CN102998367A - Damage identification method based on virtual derivative structure - Google Patents
Damage identification method based on virtual derivative structure Download PDFInfo
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- CN102998367A CN102998367A CN2012105610813A CN201210561081A CN102998367A CN 102998367 A CN102998367 A CN 102998367A CN 2012105610813 A CN2012105610813 A CN 2012105610813A CN 201210561081 A CN201210561081 A CN 201210561081A CN 102998367 A CN102998367 A CN 102998367A
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Abstract
The invention discloses a damage identification method based on a virtual derivative structure. The damage identification method comprises the following steps of: firstly, establishing a finite element model of a to-be-tested structure (also known as a source structure) by finite element software; secondly, acquiring front several modal data of vibration of the source structure by testing of a modal testing system; thirdly, constructing a series of virtual derivative structures based on the source structure and counting corresponding feature frequency parameters of the virtual derivative structures; and finally, synthesizing feature frequencies of the source structure and all the virtual derivative structures, and obtaining a source structure damage identification result containing a damage position and a degree by a hybrid frequency sensitivity diagnostic program. According to the technical scheme, the test equipment is simple, the cost is low, the defect of the existing testing technique is effectively overcome, the accuracy of the damage identification is substantially improved, and the damage identification method is particularly suitable for being applied in the damage identification of large-sized structures.
Description
Technical field
The invention belongs to the Damage Assessment Method field of civil engineering work subject, relate to a kind of damnification recognition method based on virtual derivative strucure.
Background technology
Along with developing rapidly of national economy, large quantities of large-scale civil engineering structures have been built, such as high-rise building, Longspan Bridge, large span space roof truss etc.Because the growth of tenure of use, and the impact of environmental corrosion, Hazard Loads etc., these structures will inevitably be damaged, the local damage of structure may cause the rapid destruction of structural entity, bring massive losses to people's lives and properties, must make promptly and accurately identification to the damage status in the structure, so that the consequence of averting a calamity property of maintenance and reinforcement occurs.
Mostly traditional damnification recognition method is the experimental technique of visual part, such as ultrasonic method, methods of magnetic field, temperature field method etc.Yet all there is following major defect in said method: at first, said method requires probably to know in advance damage position, so anticipation is relatively poor; Secondly said method requires detected position equipment to arrive, so workload expends greatly height; The 3rd, because there is as above defective in said method, therefore be not suitable for the damage identification of large scale civil engineering structure.
In the last few years, research method whole, real-time, that be applicable to large scale structure damage identification had become the common focus of paying close attention to of numerous field of engineering technology such as building, machinery, aviation.Wherein, the method for utilizing the variation of large scale structure mode of oscillation data to come inverting to identify its damage is present a kind of new technology.The ultimate principle of these class methods is: the Produced by Modal data are functions of structural physical parameter (such as quality, rigidity etc.), therefore the variation (structural damage) of structural physical parameter must cause the variation of Produced by Modal parameter (frequency and the vibration shape), utilizes the variation of these vibration datas just can identify conversely the damage status of structure.Yet, because the limitation of measuring technology, can only measure at present the front several lower modes that obtain structural vibration, this can not satisfy the needs of large scale structure damage identification far away, in other words, the identification equation number that can be set up by the lower mode that measure to obtain is far smaller than the number of the impairment parameter of the unknown, and this is to cause present method to damage one of the reason of the most critical of recognition failures.
In view of this, the inventor is in conjunction with being engaged in Damage Assessment Method area research work experience for many years, and the defective of above-mentioned technical field is studied for a long period of time, and this case produces thus.
Summary of the invention
Fundamental purpose of the present invention is to provide a kind of damnification recognition method based on virtual derivative strucure, and is easy and simple to handle, and testing apparatus is simple, with low cost, improved the accuracy of damage identification.
To achieve these goals, technical scheme of the present invention is as follows:
A kind of damnification recognition method based on virtual derivative strucure may further comprise the steps: at first, set up by finite element software and to treat the not finite element model under the faulted condition of geodesic structure (being called again source structure); Secondly, measure former rank mode (being characteristic frequency and the corresponding vibration shape) data that obtain the source structure vibration by the mode test macro, the rank number of mode that needs to measure considers definite according to the complexity of structure, precision and the test site condition of surveying instrument; Then, a series of virtual derivative strucure and calculate corresponding characteristic frequency parameter take source structure as base configuration; At last, the characteristic frequency of comprehensive source structure and all virtual derivative strucures by hybrid frequency sensitivity diagnostic routine, draws the source structure damage recognition result that comprises damage position and degree.
Described mode test macro comprises a data acquisition instrument, a plurality of wireless senser and a cover mode analysis software, is measured former rank characteristic frequency and the corresponding Data of Mode that obtains the source structure vibration by the mode test macro; Wherein wireless senser is arranged in the position for the treatment of to occur easily in the geodesic structure damage, the quantity of wireless senser
Can be by formula
Determine, wherein
Be the sum of unit in the finite element model,
Number for the characteristic frequency measured.
Further, described former rank modal data refers to modal data between front 4 ~ 10 rank.
Further, described virtual derivative strucure can obtain by the way of virtual arrangement quality on source structure or rigidity, the position of virtual mass or rigidity is the position at wireless senser place, can arrange separately also and can make up layout, the size of virtual mass or rigidity be taken as source structure not under the faulted condition in the finite element model mass matrix or stiffness matrix corresponding to 10% ~ 15% of sensing station place numerical value; Adopt different virtual arrangement schemes just can obtain a series of virtual derivative strucure, the sum of the virtual derivative strucure that can construct and the quantity of sensor
Between the pass be
After virtual derivative strucure is constructed, adopt again the fundamental frequency sensitivity formula to calculate the former rank characteristic frequency parameter that obtains virtual derivative strucure.
Further, described Mixed Sensitivity diagnostic routine may further comprise the steps: at first, according to source structure and the virtual derivative strucure finite element model under the faulted condition not, calculate respectively source structure and virtual derivative strucure under the faulted condition not before
Rank characteristic frequency and corresponding fundamental frequency sensitivity; Then before will measuring the source structure of gained
Before rank characteristic frequency and each the virtual derivative strucure
The rank characteristic frequency combines, and lists the one order equation of damage front and back frequency variation, solves all unknown impairment parameter by generalizde inverse
The impairment parameter output that to calculate gained by forms such as histograms at last can accurately identify damage position and the degree of source structure.
In the technical program, only utilize the minority sensor measurement to treat former rank mode of geodesic structure (source structure) vibration, obtain more frequency information by constructing a series of virtual derivative strucure, the frequency of last joint source structure and all derivative strucures identifies the damage status of source structure.
Adopt the technical program, obtain following beneficial effect: the first, the present invention only needs the sensor seldom counted, and front several lower modes of only measuring structural vibration can carry out, and testing apparatus is simple, with low cost; Second, the present invention obtains more frequency parameter by virtual a series of derivative strucure and is used for Damage Assessment Method, effectively overcome the deficiency of existing measuring technology, thereby increased substantially the accuracy of damage identification, be particularly suitable for being applied in the damage identification of large scale structure; The 3rd, derivative strucure of the present invention is virtual construct, so need not treating actual arrangement quality or rigidity member on the geodesic structure, only needs conventional mode testing apparatus and a small amount of sensor to carry out, therefore easy to operate easy to implement, and do not increase extra test job amount; Therefore the 4th, the speed according to power increases rapidly the virtual derivative strucure quantity that the present invention can construct along with the increase of number of sensors, and the used number of sensors of the present invention is minimum under the prerequisite that satisfies damage identification needs.
Technical scheme of the present invention the present invention is described in further detail below in conjunction with drawings and Examples in order further to explain.
Description of drawings
Fig. 1 is enforcement synoptic diagram of the present invention; Label declaration wherein: the 1st, Wireless Acceleration Sensor; The 2nd, the data acquisition instrument; The 3rd, model analysis software; 1, the 2 and 3 common mode test macros that form; The 4th, treat geodesic structure (source structure); The 5th, source structure is the finite element model under the faulted condition not; The 6th, virtual derivative strucure; The 7th, the Mixed Sensitivity diagnostic routine; The 8th, the damage recognition result.
Fig. 2 is a grid structure model to be detected;
Fig. 3 is the recognition result (unit 15 losss of rigidity 15%) of single degree of impairment;
The recognition result of a plurality of degree of impairments of Fig. 4 ( unit 7 and 15 rigidity all lose 15%).
Embodiment
To Fig. 4, further detailed description is done in enforcement of the present invention below in conjunction with accompanying drawing 1.
A kind of damnification recognition method based on virtual derivative strucure may further comprise the steps: at first, set up by finite element software and to treat the not finite element model under the faulted condition of geodesic structure (being called again source structure); Secondly, measured former rank mode (being characteristic frequency and the corresponding vibration shape) data that obtain the source structure vibration by the mode test macro, the rank number of mode of need measuring considers definite according to the precision of the complexity of structure, surveying instrument and test site condition, be taken as in the present embodiment between front 4 ~ 10 rank; Then, a series of virtual derivative strucure and calculate corresponding characteristic frequency parameter take source structure as base configuration; At last, the characteristic frequency of comprehensive source structure and all virtual derivative strucures by hybrid frequency sensitivity diagnostic routine, draws the source structure damage recognition result that comprises damage position and degree.
Described source structure is the finite element model under the faulted condition not, can modeling obtains to source structure by general finite element software (such as general commercial softwares such as ANSYS or MATLAB); Repeat no more herein.In the present embodiment, described finite element model comprises stiffness matrix and mass matrix, does not consider structural damping, and adopts lumped mass matrix.
Described mode test macro comprises a data acquisition instrument, a plurality of Wireless Acceleration Sensor and a cover mode analysis software (they all can be bought by market and obtain), is measured former rank characteristic frequency and the corresponding Data of Mode that obtains the source structure vibration by the mode test macro.Wherein wireless senser is arranged in the position (determining that according to engineering experience can be arranged in span centre and beam-ends section such as girder construction, plate structure can be arranged in four jiaos and center position) for the treatment of to occur easily in the geodesic structure damage, the quantity of wireless senser
Can be by formula
Determine, wherein
Be the sum of unit in the finite element model,
Number for the characteristic frequency measured.
Described virtual derivative strucure can obtain (being not actual arrangement quality or rigidity on source structure) by the way in virtual arrangement quality or rigidity on the source structure, the position of virtual mass or rigidity is the position at wireless senser place, can arrange separately also and can make up layout, the size of virtual mass or rigidity generally be taken as source structure not under the faulted condition in the finite element model mass matrix or stiffness matrix corresponding to 10% ~ 15% of sensing station place numerical value.Adopt different virtual arrangement schemes just can obtain a series of virtual derivative strucure, the sum of the virtual derivative strucure that can construct
Quantity with sensor
Between the pass be
After virtual derivative strucure is constructed, adopt again the fundamental frequency sensitivity formula to calculate the former rank characteristic frequency parameter that obtains virtual derivative strucure.
The below comes the constructing virtual derivative strucure and calculates corresponding characteristic frequency as an example of the way of virtual arrangement quality example.If source structure not mass matrix and the stiffness matrix branch under the faulted condition is
With
, they can be obtained structural modeling by finite element software, wherein mass matrix
Be diagonal matrix
In the formula (1)
Expression degree of freedom sum.Source structure occurs before and after the damage, and fair constant and only have loss of rigidity, therefore, the finite element model under the source structure faulted condition is: mass matrix still
, and stiffness matrix is reduced to
,
Be unknown stiffness matrix, it can be expressed as
(2)
Wherein
With
Respectively in the finite element model
The impairment parameter of individual unit and element stiffness matrix.Be without loss of generality, suppose on source structure, altogether to have arranged 2 acceleration transducers, be arranged in respectively the 1st and 2 degree of freedom place, can come the virtual arrangement quality to construct 3 virtual derivative strucures in these 2 sensor layout points so, be respectively: first virtual derivative strucure be for separately in lumped mass of the 1st degree of freedom place virtual arrangement
, its stiffness matrix of virtual derivative strucure of gained is still identical with source structure, its mass matrix
Be the source structure mass matrix
With additional virtual mass matrix
Sum, namely
Second virtual derivative strucure is for separately in lumped mass of the 2nd degree of freedom place virtual arrangement
, its stiffness matrix of virtual derivative strucure of gained is still identical with source structure, its mass matrix
Be the source structure mass matrix
With additional virtual mass matrix
Sum, namely
The 3rd virtual derivative strucure is simultaneously in 2 lumped masses of the 1st and 2 degree of freedom place virtual arrangement
With
, its stiffness matrix of virtual derivative strucure of gained is still identical with source structure, its mass matrix
Be the source structure mass matrix
With additional virtual mass matrix
Sum, namely
More than after three virtual derivative strucures construct, can calculate corresponding characteristic frequency value by the fundamental frequency sensitivity formula respectively, computing formula is as follows:
In the formula (9)
With
For with the mode test macro to source structure measure obtain the
Rank characteristic frequency and the vibration shape,
Be
Of individual virtual derivative strucure
The rank characteristic frequency.Notice
In except arranging that the virtual mass position is not 0 to think that other element all is 0, so do not require the measurement vibration shape that degree of freedom is complete in the calculating of formula (9)
, and as long as part vibration shape value corresponding to the virtual mass position is arranged, and this is the position of sensor just, therefore with formula (9) when calculating used all data all be to be obtained by measurement.
Described Mixed Sensitivity diagnostic routine may further comprise the steps: at first, according to source structure and the virtual derivative strucure finite element model under the faulted condition not, calculate respectively source structure and virtual derivative strucure under the faulted condition not before
Rank characteristic frequency and corresponding fundamental frequency sensitivity; Then before will measuring the source structure of gained
Before rank characteristic frequency and each the virtual derivative strucure
The rank characteristic frequency combines, and lists the one order equation of damage front and back frequency variation, solves all unknown impairment parameter by generalizde inverse
The impairment parameter output that to calculate gained by forms such as histograms at last can accurately identify damage position and the degree of source structure.
The used formula of described Mixed Sensitivity diagnostic routine is as follows: by the source structure model matrix under the faulted condition not
With
, can obtain the characteristic frequency of source structure under the faulted condition not by finding the solution following generalized eigenvalue equation
Wherein
With
Respectively that source structure is not under the faulted condition
Individual characteristic frequency and the vibration shape.The
Individual characteristic frequency is about
The one order computing formula of individual impairment parameter is
(11)
In like manner,
Individual virtual derivative strucure not characteristic frequency and the corresponding one order computing formula under the faulted condition is
,
(12),(13)
By equation (10)-(13) just can calculate obtain source structure and all virtual derivative strucures under faulted condition not before
Rank characteristic frequency and corresponding fundamental frequency sensitivity.Then before will measuring the source structure of gained
The rank characteristic frequency and calculated by formula (9) gained each virtual derivative strucure before
The rank characteristic frequency combines, and lists the one order equation of all frequency variations of damage front and back, and it is
Wherein frequency shift is vectorial
For
The impairment parameter vector
For
The Mixed Sensitivity matrix
For
Can find the solution all impairment parameter by equation (14) by generalizde inverse, namely
(18)
Subscript "+" expression is to the Matrix Calculating generalized inverse in the equation (18).Whether will be exported with histogrammic form by all impairment parameter of equation (18) calculating gained at last, and can damage source structure, the position of damage and degree are made accurate identification.
Fig. 2 is a grid structure model to be detected, and this structure basic parameter is: elastic modulus E=200GP
a, density p=7.8 * 10
3Kg/m
3, every rod member length L=1m, rod member cross-sectional area A=0.004m
2Simulate two kinds of degree of impairments, the first situation is single damage: suppose rod member 15 losss of rigidity 15% among Fig. 2; The second situation is a plurality of damages: suppose that rod member 7 and 15 rigidity all lose 15% among Fig. 2.
The step that adopts this case institute extracting method that grid structure shown in Figure 2 is damaged identification is as follows: at first, analyze the as can be known sum of unit in its finite element model of this structural model
If quadravalence mode (namely before only measuring
), so according to formula
Can determine the quantity of wireless senser
Therefore, layout level and vertical two Wireless Acceleration Sensor on the node A in Fig. 2 are arranged a horizontal acceleration sensor in Node B, altogether arrange three sensors; Secondly, utilize mode test macro (1+2+3) to measure front quadravalence characteristic frequency and the corresponding vibration shape of grid structure vibration; The 3rd, utilize finite element software to set up the not finite element model 5 under the faulted condition of source structure; The 4th, in the level of the node A of source structure and vertical both direction (being the arranged direction of two sensors of node A) virtual arrangement quality respectively, the size of virtual mass all is taken as corresponding to 10% of sensing station place finite element model quality numerical value, thereby obtain two virtual derivative strucures 6, and calculated the front quadravalence characteristic frequency of each virtual derivative strucure by formula (9); The 5th, before measuring the source structure of gained
Before rank characteristic frequency and each the virtual derivative strucure
The rank characteristic frequency combines, and inputs in the Mixed Sensitivity diagnostic routine 7, i.e. exportable damage recognition result 8 to source structure.
Adopt the damage recognition result of this case institute extracting method to list among Fig. 3 and Fig. 4 under two kinds of degree of impairments.As seen from Figure 3, for single degree of impairment, this case institute extracting method damage recognition result shows that clearly rod member 15 damages, and the impairment parameter value is 13.9%, and default 15% is very approaching.As seen from Figure 4, for a plurality of degree of impairments, this case institute extracting method damage recognition result shows that equally clearly rod member 7 and 15 damages, and the impairment parameter value is respectively 12.4% and 13.7%, and is all very approaching with default 15%.In sum, the damnification recognition method easy operating that this case is carried is implemented, and recognition result accurately and reliably.
The technical program only utilizes the minority sensor measurement to treat former rank mode of geodesic structure (source structure) vibration, obtain more frequency information by constructing a series of virtual derivative strucure, the frequency of last joint source structure and all derivative strucures identifies the damage status of source structure.In the aforementioned techniques scheme, the technology contents that the present invention does not specify is prior art, repeats no more herein.
The present invention only needs the sensor seldom counted, and front several lower modes of only measuring structural vibration can carry out, and testing apparatus is simple, with low cost; Obtain more frequency parameter by virtual a series of derivative strucure and be used for Damage Assessment Method, effectively overcome the deficiency of existing measuring technology, increased substantially the accuracy of damage identification, be particularly suitable for being applied in the damage identification of large scale structure; Derivative strucure of the present invention is virtual construct, so need not treating actual arrangement quality or rigidity member on the geodesic structure, only need conventional mode testing apparatus and a small amount of sensor to carry out, therefore easy to operate easy to implement, and do not increase extra test job amount; Therefore speed according to power increases rapidly the virtual derivative strucure quantity that the present invention can construct along with the increase of number of sensors, and the used number of sensors of the present invention is minimum under the prerequisite that satisfies damage identification needs.
The above is specific embodiments of the invention only, is not the restriction to this case design, and all equivalent variations of doing according to the design key of this case all fall into the protection domain of this case.
Claims (4)
1. damnification recognition method based on virtual derivative strucure is characterized in that: may further comprise the steps: at first, set up by finite element software and to treat the not finite element model under the faulted condition of geodesic structure (being called again source structure); Secondly, measure former rank mode (being characteristic frequency and the corresponding vibration shape) data that obtain the source structure vibration by the mode test macro, the rank number of mode that needs to measure considers definite according to the complexity of structure, precision and the test site condition of surveying instrument; Then, a series of virtual derivative strucure and calculate corresponding characteristic frequency parameter take source structure as base configuration; At last, the characteristic frequency of comprehensive source structure and all virtual derivative strucures by hybrid frequency sensitivity diagnostic routine, draws the source structure damage recognition result that comprises damage position and degree;
Described mode test macro comprises a data acquisition instrument, a plurality of wireless senser and a cover mode analysis software, is measured former rank characteristic frequency and the corresponding Data of Mode that obtains the source structure vibration by the mode test macro; Wherein wireless senser is arranged in the position for the treatment of to occur easily in the geodesic structure damage, the quantity of wireless senser
Can be by formula
Determine, wherein
Be the sum of unit in the finite element model,
Number for the characteristic frequency measured.
2. a kind of damnification recognition method based on virtual derivative strucure as claimed in claim 1, it is characterized in that: described former rank modal data refers to modal data between front 4 ~ 10 rank.
3. a kind of damnification recognition method based on virtual derivative strucure as claimed in claim 1 or 2, it is characterized in that: described virtual derivative strucure can obtain by the way of virtual arrangement quality on source structure or rigidity, the position of virtual mass or rigidity is the position at wireless senser place, can arrange separately also and can make up layout, the size of virtual mass or rigidity generally be taken as source structure not under the faulted condition in the finite element model mass matrix or stiffness matrix corresponding to 10% ~ 15% of sensing station place numerical value; Adopt different virtual arrangement schemes just can obtain a series of virtual derivative strucure, the sum of the virtual derivative strucure that can construct
Quantity with sensor
Between the pass be
After virtual derivative strucure is constructed, adopt again the fundamental frequency sensitivity formula to calculate the former rank characteristic frequency parameter that obtains virtual derivative strucure.
4. a kind of damnification recognition method based on virtual derivative strucure as claimed in claim 1 or 2, it is characterized in that: described Mixed Sensitivity diagnostic routine, may further comprise the steps: at first, according to source structure and the virtual derivative strucure finite element model under the faulted condition not, calculate respectively source structure and virtual derivative strucure under the faulted condition not before
Rank characteristic frequency and corresponding fundamental frequency sensitivity; Then before will measuring the source structure of gained
Before rank characteristic frequency and each the virtual derivative strucure
The rank characteristic frequency combines, and lists the one order equation of damage front and back frequency variation, solves all unknown impairment parameter by generalizde inverse
The impairment parameter output that to calculate gained by forms such as histograms at last can accurately identify damage position and the degree of source structure.
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| CN105424797A (en) * | 2015-11-05 | 2016-03-23 | 北京航空航天大学 | Device and method for performing modal testing on inflatable flexible film structure based on hammering excitation method |
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| CN109187769B (en) * | 2018-07-27 | 2021-02-12 | 南京航空航天大学 | Method for quantitatively detecting pipeline defects based on ultrasonic guided waves |
| CN111178703A (en) * | 2019-12-17 | 2020-05-19 | 国网江西省电力有限公司电力科学研究院 | Elastic modulus sensitivity analysis method and system for power transmission tower-platform system |
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| CN113297773A (en) * | 2021-06-08 | 2021-08-24 | 中山大学 | Uncertainty quantitative analysis method and device for structural damage identification |
| CN113297773B (en) * | 2021-06-08 | 2023-01-24 | 中山大学 | Uncertainty quantitative analysis method and device for structural damage identification |
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