CN107357992B - Composite structure correction method for finite element model based on cluster analysis - Google Patents

Composite structure correction method for finite element model based on cluster analysis Download PDF

Info

Publication number
CN107357992B
CN107357992B CN201710568512.1A CN201710568512A CN107357992B CN 107357992 B CN107357992 B CN 107357992B CN 201710568512 A CN201710568512 A CN 201710568512A CN 107357992 B CN107357992 B CN 107357992B
Authority
CN
China
Prior art keywords
mrow
parameter
msub
analysis
composite structure
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201710568512.1A
Other languages
Chinese (zh)
Other versions
CN107357992A (en
Inventor
费庆国
曹芝腑
姜东�
刘璟泽
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Southeast University
Original Assignee
Southeast University
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Southeast University filed Critical Southeast University
Priority to CN201710568512.1A priority Critical patent/CN107357992B/en
Publication of CN107357992A publication Critical patent/CN107357992A/en
Application granted granted Critical
Publication of CN107357992B publication Critical patent/CN107357992B/en
Priority to PCT/CN2018/083368 priority patent/WO2019011026A1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/17—Mechanical parametric or variational design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/26—Composites

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Theoretical Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Evolutionary Computation (AREA)
  • General Engineering & Computer Science (AREA)
  • Computer Hardware Design (AREA)
  • Computational Mathematics (AREA)
  • Mathematical Analysis (AREA)
  • Mathematical Optimization (AREA)
  • Pure & Applied Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Management, Administration, Business Operations System, And Electronic Commerce (AREA)

Abstract

The invention provides a kind of composite structure correction method for finite element model based on cluster analysis, establish initial finite element analysis model, measure the experimental modal frequency and Mode Shape of structure, calculate the relative sensitivity matrix of parameter to be modified, corrected parameter, which is treated, using hierarchical clustering algorithm carries out parameter packet, Relative sensitivity analysis is carried out to clustering parameter again, the clustering parameter that relative sensitivity average value is maximum in each parameter is selected to be modified, the modal frequency of structural analysis model and the residual vector of actual measurement modal frequency, establish the object function needed for analysis model amendment, the optimization indirect problem of structure object function is modified to the FEM model of composite structure.The present invention combines numerical simulation, experiment and optimisation technique, cluster analysis is carried out using the relative sensitivity matrix of parameter, reduce number of parameters to be modified, revision program stability is improved, a kind of composite Equivalent finite element model parameter correction method being accurately combined based on numerical simulation, experiment and optimization is provided for engineer applied.

Description

Composite structure correction method for finite element model based on cluster analysis
Technical field
The present invention relates to a kind of composite structure, and in particular to a kind of composite structure FEM updating side Method.
Background technology
Composite structure has the excellent properties such as high specific strength, high specific stiffness, endurance, is widely used in aviation boat My god, automobile and shipping industry.But simultaneously because its material component is various, complex manufacturing technology, composite structure carefully sees material Parameter is different.During structural analysis and design, if using the thin sight analysis model of composite structure, will significantly it increase Add modeling difficulty, and the time cost of Design Stage.Therefore the finite element analysis model of composite structure is established simultaneously Modifying model is carried out to it, the accuracy tool for improving composite structure analysis is of great significance.
Composite structure FEM model generally use orthotropic material, to multilayer materials structure Speech, the quantity of its parameter to be modified will be far more than experimental data, so as to produce the ill-conditioning problem in makeover process.How non-complete In the case of standby measured data, while reducing parameter in makeover process, the composite structure for obtaining precise and high efficiency is limited Element analysis model, it has also become Practical Project problem urgently to be resolved hurrily.
The content of the invention
Goal of the invention：In view of the above-mentioned deficiencies in the prior art, it is an object of the present invention to provide a kind of answering based on cluster analysis Condensation material structural finite element model updating method, cluster point is carried out to parameter using the relative sensitivity matrix of parameter to be modified Analysis, by incomplete experimental data, the method that parameters revision is carried out to the equivalent COMPOSITE FINITE ELEMENT model of multi-parameter, carry High parameters revision precision and efficiency.
Technical scheme：The invention provides a kind of composite structure FEM updating side based on cluster analysis Method, comprise the following steps：
(1) formed according to composite structure geometric properties and component, using orthotropic material relationships to reality Border composite structure is modeled, and simplifies details component, only considers macroscopical configuration of composite structure, establish it is equivalent just Beginning finite element analysis model；
(2) according to the actual geometric parameter of composite structure, experimental model is established, using dynamics modal experimental technique, Measure the experimental modal frequency and Mode Shape of structure；
(3) the relative sensitivity matrix of parameter to be modified is calculated, corrected parameter is treated using hierarchical clustering algorithm and is joined Number packet, then Relative sensitivity analysis is carried out to clustering parameter, select the cluster that relative sensitivity average value is maximum in each parameter Parameter is modified；
(4) residual vector of the modal frequency of structural analysis model and actual measurement modal frequency, establishes analysis model amendment institute The object function needed, the optimization indirect problem for building object function are modified to the FEM model of composite structure.
Further, step (2) obtains experimental modal frequency and the process of Mode Shape comprises the following steps：
2.1) according to the geometric parameter of composite structure, its experimental model is established；
2.2) structure point layout, in structure boundary away from selection pick-up point at mode stationary point；
2.3) composite structure is hung with rubber rope, it is Z-direction to define perpendicular to the direction in suspension face, and Freedom-free state is at, acceleration transducer is fixed on to selected pick-up point；
2.4) power hammer and acceleration transducer are respectively connected to signal sampler；
2.5) the model analysis module of dynamic test system is utilized, model analysis parameter is set；
2.6) firmly hammer applies impulsive force to the impacting point in structure along Z-direction successively, gathers each measuring point successively and exists By output acceleration signal at input power during pulse excitation and pick-up point；
2.7) modal parameter amendment is carried out to input/output signal with the signal analyzer of pilot system, passes through each point frequency response Lump, fitting and the amendment of function obtain the actual measurement modal frequency and Mode Shape of composite structure.
Further, step (3) comprises the following steps：
3.1) according to relative sensitivity calculation formula, relative sensitivity square of the modal frequency relative to elastic parameter is calculated Battle array：
In formula, SrIt is relative sensitivity matrix, f is output modalities frequency vector, and p is elastic parameter vector to be modified；
3.2) relative sensitivity column vector g is calculatedα、gβDistance d：
Relative sensitivity is classified apart from close parameter using hierarchical clustering algorithm, so as to obtain elastic parameter Hierarchical tree is expressed, and recycles distance threshold 0.2 to carry out packet p={ p to elastic parameter as parameter packet standard1；p2；…； pj, n1,n2,…,njThe respectively number of each group parameter, and n1+n2+…+nj=N, N represent elastic parameter sum；
3.3) clustering parameter θ is definedjFor the relative change of jth group elastic parameter：
In formula, pjIt is vectorial for jth group elastic parameter,Represent jth group elastic parameter initial value, θjIt is corresponding for jth group bullet parameter Clustering parameter；
Using the Calculation of Sensitivity formula of clustering parameter, clustering parameter is chosen, determines clustering parameter to be modified：
In formula, ScThe sensitivity matrix of clustering parameter is represented, θ is clustering parameter vector, and the vectorial element is joined by cluster Number θjComposition.
Further, step (4) comprises the following steps：
4.1) to resulting composite structure experimental modal frequency, experimental modal is determined using modal assurance criterion MAC Each rank Analysis Mode frequency corresponding to the vibration shape, carry out Mode Shape matching：
In formula, M represents modal assurance criterion matrix, ΦaAnd ΦeAnalysis and the experimental modal vibration shape are represented respectively, are finally determined such as Under objective optimization function：
In formula, p is elastic parameter to be modified vector, and J (p) represents object function, and ε (p) is modal frequency faWith mode frequency Rate feResidual vector and ε (p)=f of constructione-fa(p), W ε=round (max (fe)·diag(fe)), represent according to experiment mould The weighting matrix that state frequency is worth to, round (), max () and diag () represent round, maximum respectively Computing and diagonal matrix computing；The physical meaning of the object function is：In the excursion [p of parameterl,pu] in, find and optimize Parameter causes two Norm minimums of experimental modal frequency and Analysis Mode frequency vector difference；
4.3) elasticity based on object function (12) the structure optimization indirect problem constructed to COMPOSITE FINITE ELEMENT model Parameter is modified, and obtains effective elastic parameter.
Beneficial effect：The invention provides carry out ginseng to be modified according to the relative sensitivity matrix of parameter based on cluster analysis The method that number packet is chosen, establishes the finite element initial analysis model and experimental model of composite panel, while pass through construction Modal frequency objective optimization function, the FEM model of equivalent composite harden structure is have modified, there is highly important engineering Application value.
The present invention combines numerical simulation, experiment and optimisation technique, can correct that the composite with multi-parameter is equivalent to be had The material parameter of meta-model is limited, considers that the material constitutive relation parameter selected by Equivalent finite element model is more, causes parameter to be repaiied The problem of just accuracy is relatively low, cluster analysis is carried out using the relative sensitivity matrix of parameter, number of parameters to be modified is reduced, carries High revision program stability, provide and a kind of accurately answered based on what numerical simulation, experiment and optimization were combined for engineer applied Condensation material Equivalent finite element model parameter correction method.
Brief description of the drawings
Fig. 1 is the equivalent composite harden structure in embodiment；
Fig. 2 is parameter relative sensitivity figure to be modified；
Fig. 3 is parameter hierarchical tree figure to be modified；
Fig. 4 is clustering parameter sensitivity analysis figure；
Fig. 5 is the flow chart of the inventive method.
Embodiment
Technical solution of the present invention is described in detail below, but protection scope of the present invention is not limited to the implementation Example.
Embodiment：A kind of composite structure correction method for finite element model based on cluster analysis, as shown in figure 5, tool Body process is as follows：
Step 1, composite harden structure is modeled using shell unit and solid element, obtains equivalent finite element mould Type, sandwich layer solid elements are represented as shown in figure 1, wherein 1 represents Shell Finite Element above, 2,3 represent following Shell Finite Elements, at the beginning of structure Beginning elastic parameter value is
Step 2, to obtaining structural experiment modal frequency and Mode Shape using dynamics modal experimental technique：
2.1) according to the geometric parameter of composite structure, its experimental model is established；
2.2) structure point layout, in structure boundary away from selection pick-up point at mode stationary point；
2.3) composite structure is hung with rubber rope, it is Z-direction to define perpendicular to the direction in suspension face, and It is at freedom-free state；Acceleration transducer is cohered and selected border pick-up opening position with glue；
2.4) power hammer and acceleration transducer are respectively connected to the corresponding interface of signal sampler with connecting line；
2.5) the model analysis module of dynamic test system is utilized, model analysis parameter is set；
2.6) firmly hammer applies impulsive force to the impacting point in structure along Z-direction successively, gathers each measuring point successively and exists By output acceleration signal at input power during pulse excitation and pick-up point；
2.7) modal parameter amendment is carried out to input/output signal with the signal analyzer of pilot system, passes through each point frequency response Lump, fitting and the amendment of function obtain the actual measurement modal frequency f of composite structureeWith Mode Shape Φe。
Step 3, treat corrected parameter using cluster analysis and carry out packet selection：
3.1) according to relative sensitivity calculation formula, relative sensitivity square of the modal frequency relative to elastic parameter is calculated Battle array, relative sensitivity Matrix Computation Formulas are as follows：
In formula, SrIt is relative sensitivity matrix, f is output modalities frequency vector, and p is that elastic parameter is vectorial, obtained bullet The relative sensitivity of property parameter is as shown in Figure 2；
3.2) cluster analysis, the elastic parameter relative sensitivity matrix obtained according to step 3.1, relative sensitivity row are calculated Vectorial gα, gβDistance d：
Relative sensitivity is classified apart from close parameter using hierarchical clustering algorithm, so as to obtain elastic parameter point Layer Dendrogram, as shown in figure 3, distance threshold 0.2 is recycled as parameter packet standard, as shown in phantom in Figure 2, to bullet Property parameter be grouped, from figure 3, it can be seen that packet situation it is as follows：P={ p1；p2；…；pj}={ { p1,p11}；{p2,p3}； {p4,p10}；{p5}；{p6,p9,p12}；{p7,p13}；{p8,p14,p15}；, n1=2, n2=2, n3=2, n4=1, n5=3, n6= 2,n7=3；
3.3) clustering parameter θ is definedjFor the relative change of jth group elastic parameter：
In formula, pjIt is vectorial for jth group elastic parameter,Represent jth group elastic parameter initial value, θjFor jth group elastic parameter pair The clustering parameter answered；Using the Calculation of Sensitivity formula of clustering parameter, clustering parameter is chosen, determines cluster to be modified Parameter：
In formula, ScThe sensitivity matrix of clustering parameter is represented, θ is clustering parameter vector, and the vectorial element is joined by cluster Number θjComposition；
According to relative sensitivity numerical values recited, the clustering parameter that relative sensitivity average value is maximum in each parameter is selected to carry out Amendment, the clustering parameter sensitivity finally given is as shown in figure 4, clustering parameter θ2And θ4Sensitirity va1ue obtain the order of magnitude compared to Other five clustering parameters are relatively low, therefore the band corrected parameter finally determined is reduced to 5 from 15, reduces in makeover process Pathosis.
Step 4, parameters revision is carried out to equivalent COMPOSITE FINITE ELEMENT model using optimization method：
4.1) the modal frequency f obtained according to finite element analysis modelaWith actual measurement modal frequency feConstruct residual vector ε (p) =fe-fa(p)；
4.2) objective optimization function is determined：The experimental modal frequency and Mode Shape obtained according to step 2, is put using mode Reliability MAC carries out Mode Shape matching, determines each rank Analysis Mode frequency corresponding to the experimental modal vibration shape,
In formula, M represents modal assurance criterion matrix, ΦaAnd ΦeAnalysis and the experimental modal vibration shape are represented respectively, are finally determined such as Under objective optimization function：
In formula, W=round (max (fe)·diag(fe)) weighting matrix that is worth to according to experimental modal frequency is represented, Round (), max () and diag () represent round, maximum operation and diagonal matrix computing, p tables respectively Show parameter vector to be modified, the physical meaning of the object function is：In the excursion [p of parameterl,pu] in, find and optimize ginseng Number causes two Norm minimums of experimental modal frequency and Analysis Mode frequency vector difference；
4.3) elasticity based on object function (18) the structure optimization indirect problem constructed to COMPOSITE FINITE ELEMENT model Parameter is modified, and obtains accurately and effectively finite element analysis model.

Claims (3)

  1. A kind of 1. composite structure correction method for finite element model based on cluster analysis, it is characterised in that：Including following step Suddenly：
    (1) formed according to composite structure geometric properties and component, using orthotropic material relationships to actual multiple Condensation material structure is modeled, and simplifies details component, only considers macroscopical configuration of composite structure, and establishing equivalent initial has Finite element analysis model；
    (2) according to the actual geometric parameter of composite structure, experimental model is established, using dynamics modal experimental technique, is measured The experimental modal frequency and Mode Shape of structure；
    (3) the relative sensitivity matrix of parameter to be modified is calculated, treating corrected parameter using hierarchical clustering algorithm carries out parameter point Group, then Relative sensitivity analysis is carried out to clustering parameter, select the clustering parameter that relative sensitivity average value is maximum in each parameter It is modified；
    (4) residual vector of the modal frequency of structural analysis model and actual measurement modal frequency, is established needed for analysis model amendment Object function, the optimization indirect problem for building object function are modified to the FEM model of composite structure；
    Wherein, step (3) comprises the following steps：
    3.1) according to relative sensitivity calculation formula, relative sensitivity matrix of the modal frequency relative to elastic parameter is calculated：
    <mrow> <msub> <mi>S</mi> <mi>r</mi> </msub> <mo>=</mo> <mi>f</mi> <mfrac> <mrow> <mo>&amp;part;</mo> <mi>f</mi> </mrow> <mrow> <mo>&amp;part;</mo> <mi>p</mi> </mrow> </mfrac> <mi>p</mi> <mo>-</mo> <mo>-</mo> <mo>-</mo> <mrow> <mo>(</mo> <mn>1</mn> <mo>)</mo> </mrow> </mrow>
    In formula, SrIt is relative sensitivity matrix, f is output modalities frequency vector, and p is elastic parameter vector to be modified；
    3.2) relative sensitivity column vector g is calculatedα、gβDistance d：
    <mrow> <mi>d</mi> <mo>=</mo> <mn>1</mn> <mo>-</mo> <mfrac> <mrow> <msubsup> <mi>g</mi> <mi>&amp;alpha;</mi> <mi>T</mi> </msubsup> <msub> <mi>g</mi> <mi>&amp;beta;</mi> </msub> </mrow> <msqrt> <mrow> <mo>(</mo> <msubsup> <mi>g</mi> <mi>&amp;alpha;</mi> <mi>T</mi> </msubsup> <msub> <mi>g</mi> <mi>&amp;alpha;</mi> </msub> <mo>)</mo> <mo>&amp;CenterDot;</mo> <mo>(</mo> <msubsup> <mi>g</mi> <mi>&amp;beta;</mi> <mi>T</mi> </msubsup> <msub> <mi>g</mi> <mi>&amp;beta;</mi> </msub> <mo>)</mo> </mrow> </msqrt> </mfrac> <mo>-</mo> <mo>-</mo> <mo>-</mo> <mrow> <mo>(</mo> <mn>2</mn> <mo>)</mo> </mrow> </mrow>
    Relative sensitivity is classified apart from close parameter using hierarchical clustering algorithm, so as to obtain the layering of elastic parameter Tree table reaches, and recycles distance threshold 0.2 to carry out packet p={ p to elastic parameter as parameter packet standard1；p2；…；pj, n1,n2,…,njThe respectively number of each group parameter, and n1+n2+…+nj=N, N represent elastic parameter sum；
    3.3) clustering parameter θ is definedjFor the relative change of jth group elastic parameter：
    <mrow> <msub> <mi>p</mi> <mi>j</mi> </msub> <mo>=</mo> <msubsup> <mi>p</mi> <mi>j</mi> <mn>0</mn> </msubsup> <mrow> <mo>(</mo> <mn>1</mn> <mo>-</mo> <msub> <mi>&amp;theta;</mi> <mi>j</mi> </msub> <mo>)</mo> </mrow> <mo>-</mo> <mo>-</mo> <mo>-</mo> <mrow> <mo>(</mo> <mn>3</mn> <mo>)</mo> </mrow> </mrow>
    In formula, pjIt is vectorial for jth group elastic parameter,Represent jth group elastic parameter initial value, θjTo gather corresponding to jth group bullet parameter Class parameter；
    Using the Calculation of Sensitivity formula of clustering parameter, clustering parameter is chosen, determines clustering parameter to be modified：
    <mrow> <msub> <mi>S</mi> <mi>c</mi> </msub> <mo>=</mo> <mfrac> <mrow> <mo>&amp;part;</mo> <mi>f</mi> </mrow> <mrow> <mo>&amp;part;</mo> <mi>p</mi> </mrow> </mfrac> <mfrac> <mrow> <mo>&amp;part;</mo> <mi>p</mi> </mrow> <mrow> <mo>&amp;part;</mo> <mi>&amp;theta;</mi> </mrow> </mfrac> <mo>-</mo> <mo>-</mo> <mo>-</mo> <mrow> <mo>(</mo> <mn>4</mn> <mo>)</mo> </mrow> </mrow>
    In formula, ScThe sensitivity matrix of clustering parameter is represented, θ is clustering parameter vector, and the element of clustering parameter vector is by clustering Parameter θjComposition.
  2. 2. the composite structure correction method for finite element model according to claim 1 based on cluster analysis, its feature It is：Step (2) obtains experimental modal frequency and the process of Mode Shape comprises the following steps：
    2.1) according to the geometric parameter of composite structure, its experimental model is established；
    2.2) structure point layout, in structure boundary away from selection pick-up point at mode stationary point；
    2.3) composite structure is hung with rubber rope, it is Z-direction to define perpendicular to the direction in suspension face, and makes it In freedom-free state, acceleration transducer is fixed on to selected pick-up point；
    2.4) power hammer and acceleration transducer are respectively connected to signal sampler；
    2.5) the model analysis module of dynamic test system is utilized, model analysis parameter is set；
    2.6) firmly hammer successively to the impacting point in structure along Z-direction apply impulsive force, gather successively each measuring point by Input power during pulse excitation is with exporting acceleration signal at pick-up point；
    2.7) modal parameter amendment is carried out to input/output signal with the signal analyzer of pilot system, passes through each point frequency response function Lump, fitting and amendment obtain the actual measurement modal frequency and Mode Shape of composite structure.
  3. 3. the composite structure correction method for finite element model according to claim 1 based on cluster analysis, its feature It is：Step (4) comprises the following steps：
    4.1) to resulting composite structure experimental modal frequency, the experimental modal vibration shape is determined using modal assurance criterion MAC Corresponding each rank Analysis Mode frequency, carry out Mode Shape matching：
    <mrow> <mi>M</mi> <mo>=</mo> <mfrac> <mrow> <mo>|</mo> <msubsup> <mi>&amp;Phi;</mi> <mi>a</mi> <mi>T</mi> </msubsup> <msub> <mi>&amp;Phi;</mi> <mi>e</mi> </msub> <msup> <mo>|</mo> <mn>2</mn> </msup> </mrow> <mrow> <mo>(</mo> <msubsup> <mi>&amp;Phi;</mi> <mi>a</mi> <mi>T</mi> </msubsup> <msub> <mi>&amp;Phi;</mi> <mi>a</mi> </msub> <mo>)</mo> <mo>(</mo> <msubsup> <mi>&amp;Phi;</mi> <mi>e</mi> <mi>T</mi> </msubsup> <msub> <mi>&amp;Phi;</mi> <mi>e</mi> </msub> <mo>)</mo> </mrow> </mfrac> <mo>-</mo> <mo>-</mo> <mo>-</mo> <mrow> <mo>(</mo> <mn>5</mn> <mo>)</mo> </mrow> </mrow>
    In formula, M represents modal assurance criterion matrix, ΦaAnd ΦeAnalysis and the experimental modal vibration shape are represented respectively, are finally defined below Objective optimization function：
    <mrow> <mfenced open = "{" close = ""> <mtable> <mtr> <mtd> <mrow> <mi>min</mi> <mi> </mi> <mi>J</mi> <mrow> <mo>(</mo> <mi>p</mi> <mo>)</mo> </mrow> <mo>=</mo> <mi>&amp;epsiv;</mi> <msup> <mrow> <mo>(</mo> <mi>p</mi> <mo>)</mo> </mrow> <mi>T</mi> </msup> <mi>W</mi> <mi>&amp;epsiv;</mi> </mrow> </mtd> </mtr> <mtr> <mtd> <mrow> <mi>s</mi> <mo>.</mo> <mi>t</mi> <mo>.</mo> <msub> <mi>p</mi> <mi>l</mi> </msub> <mo>&amp;le;</mo> <mi>p</mi> <mo>&amp;le;</mo> <msub> <mi>p</mi> <mi>u</mi> </msub> </mrow> </mtd> </mtr> </mtable> </mfenced> <mo>-</mo> <mo>-</mo> <mo>-</mo> <mrow> <mo>(</mo> <mn>6</mn> <mo>)</mo> </mrow> </mrow>
    In formula, p is elastic parameter to be modified vector, and J (p) represents object function, and ε (p) is modal frequency faWith modal frequency feStructure Residual vector and ε (p)=f madee-fa(p), W ε=round (max (fe)·diag(fe)), represent according to experimental modal frequency The weighting matrix being worth to, round (), max () and diag () represent respectively round, maximum operation and Diagonal matrix computing；The physical meaning of the object function is：In the excursion [p of parameterl,pu] in, finding the most optimized parameter makes Obtain two Norm minimums of experimental modal frequency and Analysis Mode frequency vector difference；
    4.3) elastic parameter of COMPOSITE FINITE ELEMENT model is entered based on object function (6) the structure optimization indirect problem constructed Row amendment, obtains effective elastic parameter.
CN201710568512.1A 2017-07-13 2017-07-13 Composite structure correction method for finite element model based on cluster analysis Active CN107357992B (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CN201710568512.1A CN107357992B (en) 2017-07-13 2017-07-13 Composite structure correction method for finite element model based on cluster analysis
PCT/CN2018/083368 WO2019011026A1 (en) 2017-07-13 2018-04-17 Composite material structure finite element model correction method based on cluster analysis

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201710568512.1A CN107357992B (en) 2017-07-13 2017-07-13 Composite structure correction method for finite element model based on cluster analysis

Publications (2)

Publication Number Publication Date
CN107357992A CN107357992A (en) 2017-11-17
CN107357992B true CN107357992B (en) 2018-03-23

Family

ID=60292568

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201710568512.1A Active CN107357992B (en) 2017-07-13 2017-07-13 Composite structure correction method for finite element model based on cluster analysis

Country Status (2)

Country Link
CN (1) CN107357992B (en)
WO (1) WO2019011026A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109283071A (en) * 2018-10-30 2019-01-29 济南大学 A kind of low test cost acquisition methods of CFRP low-velocity impact damage sample

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107357992B (en) * 2017-07-13 2018-03-23 东南大学 Composite structure correction method for finite element model based on cluster analysis
CN107992709B (en) * 2017-12-28 2021-05-14 南京林业大学 Thermal structure model correction method based on intermediate function
CN108416080B (en) * 2018-01-19 2019-05-14 东南大学 Composite material modeling method based on repetitive substructure
CN108287970B (en) * 2018-01-31 2019-01-29 东南大学 Sensitivity Analysis Method of the hot-die state based on two-dimensional quadrature anisotropic composite material plate to structural parameters
CN108595781A (en) * 2018-03-30 2018-09-28 东南大学 The elastic parameter recognition methods of fiber and matrix after a kind of composite molding
CN108959686A (en) * 2018-04-17 2018-12-07 中国科学院沈阳自动化研究所 A kind of correction method for finite element model based on sensitivity analysis
CN108984887B (en) * 2018-07-06 2023-04-25 南京林业大学 Multi-stage identification method for deterministic parameters of composite material
CN109241559B (en) * 2018-08-01 2019-06-18 东南大学 A kind of composite material elastic parameter recognition methods based on minor structure
CN109885896B (en) * 2019-01-25 2020-04-24 东南大学 Nonlinear structure finite element model correction method based on complex variation differential sensitivity
CN110222413B (en) * 2019-06-03 2022-10-14 中船动力研究院有限公司 Oil pan optimization method and device, computer equipment and medium
CN111931396A (en) * 2020-06-28 2020-11-13 中国电力科学研究院有限公司 Distribution transformer oil tank structure modal analysis method and device
CN112016222B (en) * 2020-07-13 2024-06-25 苏州睿友智能装备有限公司 Modal optimization method based on assembly finite element model and orthogonal test method
CN112036062A (en) * 2020-08-07 2020-12-04 丽水学院 Metal material bending forming rebound angle prediction method
CN112231954B (en) * 2020-10-15 2023-11-21 中国水利水电科学研究院 Method for establishing digital twin model of hydraulic structure
CN113128083B (en) * 2021-03-15 2024-04-19 西安理工大学 Actuator optimal arrangement method for vibration control of hydraulic arc-shaped steel gate
CN113204739A (en) * 2021-05-24 2021-08-03 桂林电子科技大学 Frequency response function quality line optimization method based on K-means clustering
CN113779837B (en) * 2021-09-13 2024-02-13 长春工程学院 Structural modal sensitivity analysis method based on novel actual measurement normalization technology
CN114398808B (en) * 2021-12-10 2024-03-29 航天科工火箭技术有限公司 Quick model correction method for bolt connection joint surface
CN114386284B (en) * 2022-01-17 2024-08-06 北京源清慧虹信息科技有限公司 Automatic modal parameter identification method based on cluster analysis and data fusion
CN114815586B (en) * 2022-04-28 2024-09-10 南阳煜众精密机械有限公司 Digital twin process model construction method and application of machine tool feeding system
CN114970243A (en) * 2022-05-05 2022-08-30 西安交通大学 Reverse identification method and system for joint surface rigidity parameters
CN115166055B (en) * 2022-06-07 2024-07-09 中国航空规划设计研究总院有限公司 Ancient building wood structure mechanical parameter identification method and auxiliary test device thereof
CN115062514B (en) * 2022-06-21 2024-07-12 重庆邮电大学 Modal parameter-based generator stator end winding physical parameter identification and mathematical model establishment method
CN115828673B (en) * 2022-11-21 2024-06-04 中国人民解放军96901部队22分队 Analysis method for vibration characteristics of rocket
CN117852351B (en) * 2024-01-08 2024-08-16 北京建筑大学 Method and system for calculating and arranging monitoring sensor positions in wood structure building
CN118332883A (en) * 2024-06-17 2024-07-12 西安航天动力研究所 Simulation calculation method and device for detail stress of metal hose

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106529055A (en) * 2016-11-18 2017-03-22 南京航空航天大学 Model updating method based on strain modal shape correlation

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102567582B (en) * 2011-12-30 2015-05-20 南京航空航天大学 Finite-element analysis-based method for designing profile of autoclave molding fixture of composite material member
CN103077286B (en) * 2013-01-18 2016-01-13 大连理工大学 A kind of frequency error correction method of plane flutter model
CN105184390A (en) * 2015-08-12 2015-12-23 中国运载火箭技术研究院 Integrated optimization method of static strength, rigidity, stability of wallboard structure
CN107357992B (en) * 2017-07-13 2018-03-23 东南大学 Composite structure correction method for finite element model based on cluster analysis

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106529055A (en) * 2016-11-18 2017-03-22 南京航空航天大学 Model updating method based on strain modal shape correlation

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
The sensitivity method in finite element model updating: A tutorial;John E. Mottershead等;《Mechanical Systems and Signal Processing》;20111231;第2275-2296页 *
一种有限元模型修正中的参数选择方法;姜东等;《固体力学学报》;20111031;全文 *
复合材料结构有限元模型修正技术研究;刘国青;《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》;20110715;摘要、第3-8页、第52-62页 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109283071A (en) * 2018-10-30 2019-01-29 济南大学 A kind of low test cost acquisition methods of CFRP low-velocity impact damage sample

Also Published As

Publication number Publication date
CN107357992A (en) 2017-11-17
WO2019011026A1 (en) 2019-01-17

Similar Documents

Publication Publication Date Title
CN107357992B (en) Composite structure correction method for finite element model based on cluster analysis
CN106294941B (en) A kind of bolt connection combination face stiffness simulation method for considering pretightning force
CN104866673B (en) A kind of axle presses the Cutout reinforcement method of reinforcement post shell
CN110162821B (en) Method for calculating bird-hit high-speed rotating engine blade
CN107085633B (en) Device and method for multi-point vibration response frequency domain prediction based on support vector machine
CN111159934B (en) Dynamics simulation method for aluminum-based composite material
CN106055769A (en) Performance recognition method of bolt interfaces under different tightening torques
CN103955604A (en) Method for predicating residual intensity of metal gradient material with cracks
CN112414668B (en) Wind tunnel test data static bomb correction method, device, equipment and medium
CN112528411A (en) Geometric nonlinear structure noise vibration response calculation method based on modal reduction
CN101702092B (en) Random vibration control method of electro-hydraulic servo system based on Kalman filter
CN109101692A (en) Composite laminated plate ultimate load calculation method based on maximum stress criterion
Gong et al. Application of Ritz method for vibration analysis of stepped functionally graded spherical torus shell with general boundary conditions
CN110704953A (en) Analysis method for design sensitivity of static air elastic energy of high-aspect-ratio wing
CN107657073A (en) A kind of parameter identification method of sandwich composite structure
CN114818410A (en) Simulation method for fatigue strength of butt solid weld
CN113158508A (en) Method for determining ultimate load after patching and repairing composite laminated plate
CN107314938A (en) The implementation method of nugget region material plastic inverting identification
CN104008234B (en) Method for correcting closely spaced mode model with damping structure
Neumann et al. Steady and unsteady aeroelastic simulations of the HIRENASD wind tunnel experiment
CN113239464B (en) Method and device for determining vehicle body section
CN114880904A (en) Large-scale finite element analysis method for rubber bushing
CN109117547B (en) Method for optimizing dynamic characteristics of large part structure of machine tool
CN102930161A (en) Hybrid modal indicating method based on multi-cabin spacecraft
CN108197397B (en) Optimization design method for dynamic performance of fastening joint surface of aircraft engine

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant