CN108226399B - A kind of beam-string structure damage combined recognising method based on modal parameter - Google Patents
A kind of beam-string structure damage combined recognising method based on modal parameter Download PDFInfo
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Abstract
A kind of beam-string structure damage combined recognising method based on modal parameter, this method acquires the acceleration signal being arranged on beam-string structure first, and before being damaged respectively, the displacement modes of intrinsic frequency and structural damage front and back top truss portion afterwards, then before supportting partial injury to rope, intrinsic frequency afterwards seeks first five rank normalized frequency change rate index, draw frequency-position curve, establish frequency fingerprint library, then the frequency fingerprint parameter in the case of actual damage is calculated, it is positioned on respective frequencies fingerprint curves, it finds out the corresponding damage position of each order frequency fingerprint and is screened, then before being damaged to truss portion, camber mode afterwards seeks first three rank camber mode poor index respectively, finally according to camber mode poor index, draw first three rank curvature mode difference-position curve, find out curve mutated site, as damage Position, and mutation is bigger, degree of injury is bigger.The present invention not only can effectively carry out the damage reason location of single injury, poly-injury operating condition to beam-string structure, and can relatively accurately identification of damage degree.
Description
Technical field:
The present invention relates to large span steel structure damage recognition and diagnosis technical fields, are based on modal parameter more particularly to one kind
Beam-string structure damage combined recognising method.
Background technique:
Large span steel structure is the one of the important signs that for measuring a national building technology level.Large span steel structure is because of its form
It graceful, the advantages that economical rationality and span ability are strong, is developed rapidly in China.Wherein, tension string beam structure is by upper
A kind of space hybrid structure form that portion's rigid arch truss and lower flexible drag-line are composed by strut, in Harbin sport
Conference and exhibition center, Guangzhou International Exhibition, Shenzhen Convention And Exhibition, Shanghai World's Fair theme shop, National Indoor Stadium etc. are multinomial great
It succeeds in engineering application, becomes one of one kind form across prestressed steel structure greatly that China is most widely used.
The general scale of large span steel structure is big, service phase limit for length, but often in low-temp. low-voltage power, generating collision and corrosion
Under the collective effect of equal loads and environment, there is different degrees of local damage, it is difficult to the naked eye differentiate, therefore will often make
Obtaining damaged member cannot handle and reinforce in time.Damage persistently can generate shadow to the normal use of structure in this case
It rings, serious or even initiation continuous collapse generates biggish Socie-economic loss.
Damage recognition and diagnosis is the effective means for realizing large scale structure life cycle management design and maintenance.For different knots
Configuration formula and architectural characteristic carry out damage diagnosis to existing structure, can provide strong support, have for the maintenance and reinforcement of existing structure
There is extremely important practical engineering value.
In traditional damnification recognition method, non-destructive tests, but single damage are often carried out to structure using single method
Hurt recognition methods and tend not to the non-destructive tests for meeting each position of structure, particularly for large-span space structure, every kind of method is all
Having some limitations property, so that the precision to non-destructive tests has an impact,
Such as: although the damnification recognition method acquisition frequency accuracy based on intrinsic frequency is higher, damage can not be carried out more
Wound is accurately positioned, affected by noise big.
Damnification recognition method based on camber mode and flexibility matrix, although poly-injury positioning and qualitative can be carried out
Judgement damage degree of injury, but Data of Mode obtain precision it is not high, and calculate it is relative complex, and needed in Practical Project compared with
Multisensor could obtain accurate modal data.
Damnification recognition method based on strain mode, is the first derivative being displaced due to straining, and the damage of strain mode is known
Other effect is also superior to displacement modes.But in practical applications, the measurement accuracy of strain mode is the key that non-destructive tests, is led to
Normal strain measurement method precision is not high, and discreteness is big, when damage occurs at the node of strain mode, the change of strain mode
Change it is unobvious, whether can not just differentiating structural damage.
Damnification recognition method based on stiffness matrix, it is similar to flexibility matrix method, it can not only identify the position of damage
It sets, and can be compared with accurate judgement degree of injury, but the premise of the method is each member to damage element stiffness matrix
Element is changed by same ratio, and this hypothesis can not strictly be set up sometimes, carry out non-destructive tests and positioning with stiffness matrix method
Effect have certain deviation.Also, only when degree of injury is larger, stiffness matrix can just occur significantly to change, by
Apparently the method is not suitable for small Damage Assessment Method for this.
Damnification recognition method based on frequency response function avoids mould due to not needing to carry out modeling analysis to structure
State analyzes brought error, but due to equipment test error and Environmental Noise Influence etc., this method damages lesser structure
Wound identification is not very sensitive.
Damnification recognition method based on wavelet analysis, the quality for collecting signal directly influence the effect of non-destructive tests, because
This wavelet analysis suffers from strict requirements to number of sensors and the optimum layout and signal collection.
Using environmental vibration testing, modal parameters are obtained, and then carry out the non-destructive tests based on modal parameter, in bridge
It is had been demonstrated in girder construction and Multistory-tall building effectively, therefore, the non-destructive tests based on modal parameter are that large span steel structure is realized
The ideal method of earlier damage diagnosis.
Large span steel structure is larger, rod piece is various, and especially there are drag-line, strut and purlins in prestressing force beam string structure structure
The different types rod piece such as frame, force-mechanism is more complicated, non-destructive tests and conventional bridge type structure or multi-rise building structure
There are notable differences.For this purpose, being directed to tension string beam structure feature, research is respectively suitable for lower cable support body system and top girder system
Signatures for damage detection, propose the damage combined recognising method based on modal parameter, carry out tension string beam structure different type damage
Hurt the non-destructive tests test under operating condition, provides theoretical method and technology for the damage diagnosis and performance maintenance of in-service tension string beam structure
Support.
Summary of the invention:
The technical problem to be solved by the present invention is to providing a kind of not only effectively can carry out single injury, more to beam-string structure
The damage reason location of damage regime, and can relatively accurately identification of damage degree the beam-string structure damage group based on modal parameter
Close recognition methods.
The technical solution of the invention is as follows, provides a kind of beam-string structure damage combination identification side based on modal parameter
Method, method includes the following steps:
The acceleration letter for the acceleration transducer that step 1. is arranged on beam-string structure by the acquisition of dynamic signal acquisition instrument
Number, obtain intrinsic frequency and structural damage that beam-string structure damages forward and backward drag-line and strut part respectively by mould measurement
The displacement modes of front and back top truss portion；
Step 2. intrinsic frequency forward and backward to beam-string structure rope support partial injury asks first five rank normalized frequency change rate to refer to
Mark, draws frequency-position curve, establishes frequency fingerprint library；
Step 3. calculates the frequency fingerprint parameter in the case of actual damage according to field measurement data, in corresponding frequency
It is positioned, find out the corresponding damage position of each order frequency fingerprint and is screened, institute in each recognition result on fingerprint curves
It is final required damage position comprising shared damage information；
Step 4. damages forward and backward camber mode to beam-string structure truss portion and first three rank curvature mode difference is asked to refer to respectively
Mark；
Step 5. draws first three rank curvature mode difference-position curve according to camber mode poor index, finds out curve mutation position
It sets, as damage position, and mutation is bigger, degree of injury is bigger, can qualitatively judge member bar injury degree.
Preferably, in the step 1, acceleration transducer test point location arrangements phase before and after beam-string structure damage
Together, the rank number of mode for testing acquisition is no less than five ranks.
Preferably, the step 2 specifically refers to,
1. obtaining frequency change rate FFC according to the intrinsic frequency of each rank before and after the damage measured in step 1i,
Wherein, fuiAnd fdiRespectively frequency of the beam-string structure under health and faulted condition；
2. frequency change rate and damage position and degree of injury are related, FFCiIt can be expressed as:
FFCi=gi(r)fi(ΔK,ΔM)
Wherein, Δ K and Δ M is respectively to damage front-end geometry stiffness change amount and quality knots modification, giIt (r) is position letter
Number；
3. frequency is changed function fiMake series expansion on Δ K=0 and Δ M=0 and ignore higher order term, simplification can obtain:
FFCi=Δ Kqi(r)+ΔMpi(r)
4. it is approximately considered mass conservation Δ M ≈ 0, therefore normalized frequency change rate NFCRiIt can indicate are as follows:
5. according to the NFCR that rope support damage obtains under each operating conditioniData target draws structure frequency-position curve, establishes
Frequency fingerprint library.
Preferably, the step 4 specifically refers to,
1. acquiring the camber mode before and after structural damage using difference method according to the displacement modes parameter of in-site measurement
φ"i:
Wherein, i is i-th of measuring point；L is the distance between two adjacent measuring points.
2. rank camber mode each after damage is subtracted each other with each rank camber mode value before corresponding damage, it is exhausted to obtain curvature mode difference
To value D φ ":
D φ "=| φ "o-φ"d|
Wherein, φ "oTo damage pre-structure camber mode；φ"dFor structural curvature mode after damage.
The beneficial effects of the present invention are:
Single signatures for damage detection is more difficult to carry out the comprehensive Study on Damage Identification of tension string beam structure.As typically greatly across
Space structure system, tension string beam structure contain prestressed cable, vertical strut and top truss three parts, each section pair
It is different in the influencing mechanism of structural dynamic characteristic index, it is difficult to comprehensively to be damaged using a kind of unified theory or method
Identification；
Truss-string-structure is relative complex, and rod piece is various, it may occur however that the position of damage is more, damages and knows in practice
When other method can not one-time detection go out the health degree of structure everywhere.It is therefore proposed that the damage for truss-string-structure is combined
Recognition methods carries out non-destructive tests to structure different parts using different signatures for damage detection.
Under the premise of herein, by the sensibility of truss-string-structure unit, by top truss portion and lowermost strut drag-line portion
It is divided into two parts of truss-string-structure, carries out diagnosing structural damage with different damnification recognition methods respectively.
A kind of beam-string structure damage combined recognising method based on modal parameter of the present invention is referred to based on structural damage front and back
The relationship of the opposite variation of target, proposes the calculation method of prestressing force beam string structure non-destructive tests, this method can be effectively to pre-
Stress beam-string structure carries out the damage reason location of single injury, poly-injury operating condition, and more accurate identification of damage degree, is prestressing force
Beam-string structure non-destructive testing and assessment provide a kind of effective new method.
Detailed description of the invention:
Fig. 1 is the flow diagram that a kind of beam-string structure based on modal parameter of the present invention damages combined recognising method；
Fig. 2 is single Pin truss string structure simplified model dimensional drawing of the embodiment of the present invention；
Fig. 3 (a) is that each operating condition single order normalized frequency becomes in the strut drag-line unit frequency fingerprint base of the embodiment of the present invention
Rate schematic diagram；
Fig. 3 (b) is that each operating condition second order normalized frequency becomes in the strut drag-line unit frequency fingerprint base of the embodiment of the present invention
Rate schematic diagram；
Fig. 3 (c) is that each three rank normalized frequency of operating condition becomes in the strut drag-line unit frequency fingerprint base of the embodiment of the present invention
Rate schematic diagram；
Fig. 4 (a) is that the single order curvature mode difference curve in operating condition of embodiment of the present invention N13 curvature mode difference tracing analysis shows
It is intended to；
Fig. 4 (b) is the preceding second order curvature mode difference curve in operating condition of embodiment of the present invention N13 curvature mode difference tracing analysis
Contrast schematic diagram；
Fig. 4 (c) is first three rank curvature mode difference curve in operating condition of embodiment of the present invention N13 curvature mode difference tracing analysis
Contrast schematic diagram；
Fig. 5 (a) is that the single order curvature mode difference curve in operating condition of embodiment of the present invention N14 curvature mode difference tracing analysis shows
It is intended to；
Fig. 5 (b) is the preceding second order curvature mode difference curve in operating condition of embodiment of the present invention N14 curvature mode difference tracing analysis
Contrast schematic diagram；
Fig. 5 (c) is first three rank curvature mode difference curve in operating condition of embodiment of the present invention N14 curvature mode difference tracing analysis
Contrast schematic diagram；
Fig. 6 (a) is that operating condition N13 is bent in the analysis of operating condition of the embodiment of the present invention N13, N15, N16 curvature mode difference curve comparison
Rate mode difference curve synoptic diagram；
Fig. 6 (b) be operating condition of the embodiment of the present invention N13, N15, N16 curvature mode difference curve comparison analysis in operating condition N13,
N15 curvature mode difference curve synoptic diagram；
Fig. 6 (c) be operating condition of the embodiment of the present invention N13, N15, N16 curvature mode difference curve comparison analysis in operating condition N13,
N15, N16 curvature mode difference curve synoptic diagram；
Fig. 7 (a) is the operating condition N17 curvature modulus value schematic diagram in operating condition of embodiment of the present invention N17 Curvature Modal Analysis；
Fig. 7 (b) is that the operating condition N17 curvature mould differential in operating condition of embodiment of the present invention N17 Curvature Modal Analysis is intended to；
Fig. 8 (a) is the operating condition N18 curvature modulus value schematic diagram in operating condition of embodiment of the present invention N17 Curvature Modal Analysis；
Fig. 8 (b) is that the operating condition N18 curvature mould differential in operating condition of embodiment of the present invention N17 Curvature Modal Analysis is intended to；
Fig. 9 is weight poly-injury curvature mode difference comparative analysis schematic diagram of the embodiment of the present invention；
Figure 10 (a) is the single order camber mode value contrast schematic diagram of operating condition of embodiment of the present invention N19；
Figure 10 (b) is the second order curvature mode value contrast schematic diagram of operating condition of embodiment of the present invention N19；
Figure 10 (c) is the three rank camber mode value contrast schematic diagrams of operating condition of embodiment of the present invention N19；
Figure 11 (a) is that rope of the embodiment of the present invention supports the signal of unit operating condition N20 single order normalized frequency change rate recognition effect
Figure；
Figure 11 (b) is that rope of the embodiment of the present invention supports the signal of unit operating condition N20 second order normalized frequency change rate recognition effect
Figure；
Figure 11 (c) is that rope of the embodiment of the present invention supports the signal of tri- rank normalized frequency change rate recognition effect of unit operating condition N20
Figure；
Figure 12 is operating condition of embodiment of the present invention N20 curvature mode difference curve synoptic diagram.
Specific embodiment:
The beam-string structure damage combination based on modal parameter a kind of to the present invention is known in the following with reference to the drawings and specific embodiments
Other method is described further:
As shown in Figure 1, the present invention it is a kind of based on modal parameter beam-string structure damage combined recognising method mainly include with
Lower step:
The acceleration letter for the acceleration transducer that step 1. is arranged on beam-string structure by the acquisition of dynamic signal acquisition instrument
Number, obtain intrinsic frequency and structural damage that beam-string structure damages forward and backward drag-line and strut part respectively by mould measurement
The displacement modes of front and back top truss portion；
Step 2. intrinsic frequency forward and backward to beam-string structure rope support partial injury asks first five rank normalized frequency change rate to refer to
Mark, draws frequency-position curve, establishes frequency fingerprint library；
Step 3. calculates the frequency fingerprint parameter in the case of actual damage according to field measurement data, in corresponding frequency
It is positioned, find out the corresponding damage position of each order frequency fingerprint and is screened, institute in each recognition result on fingerprint curves
It is final required damage position comprising shared damage information；
Step 4. damages forward and backward camber mode to beam-string structure truss portion and first three rank curvature mode difference is asked to refer to respectively
Mark；
Step 5. draws first three rank curvature mode difference-position curve according to camber mode poor index, finds out curve mutation position
It sets, as damage position, and mutation is bigger, degree of injury is bigger, can qualitatively judge member bar injury degree.
Specifically, arranging corresponding acceleration transducer according to the shape size of structure, and damage front and back in step 1
Point position arrangement is identical.
Specifically, the rank number of mode for testing acquisition is no less than five ranks in step 1.
Specifically, modal parameters test measures each rank in structural damage front and back using the method that can survey excitation in step 1
Intrinsic frequency fiAnd the displacement modes φ of each bar element nodei。
Specifically, obtaining frequency change rate according to the intrinsic frequency of each rank before and after the damage measured in step 1 in step 2
FFCi:
Wherein, fuiAnd fdiRespectively frequency of the structure under health and faulted condition.
Specifically, frequency change rate and damage position and degree of injury are related in step 2, can be expressed as:
FFCi=gi(r)fi(ΔK,ΔM)
Wherein, Δ K and Δ M is respectively to damage front-end geometry stiffness change amount and quality knots modification, giIt (r) is position letter
Number.
Specifically, frequency is changed function f in step 2iMake series expansion on Δ K=0 and Δ M=0 and ignores high-order
, simplification can obtain:
FFCi=Δ Kqi(r)+ΔMpi(r)
Further, in step 2, it is approximately considered mass conservation Δ M ≈ 0, therefore normalized frequency change rate NFCRiIt can indicate
Are as follows:
It can be seen that by above formula, normalized frequency change rate is only related with damage position, unrelated with degree of injury.
Further, in step 2, according to the NFCR that rope support damage obtains under each operating conditioniData target draws structure frequency-
Position curve establishes frequency fingerprint library.
Specifically, bring step 2 into according to field measurement data in step 3, calculates the frequency in the case of actual damage and refer to
Line parameter.
Further, it in step 3, is positioned on the frequency fingerprint curve established in step 2, finds out each order frequency fingerprint
Corresponding damage position is simultaneously screened, and the damage information shared included in each recognition result is final required damage
Position.
Specifically, in step 4, according to the displacement modes parameter of in-site measurement, before acquiring structural damage using difference method
Camber mode φ " afterwardsi:
Wherein, i is i-th of measuring point；L is the distance between two adjacent measuring points.
Further, in step 4, rank camber mode each after damage is subtracted each other with each rank camber mode value before corresponding damage, is obtained
To curvature mode difference absolute value D φ ":
D φ "=| φ "o-φ″d|
Wherein, φ "oTo damage pre-structure camber mode；φ″dFor structural curvature mode after damage.
Specifically, bringing step 4 into according to field measurement data in step 5, first three rank in the case of actual damage is calculated
Curvature mode difference D φ ", and be depicted as curve.
Further, in step 5, each rank curvature mode difference curve in the case of top truss structure partial injury is observed, is found out
The peak position of the mutation of curve, as STRUCTURE DAMAGE LOCATION, and mutation is bigger, degree of injury is bigger, can qualitatively judge bar
Part degree of injury.
It below will be using certain railway station ceiling structure model as the preferred embodiment of the present invention, to a kind of base of the present invention
It is illustrated in further detail in the beam-string structure damage combined recognising method of modal parameter.
As shown in Fig. 2, obtaining truss-string-structure Numerical-Mode by reduced scale simplification according to certain railway station ceiling structure model
Analog model, the model only retain the representative top rigid truss of truss-string-structure, intermediate rigid support rod piece and
Lower flexible drag-line component forms single Pin tension string beam structure simplified model as shown in the figure.The span of model is 6m, and wind up truss
Structure uses inverted triangle space truss, is made of between every two node quadrangular pyramid basic unit, width 0.25m, model knot
Structure rise is 0.4m, sag 0.4m.5 struts are evenly arranged in the middle part of structure, span centre strut height is 0.65m, remaining strut
For size as schemed, lower edge is the drag-line of near parabolic type.In analysis, one end support is set as hinged-support, and the other end is set as sliding
Dynamic support is identical as support restraint form used by roof system across truss string structure greatly.Meanwhile model forms machine when to prevent analysis
Structure is provided with the support of freedom degree outside 6 constraint planes at the model place of winding up.
Using ANSYS finite element modeling, the model totally 96 key nodes constrain tri- direction positions of X, Y, Z in node A
It moves, simulates fixed-hinged support, the displacement of X, Z both direction is constrained at node B, simulates sliding support.Analysis model is list Pin knot
Structure, therefore in support and wind up and apply flat out of plane constraint everywhere.Using the upper and lower chord member of BEAM4 unit simulation, truss web,
Using the drag-line below LINK10 unit simulation, centre is evenly arranged 5 struts, using LINK8 unit simulation.Using MASS21
Simulate top boom node unit quality.Rod piece is round steel pipe in structure structure, and size is shown in Table 1.
Table 1: structure main member section specification table
In model analysis, steel are unyielding, therefore only consider this structure of steel elastic stage, and the elastic modulus Es of steel=
2.06 × 1011Pa, density 7900kg/m3.Model load is roof load of the original structure in serviceability limit stage, mode
Node quality, the prestressing force that lower section Suo Li is applied to 2KN using initial strain mode is applied are equivalent to when analysis.
One, rope supports part non-destructive tests
For the frequency fingerprint library for establishing truss string strut drag-line part, the present embodiment is quasi- to count truss-string-structure
Value simulation, the rigidity at strut drag-line reduce to simulate degree of impairment, due to the damage based on intrinsic frequency introduced before this
It is unrelated with degree of injury, and only related to damage position for hurting distinguishing indexes, therefore by each list of strut when establishing frequency fingerprint library
Member changes into Φ 20 × 2 by Φ 32 × 2.5 to simulate damage, and drag-line unit is substituted for 4 wirerope of Φ by 8 wirerope of Φ.
In the intrinsic frequency of structure, the energy that lower mode vibrates total is contributed more, and it is in practical work
Difficulty is measured in journey and error is also lower compared with high order mode, so in non-destructive tests analytic process, it is only necessary to consider structure
Lower mode establishes corresponding frequency fingerprint library.The present embodiment has chosen first three rank intrinsic frequency of structure as research
Object, analytical calculation obtains structural natural frequencies under various operating conditions and every frequency fingerprint identified amount is as shown in table 2.
The fingerprint curves of canonical frequency change rate (are drawn in operating condition N2~N6 (strut unit fingerprint base) and operating condition N7~N12
Cable elements fingerprint base) present symmetry be consistent this is because beam-string structure model inherently has symmetry with actual conditions,
Symmetrical operating condition canonical frequency change rate signatures for damage detection curve is removed with good monotonicity, is conducive to non-destructive tests, and
It is more sensitive to the change in location of structural damage.
2 strut drag-line component frequency fingerprint base of table
Remarks: FCR, NFCR are respectively Frequency scaling algorithm and normalized frequency change rate in table
By normalized frequency change rate index calculate obtain rope support system frequency fingerprint library, Fig. 3 (a), Fig. 3 (b) and
Fig. 3 (c) is this it appears that single order normalized frequency change rate, second order normalized frequency change rate, three rank normalized frequencies become
Rate shows stronger symmetry on 6 units of the 5 of strut units and drag-line, this also with symmetrical configuration phase
Symbol, later period by obtaining first three order frequency of actual damage structure, calculate single order normalized frequency change rate, second order regularization frequency
Rate change rate, three rank normalized frequency change rates determine STRUCTURE DAMAGE LOCATION to compare with the operating condition in fingerprint base.
Two, truss portion non-destructive tests
(1) single injury performance analysis
Single injury situation considers that truss structure part in top is analyzed, and considers different operating condition non-destructive tests effects, considers
Influence of the preceding difference order modal data to non-destructive tests effect, considers the non-destructive tests effect under same position Injured level
Fruit.
Curvature mode difference index analysis:
As shown in Figure 4, operating condition N13 is that position occurs for simulation damage between node 7,8, from Fig. 4 (a) it is found that before
The camber mode difference maximum value that first-order modal data are calculated in 8 position of node, and 11 camber mode difference of node also compared with
Greatly, therefore only carry out that the non-destructive tests effect based on curvature mode difference is general, and there are distracters, i.e., bent with preceding single order modal data
Line micromutation.
Fig. 4 (b) and Fig. 4 (c) is to compare to carry out the damage based on curvature mode difference with preceding second order, first three rank modal data
Hurt recognition effect, it can be clearly seen that Fig. 4 (b) and Fig. 4 (c) combines first three rank modal data to carry out non-destructive tests effect most
Good, peak of curve appears in node 7,8 and is more and more obvious, and curve other positions are got up more gentle relatively.It therefore, can be obvious
Identify that position occurs for damage.
Conclude that (1) curvature mode difference signatures for damage detection has preferably truss-string-structure from the above analysis
Recognition effect；(2) general with first-order modal parameter progress non-destructive tests effect, damage knowledge is carried out with first three rank modal parameter
There is not preferable effect；
As shown in Fig. 5 (a), Fig. 5 (b) and Fig. 5 (c), operating condition N14 is that top truss structure lower edge rod bearing nearby damages
Hurt (between node 2,3), from curve it can be seen that peak-peak is strictly to occur at node 2,3.But the damage of operating condition N14
Recognition effect not as good as operating condition N13 it is obvious because there are two larger peak values, will affect the preliminary judgement of non-destructive tests, this with
Structural model and rod piece position are related, and lower boom stress condition is complicated, and stress is larger, therefore non-destructive tests effect is general.
Fig. 6 (a), Fig. 6 (b) and Fig. 6 (c) have carried out same position and the non-destructive tests damaged in various degree analysis (the occur
Three first order mode data), from Fig. 4 (a) it can be seen that curve is obviously mutated at node 7,8, can see from Fig. 4 (c)
Injured level camber mode difference curve mutation content is different, and damage more macromutation degree is higher, therefore can be according to song
The qualitative judgement of line mutation content size progress degree of injury.
(2) poly-injury performance analysis
Curvature mode difference index analysis
Fig. 7 (a), Fig. 7 (b), Fig. 8 (a) and Fig. 8 (b) are the damage of curvature mode difference in the case of operating condition N17, N18 respectively
Recognition effect, simulation damage position are set between node 7,8 between node 10,11, it can be seen that camber mode difference two
A apparent peak point is just in the position that simulation damage occurs, and recognition effect is preferable, and Fig. 9 can also be seen that with damage
Increase, curve mutation content increases.
3, weld damage identifies
Due to that can not arrange that weld damage is in practical projects compared with multiple acceleration transducers in Practical Project around weld seam
Want to be accurately positioned more difficulty with damnification recognition method, the damage that can not carry out being accurate to weld seam region is known
Not.Weld damage identification is changed using weld seam elasticity modulus in the present embodiment carries out lesion mimic, and damage position defaults in No. 7 sections
Point left side, is reduced 50% for elasticity modulus, carries out weld damage identification with camber mode poor index.
As can be seen that weld seam stiffness injury 50% influences very camber mode value from Figure 10 (a), 10 (b) and 10 (c)
Small, for curve close to being overlapped, this is consistent with sensitivity analysis conclusion, and weld seam unit influences very little for structure Integral modes parameter.
4, drag-line chord member combines non-destructive tests
Operating condition N20 is to wind up bar unit and damage composite condition that drag-line unit damages simultaneously, utilizes the operating condition mould
State analysis first three order frequency of gained and first three order frequency of lossless operating condition calculate gained normalized frequency change rate index such as 3 institute of table
Show, operating condition N20 non-destructive tests figure such as Figure 11 (a), Figure 11 (b) and Figure 11 (c) are shown.
Table 3 is lossless, operating condition N20 first three order frequency
It can be to correspond to 9,10 institute of operating condition in comprehensive descision operating condition N20 and fingerprint base from Figure 11 (a), Figure 11 (b) and Figure 11 (c)
It is closest to obtain normalized frequency change rate index, therefore may determine that drag-line middle cell damages, recognition effect is preferable.
Using first three order frequency of gained and Data of Mode in operating condition N20, corresponding curvature mode difference can be calculated, curve is passed through
The judgement that mutated site carries out damage position can schemed as shown in figure 12, find out that curve occurs in node 7,8 positions in 12
Obvious mutation is damaged to judge that bar element damages between top boom 7,8 nodes, presets damage position with operating condition and is consistent
It is preferable to hurt recognition effect.
Embodiment described above is only that the preferred embodiment of the present invention is described, not to the scope of the present invention
It is defined, without departing from the spirit of the design of the present invention, those of ordinary skill in the art are to technical solution of the present invention
The various changes and improvements made should all be fallen into the protection scope that claims of the present invention determines.
Claims (4)
1. a kind of beam-string structure based on modal parameter damages combined recognising method, it is characterised in that: this method includes following step
It is rapid:
The acceleration signal for the acceleration transducer that step 1. is arranged on beam-string structure by the acquisition of dynamic signal acquisition instrument, leads to
It crosses mould measurement and obtains intrinsic frequency and structural damage front and back that beam-string structure damages forward and backward drag-line and strut part respectively
The displacement modes of top truss portion；
Step 2. intrinsic frequency forward and backward to beam-string structure rope support partial injury seeks first five rank normalized frequency change rate index,
Frequency-position curve is drawn, frequency fingerprint library is established；
Step 3. calculates the frequency fingerprint parameter in the case of actual damage according to field measurement data, in corresponding frequency fingerprint
It is positioned, find out the corresponding damage position of each order frequency fingerprint and is screened on curve, included in each recognition result
Shared damage information is final required damage position；
Step 4. damages forward and backward camber mode to beam-string structure truss portion and seeks first three rank camber mode poor index respectively；
Step 5. draws first three rank curvature mode difference-position curve, finds out curve mutated site according to camber mode poor index,
As damage position, and mutation is bigger, degree of injury is bigger, can qualitatively judge member bar injury degree.
2. a kind of beam-string structure based on modal parameter according to claim 1 damages combined recognising method, feature exists
In: in the step 1, acceleration transducer test point location arrangements before and after beam-string structure damage are identical, and test obtains
Rank number of mode be no less than five ranks.
3. a kind of beam-string structure based on modal parameter according to claim 1 damages combined recognising method, feature exists
In: the step 2 specifically refers to,
1. obtaining frequency change rate FFC according to the intrinsic frequency of each rank before and after the damage measured in step 1i,
Wherein, fuiAnd fdiRespectively frequency of the beam-string structure under health and faulted condition；
2. frequency change rate and damage position and degree of injury are related, FFCiIt can be expressed as:
FFCi=gi(r)fi(ΔK,ΔM)
Wherein, Δ K and Δ M is respectively to damage front-end geometry stiffness change amount and quality knots modification, giIt (r) is position function；
3. frequency is changed function fiMake series expansion on Δ K=0 and Δ M=0 and ignore higher order term, simplification can obtain:
FFCi=Δ Kqi(r)+ΔMpi(r)
4. it is approximately considered mass conservation Δ M ≈ 0, therefore normalized frequency change rate NFCRiIt can indicate are as follows:
5. according to the NFCR that rope support damage obtains under each operating conditioniData target draws structure frequency-position curve, establishes frequency and refers to
Line library.
4. a kind of beam-string structure based on modal parameter according to claim 1 damages combined recognising method, feature exists
In: the step 4 specifically refers to,
1. acquiring the camber mode φ " before and after structural damage using difference method according to the displacement modes parameter of in-site measurementi:
Wherein, i is i-th of measuring point；L is the distance between two adjacent measuring points,
2. rank camber mode each after damage is subtracted each other with each rank camber mode value before corresponding damage, curvature mode difference absolute value is obtained
D φ ":
D φ "=| φ "o-φ”d|
Wherein, φ "oTo damage pre-structure camber mode；φ″dFor structural curvature mode after damage.
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