s3, vibration mode difference ratio calculation is carried out on the vibration mode values of each layer of the building structure to be measured, each order of natural frequency of each working condition obtains a vibration mode difference ratio matrix respectively, the vibration mode difference ratio matrices have the same form, wherein the vibration mode difference ratio matrix A is obtained under the r order of natural frequency of the kth working condition kr The form is as follows:
in the formula: subscripts 0, 1,2,3,4 … n-3, n-2, n-1, n respectively represent the number of layers of the building structure to be tested;
respectively represent the vibration mode values of 0, 1,2,3,4 … n-3, n-2, n-1 and n layers under the natural frequency of the r order,
the mode shape value of (1) is 0;
comparing the vibration mode difference ratio matrix A kr Is simplified into
[1:1,1:2,…,1:n,2:2,2:3,…,2:n,…,n:n]
In the formula: n represents the number of layers of the row of the vibration mode difference ratio data in the matrix, the first n represents the vibration mode difference value between the n layers of the row of the vibration mode difference ratio data, and the second n represents the vibration mode difference value between the n layers of the row of the vibration mode difference ratio data;
s4, combining the vibration mode difference ratio matrixes under the r-order natural frequency before the k-th working condition to obtain a global vibration mode difference ratio matrix A (k) ([ A ]) capable of representing the structural damage state k1 A k2 A k3 … A kr ]Wherein A (k) represents a global vibration mode difference ratio matrix of the kth working condition, and when the damage mode library has q damage working conditions in total, q different vibration mode difference matrixes are obtainedA global vibration mode difference ratio matrix, establishing a damage mode library psi ═ A (1) A (2) A (3) … A (q)]Naming indexes in the damage mode library by corresponding damage conditions;
s5, at least two acceleration sensors are installed on different layers of the building structure to be tested, and response signals z (t) of the acceleration sensors under random excitation are obtained respectively;
s6, calculating the response power spectrum ratio of the response signal z (t), wherein the response power spectrum ratio is defined and the relation between the pole and the mode shape ratio of the response power spectrum ratio is as follows:
let z i (t) and z j (t) is the acceleration data of the acceleration sensor at two layers i and j, z p (t) is the acceleration data of the reference layer p, then z i (t) and z j (t) with respect to z p (t) ratio of response power spectra
Defined as the power spectrum G ip (s) and a power spectrum G jp (s) ratio, i.e.
In the formula:
w is the angular frequency of the wave or wave,
p is any reference layer, and if the reference layer is set as i, the response power spectral ratio can be obtained only by knowing the response of two layers of the building structure to be detected
Omitting superscript i for convenience of expression, i.e.
T ij (s)＝G ii (s)/G ji (s)
When s approaches the pole λ r When the frequency w is close to the r-order natural frequency w of the building structure to be measured r When satisfying the following formula
In the formula: phi is a unit of ir 、φ jr Respectively representing the vibration mode values of the i layer and the j layer under the natural frequency of the order r; namely that
Wherein: i T ij (w r ) I is the natural frequency w of the two layers of response signals of i and j in the order of r r Lower response power spectral ratio amplitude;
s7, utilizing response power spectrum ratio to obtain natural frequency w in r order r The following relationship to mode shape ratio constructs the mode shape difference ratio derived from the response signal, defined as follows:
wherein: i T ae (w r )|、|T be (w r )|、|T ce (w r )|、|T de (w r ) I is response signals of a two layers a and e of the building structure to be detected, a two layers b and e of the building structure to be detected, a two layers c and e of the building structure to be detected and a two layers d and e of the building structure to be detected at the natural frequency w r The lower response power spectrum ratio amplitude value e is any layer of the building structure to be measured with the vibration type value not 0,
representing the mode shape value of the e layer under the natural frequency of the r order;
s8, constructing a mode shape difference ratio matrix obtained by the response signals, wherein the mode shape difference ratio matrix has the same form, and the r-order natural frequency w of the k-th working condition r Lower vibration type difference ratio matrix B kr The form of (A) is as follows:
in the formula: i T 0e |、|T 1e |、|T 2e |、|T 3e |、|T 4e |、|T (n-3)e |、|T (n-2)e |、|T (n-1)e |、|T ne | represents the natural frequency w in the order of r r Lower building structure 0 to be tested, two layers of e, building structure 1 to be tested, two layers of e, building structure 2 to be tested, two layers of e, building structure 3 to be tested, two layers of e, building structure 4 to be tested, two layers of e, building structure n-3 to be tested, two layers of e, building structure n-2 to be tested, two layers of e, building structure n-1 to be tested, two layers of e, building structure n to be tested, two layers of e, response power spectrum ratio amplitude of building structure n to be tested and two layers of e, e is any layer of building structure to be tested with vibration type value not 0, | T 0e The value of | is 0;
s9, combining the mode shape difference ratio matrixes under the pre-k-order natural frequency of the working condition to obtain B (k) ═ B k1 B k2 B k3 … B kr ]Wherein B (k) represents a global vibration pattern difference ratio matrix obtained by substituting the r-order natural frequency before the k-th working condition into the amplitude of the response power spectral ratio, q global vibration pattern difference ratio matrices obtained by substituting the natural frequency of q damage working conditions into the amplitude of the response power spectral ratio, and a matching matrix psi ═ B (1) B (2) B (3) … B (q)]；
S10, matching q global vibration mode difference ratio matrixes in the matching matrix psi with q global vibration mode difference ratio matrixes in the damage mode library psi in a one-to-one mode by adopting a correlation coefficient difference inverse ROCCD, wherein the working condition corresponding to the maximum value of the correlation coefficient difference inverse ROCCD is the actual damage condition of the building structure to be detected.
Further, it is noted that, in the step S3, the number of elements in each row of the matrix is different, the vibration mode difference ratio matrix is constructed in the form of [1:1,1:2, …,1: n,2:2,2:3, …,2: n, …, n: n ], a ratio relationship between all vibration mode differences on the building structure to be tested under a certain order of natural frequency can be constructed, the state of the building structure to be tested is represented, and when damage occurs, because the vibration mode value at the damaged position changes greatly, the vibration mode values at other positions also change correspondingly, and the vibration mode difference ratio matrix is further driven to change greatly.
Further, r vibration mode difference ratio matrixes can be constructed by utilizing the first r-order natural frequency of the building structure to be tested in the step S4, the current state of the building structure to be tested can be represented by the combination of the r vibration mode difference ratio matrixes, and the vibration mode difference ratio is only related to the natural attribute vibration mode of the building structure to be tested and is irrelevant to excitation, so that the vibration mode difference ratio can be used as an index for representing the building structure to be tested in a damage mode library.
Further, the relation between the dynamic response signal and the mode parameter vibration mode can be obtained by calculating the response power spectral ratio of the building structure to be tested, and a vibration mode difference ratio matrix obtained by the response power spectral ratio can be constructed according to the relation between the response power spectral ratio and the vibration mode ratio and is also irrelevant to excitation, so that the dynamic response signal can be accurately matched with data in a damage mode library.
Furthermore, the finite element analysis of the simulation software also comprises a damage position and a damage degree, and the damage position and the damage degree of the building structure to be detected can be obtained after the mode matching.
Further, in step S10, a similarity analysis is performed by using the reciprocal of the correlation coefficient difference, and the formula is as follows:
sorting the data in the matrix A (k), wherein m is the total number of the matrix data, the sequence of the data in the matrix A (k) is from top to bottom, the first column value is first, then the second column value is second, and the last column value is first, the sequence number is from 1 to m, and the matrix B (k) is sorted in the same way;
wherein, A (k) l The l-th matrix element of the matrix a (k),
is the average of all matrix elements in matrix a (k); b (k) l The l-th matrix element of the matrix b (k),
is the average of all matrix elements in matrix b (k); the larger the ROCCD value, the higher the degree of matching.
Compared with the prior art, the invention has the following advantages and effects:
1) the vibration mode difference ratio matrix concept provided by the invention can sensitively represent the vibration mode change caused by the structural damage of the building to be detected, and the vibration mode difference ratio matrix obtained from the response power spectrum ratio eliminates the influence of excitation, does not need to carry out mode identification, and only needs to carry out a small amount of vibration detection work.
2) The vibration mode difference ratio matrix is used for pattern matching, the matching process only needs to carry out simple one-to-one matching on the obtained vibration mode difference ratio matrix, complex operation and iteration processes are not involved, and the target of quickly identifying the structural damage of the building to be detected can be achieved.
3) According to the method, only part of the vibration mode difference ratio relation needs to be known, all vibration mode difference ratio data exist in the damage model library, elements related to the measuring points in the library can be selected according to the actual measuring points for matching, the damage position can be located and the damage degree can be quantified by using a small amount of sensor data, the number of sensors is reduced, the cost is low, the implementation process is simple, and the practicability in the damage detection problem is effectively improved.
4) And the data are matched by adopting a correlation coefficient difference reciprocal method, the result display effect is good, and the final matching result can be intuitively known.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention and do not constitute a limitation of the invention. In the drawings:
FIG. 1 is a diagram illustrating a method for rapidly identifying structural damage based on a mode shape difference ratio matrix and mode matching, according to an embodiment of the present invention;
FIG. 2 is a diagram of a numerical simulation interlaminar shear model in accordance with an embodiment of the present invention;
FIG. 3 is a schematic diagram of an acceleration original signal measured by numerical simulation according to an embodiment of the present invention;
FIG. 4 is a graph showing the result of the ratio of the response power spectra of the measured acceleration signals at 1 and 4 points in numerical simulation according to the first embodiment of the present invention;
FIG. 5 is a diagram illustrating the recognition result of the numerical simulation lossless mode 0-0-0 according to the first embodiment of the present invention;
FIG. 6 is a diagram illustrating the recognition result of the numerical simulation single-loss operating mode 40-0-0-0 according to the first embodiment of the present invention;
FIG. 7 is a diagram illustrating the recognition results of the numerical simulation double-loss operating mode 0-60-60-0 according to the first embodiment of the present invention;
FIG. 8 is a diagram illustrating the recognition results of the numerical simulation double-loss operating mode 38-0-18-0 according to the first embodiment of the present invention;
FIG. 9 is a structural diagram of an experimental interlaminar shear in the second embodiment of the present invention;
FIG. 10 is a schematic diagram of the acceleration signal applied in the experiment according to the second embodiment of the present invention;
FIG. 11 is a diagram illustrating the result of identifying experimental non-destructive operating conditions in the second embodiment of the present invention;
FIG. 12 is a graph of the identification result of the experimental single-loss operating condition 40-0-0-0 in the second embodiment of the present invention;
FIG. 13 is a graph of the recognition results of the experimental double-loss operating condition 40-0-20-0 in the second embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example one
As shown in fig. 1, fig. 1 is a flowchart of a method for rapidly identifying structural damage based on local transfer rate function and pattern matching, and a schematic diagram of a simulation of a 4-layer interlayer shear model used in the first embodiment is shown in fig. 2. Wherein the building of the upright post and the floor respectively adopts beam3 and mass21 units. Under the condition of no damage, the height of each layer of upright post of the model is 0.2m, the width is 0.1m, the thickness is 0.01m, the total height of the model is 0.8m, and the floor mass is 1 kg.The material is steel, and the density and the elastic modulus are respectively as follows: rho 7850kg/m 3 、E＝1.99e 11 Pa. The specific implementation process is as follows:
t1, reducing the interlayer rigidity of each layer of the model in the first embodiment to simulate damage working conditions, performing modal analysis on each working condition, storing respective inherent frequency and vibration mode data, and establishing 67 damage modes according to a vibration mode difference ratio matrix shown in table 1, wherein 0-0-0-0 represents that the rigidity of the first layer is reduced by 0%, the rigidity of the second layer is reduced by 0%, the rigidity of the third layer is reduced by 0%, and the rigidity of the fourth layer is reduced by 0%.
TABLE 1 Damage Pattern library
T2, acquiring an acceleration response signal of the model under the environment excitation, and displaying the acceleration response signal in the environment excitation as shown in figure 3.
T3, calculating the response power spectrum ratio of the acceleration response, and taking the response power spectrum ratio curve of 1 point and 4 points as shown in fig. 4.
T4, first order mode only considered, i.e. using only first order mode shape data in accordance with [1:1,1:2, …,1: n,2:2,2:3, …,2: n, …, n: n]Constructing global vibration mode difference ratio matrixes of 67 working conditions for the four-layer interlayer shearing model in a form, and constructing a vibration mode difference ratio damage mode library psi [ A (1) A (2) A (3) … A (67) ]]Wherein
The matrix form is:
first row
A total of 16 elements;
second row
A total of 12 elements;
third column
A total of 8 elements;
fourth column
A total of 4 elements;
the last six columns are as follows:
and T5, only considering a first-order mode, and constructing a global mode shape difference ratio matrix according to a response power spectrum ratio and a four-layer interlayer shearing model, wherein the result is as follows according to the form of [1:1,1:2, …,1: n,2:2,2:3, …,2: n, … and n: n ]:
first row
A total of 16 elements;
second column
A total of 12 elements;
third column
A total of 8 elements;
fourth column
A total of 4 elements;
the last six columns are as follows:
wherein e is any layer of 1,2,3,4, | T 0e |＝0。
And T6, substituting the first-order natural frequencies of 67 working conditions into a mode shape difference ratio matrix constructed by the response power spectrum ratio to obtain a corresponding matching matrix psi ═ B (1) B (2) B (3) … B (67).
T7, matching the mode shape difference ratio matrix obtained by the T6 and 67 mode shape difference ratio matrices in the library in a one-to-one mode as follows:
wherein m is 65, A (k) l The l-th matrix element of the matrix a (k),
is the average of all matrix elements in matrix a (k); b (k) l The l-th matrix element of the matrix b (k),
is the average of all matrix elements in matrix b (k); the larger the ROCCD value, the higher the degree of matching.
T8, 4 damage test working conditions are selected, and the information of damage positions and damage degrees is shown in table 2. Through steps T5, T6 and T7 in the first embodiment, the ROCCD value of each damage mode is obtained, and is drawn into a histogram, from which the damage mode library number corresponding to the maximum ROCCD value is obtained, that is, the number is regarded as the real damage condition of the building structure to be tested.
TABLE 2 details of the numerical simulation test conditions
| Lossless and non-destructive | Single loss | Double loss | Double loss |
| 0-0-0-0 | 60-0-0-0 | 0-60-60-0 | 38-0-18-0 |
Example two
And (5) constructing an interlaminar shearing experimental model. The experimental model simulates the quality between the upright column and the floor of the actual floor by a steel plate and a mass block, and the size and the physical parameters of the steel plate are as follows: width and height 0.1m 0.8m 0.01m, material density and elastic modulus: rho 7850kg/m 3 、E＝1.99e 11 Pa. 8 mass blocks with the weight of 1kg are symmetrically hung at the positions of 0.2m, 0.4m, 0.6m and 0.8m of steel plates to simulate floors, as shown in figure 9. The damage mode database shown in table 1 was created based on the damage modes of the model in the second finite element simulation example.
P1, the effect of simulating damage is achieved by reducing the width of the steel plate during the experiment. Three experimental simulation conditions to be measured are shown in table 3:
TABLE 3 Experimental test Condition details
| Lossless and non-destructive | Single loss | Double loss |
| 0-0-0-0 | 40-0-0-0 | 40-0-20-0 |
P2, knocking the center of the interlayer steel plate by using a force hammer, collecting an acceleration response signal and calculating a response power spectrum ratio of the signal of the sensor, as shown in fig. 10.
And P3, selecting numerical simulation first-order vibration mode data, constructing a vibration mode difference ratio matrix, and obtaining 67 vibration mode difference ratio matrices which are stored in a damage mode library.
And P4, selecting the first-order mode shape data, and constructing a mode shape difference ratio matrix according to the response power spectrum ratio.
And P5, substituting 67 first-order natural frequencies obtained by numerical simulation into P4 to obtain 67 matrix of mode shape difference ratios to be matched.
P6, matching by reciprocal correlation coefficient difference as follows:
wherein m is 65, A (k) l The l-th matrix element of the matrix a (k),
is the average value of all matrix elements in the matrix A (k); b (k) l The l-th matrix element of the matrix b (k),
is the average of all matrix elements in matrix b (k); the larger the ROCCD value, the higher the degree of matching.
P7, selecting 3 damage test working conditions, wherein the information of damage positions and damage degrees is shown in Table 3. Through the steps in the second embodiment, the ROCCD values of the working conditions and the modes to be tested are obtained, the ROCCD values are drawn into a histogram, the mode number corresponding to the maximum ROCCD value can be obtained, and then the damage mode corresponding to the mode number is found out through the damage mode database, namely, the damage mode is regarded as the real damage condition of the building structure to be tested.
In summary, the present embodiment provides a method for quickly identifying structural damage based on a mode shape difference ratio matrix and mode matching. Firstly, the pattern matching does not involve complex algorithm, only the matrix obtained by the response signal and the matrix in the damage pattern library are needed to be matched one to one, and the damage position and the damage degree of the structure can be quickly identified without the data of all the measuring points of the structure. Secondly, the method only needs to obtain a structural response signal, is not influenced by excitation, has low cost and simple implementation process, and can realize the aim of quickly identifying the damage. Finally, the method matches the data by adopting a correlation coefficient difference reciprocal method, the final result display effect is better, and the final matching result can be intuitively understood.
The above embodiments are preferred embodiments of the present invention, but the present invention is not limited to the above embodiments, and any other changes, modifications, substitutions, combinations, and simplifications which do not depart from the spirit and principle of the present invention should be construed as equivalents thereof, and all such modifications are intended to be included in the scope of the present invention.
Claims (3)
1. A method for quickly identifying structural damage based on vibration mode difference ratio matrix and pattern matching is characterized by comprising the following steps of:
s1, constructing a mode difference ratio, wherein the mode is as follows:
in the formula: subscripts a, b, c and d respectively represent different layers of the building structure to be tested; subscript r represents the natural frequency of the building structure to be tested in order r;
respectively representing the vibration mode values of a layer a, a layer b, a layer c and a layer d under the natural frequency of the order r;
s2, carrying out finite element analysis on the simulation software of the building structure to be tested to obtain and store natural frequency and vibration mode data of various damage working conditions;
s3, calculating the vibration mode difference ratio of each layer of the building structure to be measured, and obtaining a vibration mode difference ratio moment from each order of natural frequency of each working conditionThe matrix of vibration mode difference ratio has the same form, wherein the matrix A of vibration mode difference ratio under r order natural frequency of k type working condition kr The form is as follows:
in the formula: subscripts 0, 1,2,3, 4.. n-3, n-2, n-1, n respectively represent the number of layers of the building structure to be tested;
respectively represent the vibration mode values of 0, 1,2,3, 4.. n-3, n-2, n-1 and n layers under the natural frequency of the r order,
the mode shape value of (1) is 0;
using the vibration mode difference ratio matrix A kr Is simplified into
[1：1，1：2，...，1：n，2：2，2：3，...，2：n，...，n：n]
In the formula: n: n represents the number of layers of the row of mode shape difference ratio data in the matrix, the first n represents the mode shape difference value between the n layers of the phase difference of the numerator of the row of mode shape difference ratio data, and the second n represents the mode shape difference value between the n layers of the phase difference of the denominator of the row of mode shape difference ratio data;
s4, combining the mode shape difference ratio matrixes under the pre-k working condition r order natural frequency to obtain a global mode shape difference ratio matrix A (k) [ [ A ] ]which can represent the structural damage state k1 A k2 A k3 ... A kr ]Wherein A (k) represents a global vibration mode difference ratio matrix of a k-th working condition, when a damage mode library has q damage working conditions in total, q different global vibration mode difference ratio matrices are obtained, and a damage mode library psi [ [ A (1) A (2) A (3.. A (q) ])]Naming indexes in the damage mode library by corresponding damage conditions;
s5, at least two acceleration sensors are installed on different layers of the building structure to be tested, and response signals z (t) of the acceleration sensors under random excitation are respectively obtained;
s6, calculating the response power spectrum ratio of the response signal z (t), wherein the response power spectrum ratio is defined and the relation between the pole and the mode shape ratio of the response power spectrum ratio is as follows:
let z i (t) and z j (t) is the acceleration data of the acceleration sensor at two layers i and j, z p (t) is the acceleration data of the reference layer p, then z i (t) and z j (t) with respect to z p (t) response power spectral ratio
Defined as the power spectrum G ip (s) and a power spectrum G jp (s) ratio, i.e.
In the formula:
w is the angular frequency of the wave,
p is any reference layer, and if the reference layer is set as i, the response power spectral ratio can be obtained by only knowing the response of two layers of the building structure to be tested
Omitting superscript i for convenience of expression, i.e.
T ij (s)＝G ii (s)/G ji (s)
When s approaches the pole λ r When the frequency w is close to the r-order natural frequency w of the building structure to be measured r When satisfying the following formula
In the formula: phi is a ir 、φ jr Respectively representing the vibration mode values of the i layer and the j layer under the natural frequency of the order r; namely, it is
Wherein: | T ij (w r ) I and j are two layers of response signals of the i and the j at the r-order natural frequency w r Lower response power spectral ratio amplitude;
s7, using response power spectrum ratio to natural frequency w in order r r The following relationship to mode shape ratio constructs the mode shape difference ratio derived from the response signal, defined as follows:
wherein: i T ae (w r )|、|T be (w r )|、|T ce (w r )|、|T de (w r ) I is response signals of a two layers a and e of the building structure to be detected, a two layers b and e of the building structure to be detected, a two layers c and e of the building structure to be detected and a two layers d and e of the building structure to be detected at the natural frequency w r The lower response power spectrum ratio amplitude value e is any layer of the building structure to be measured with the vibration type value not 0,
representing the mode shape value of the e layer under the natural frequency of the r order;
s8, constructing a mode shape difference ratio matrix obtained by the response signals, wherein the mode shape difference ratio matrix has the same form, and the r-order natural frequency w of the k-th working condition r Lower vibration type difference ratio matrix B kr The form of (A) is as follows:
in the formula: i T 0e |、|T 1e |、|T 2e |、|T 3e |、|T 4e |、|T (n-3)e |、|T (n-2)e |、|T (n-1)e |、|T ne | represents the natural frequency w in the order of r r Lower building structure 0 and two layers of building structure e to be tested, building structure 1 and two layers of building structure e to be tested, building structure 2 and two layers of building structure e to be tested, building structure 3 and two layers of building structure e to be tested, building structure 4 and two layers of building structure e to be tested, building structure n-3 and two layers of building structure e to be tested, building structure n-2 and two layers of building structure e to be tested, building structure n-1 and two layers of building structure e to be tested, response power spectrum ratio amplitude of building structure n and two layers of building structure e to be tested, e is any layer of building structure to be tested with vibration type value not 0, | T 0e The value of | is 0;
s9, combining the vibration mode difference ratio matrix at the r-th order natural frequency before the k-th operation condition to obtain B (k) ═ B k1 B k2 B k3 ... B kr ]Wherein, B (k) represents a global vibration pattern difference ratio matrix obtained by substituting the prior r-order natural frequency of the kth working condition into the amplitude of the response power spectral ratio, q natural frequencies of q damage working conditions are substituted into the amplitude of the response power spectral ratio to obtain q global vibration pattern difference ratio matrices, and a matching matrix psi is established [ B (1) B (2) B (3).. B (q)]；
S10, matching q global vibration mode difference ratio matrixes in the matching matrix psi with q global vibration mode difference ratio matrixes in the damage mode library psi in a one-to-one mode by adopting a correlation coefficient difference inverse ROCCD, wherein the working condition corresponding to the maximum value of the correlation coefficient difference inverse ROCCD is the actual damage condition of the building structure to be detected.
2. The method as claimed in claim 1, wherein the step S2 of performing the finite element analysis on the simulation software of the building structure to be tested further includes analyzing the damage position and the damage degree, the damage pattern library includes the vibration mode difference ratios of all layers and frequencies of the building structure to be tested, and the database is selected according to the number of sensors and the positions for matching in actual situations.
3. The method for rapidly identifying structural damage based on mode shape difference ratio matrix and mode matching according to claim 1, wherein the calculation formula of the inverse correlation coefficient difference ROCCD adopted in step S10 is as follows:
sequencing matrix elements in a matrix A (k), wherein m is the total number of the matrix elements in the matrix A (k), the sequence of the matrix elements in the matrix A (k) is from top to bottom, the first column of values is arranged, then the second column of values is arranged until the last column of values is arranged, the sequence number is from 1 to m, and the sequence of the matrix B (k) is the same as the sequence;
wherein, A (k) l The l-th matrix element of the matrix a (k),
is the average value of all matrix elements in the matrix A (k); b (k) l The l-th matrix element of the matrix b (k),
is the average of all matrix elements in matrix b (k); the larger the ROCCD value, the higher the degree of matching.
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