CN106950280B - Fibre reinforced composites parameter identification method based on the lossless scanning of laser - Google Patents

Fibre reinforced composites parameter identification method based on the lossless scanning of laser Download PDF

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CN106950280B
CN106950280B CN201710155498.2A CN201710155498A CN106950280B CN 106950280 B CN106950280 B CN 106950280B CN 201710155498 A CN201710155498 A CN 201710155498A CN 106950280 B CN106950280 B CN 106950280B
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test specimen
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beam test
fiber
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CN106950280A (en
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李晖
刘�东
高宁
王雨波
薛鹏程
闻邦椿
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Northeastern University China
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
    • G01N29/04—Analysing solids
    • G01N29/045—Analysing solids by imparting shocks to the workpiece and detecting the vibrations or the acoustic waves caused by the shocks
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
    • G01N29/36—Detecting the response signal, e.g. electronic circuits specially adapted therefor
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2291/00—Indexing codes associated with group G01N29/00
    • G01N2291/02—Indexing codes associated with the analysed material
    • G01N2291/023—Solids
    • G01N2291/0231—Composite or layered materials
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2291/00—Indexing codes associated with group G01N29/00
    • G01N2291/02—Indexing codes associated with the analysed material
    • G01N2291/028—Material parameters

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Abstract

The present invention discloses a kind of fibre reinforced composites parameter identification method based on the lossless scanning of laser, according to fiber-reinforced composite structural material parameter identification method, input first three rank intrinsic frequency, damping ratio and resonance amplitude curve, it is 10% that identification error permissible value, which is arranged, can obtain fiber longitudinal modulus of elasticity E1, fiber transverse modulus of elasticity E2, shear modulus G12, Poisson's ratio ν21And fiber longitudinal direction fissipation factor η11, fiber lateral loss factor η22With shearing fissipation factor η12。

Description

Fibre reinforced composites parameter identification method based on the lossless scanning of laser
Technical field
The present invention relates to machinery field, specifically a kind of fibre reinforced composites parameter identification method and device.
Background technique
Structural composite material because the specific strength of its structure is high, specific modulus is high, material has designability, thermal stability good, But also have many advantages, such as that bearing capacity is big, light-weight, it is widely used in Aeronautics and Astronautics, ship, sports apparatus, electrical equipment, doctor The fields such as, weapon industry and chemical industry.With the continuous improvement of modern industry level, many fiber-reinforced composite thin-walled structures Part, such as composite material blade, composite material integral blade disk and compound organic substrate, often work high speed rotation, high temperature, In the adverse circumstances such as etchant gas erosion, thus bring vibrating fatigue, vibration failur problem are more and more prominent, prevent it from just Often fulfil the function that people imagine it in advance.
In industrial production constantly using fibre reinforced composites, it is often required that every material property to this kind of material has Clear awareness and understanding.However, its fiber longitudinal modulus of elasticity is being detected due to the anisotropy feature of composite material, Fiber transverse modulus of elasticity, modulus of shearing, Poisson's ratio and fiber longitudinal direction fissipation factor, the fiber lateral loss factor and shearing damage When consuming the material parameters such as the factor, industrially measured mostly by fatigue tester at present.This method has in all various aspects Its limitation: in terms of cost: needing to destroy more material template, cause largely to waste in terms of manpower and material resources；Measurement means Aspect: high-intensitive stretching has particular/special requirement to the stability of instrument, while the accuracy measured is difficult to ensure that measurement result is deposited In large error；Secure context: material can be broken in measurement process, there is larger hidden danger in safety.
Currently, being not very deep to the research of NDT of composite this aspect, but also there is part is relevant to grind Studying carefully has certain reference value.Patent CN201610166104.9 has invented a kind of novel composite material parameter identifier, leads to The structure for changing identifier is crossed so that the parameter identified is more accurate, however its principle is still by the biography such as pressing, cutting, draw System mode measures the parameter of composite material, there is no waste is fundamentally solved, there is the problems such as certain security risk.Fiber is increased The detection method of strong composite material needs to improve, and can be well solved relevant issues using vibration and the lossless scanning technique of laser.
Summary of the invention
In view of the problems of the existing technology, the present invention provides a kind of fiber-reinforced composite knot based on the lossless scanning of laser Structure material parameter tester and its working method.Specific technical solution is as follows:
Fibre reinforced composites parameter identification method based on the lossless scanning of laser, comprising the following steps:
Step 1: opening vacuum casting, adjusting screws screw rod, composite beam test specimen to be measured is successively installed on clamping device Base position；
Step 2: screw rod is screwed by adjusting, gradually tightens the pressure of clamping device, the pressure exported according to pressure sensor Power registration after judgement arrived suitable clamping force, stops adjusting；
Step 3: adjusting hoistable platform to suitable position, tighten vacuum casting；The gas in shell is discharged with air exhauster, Manufacture vacuum environment；
Step 4: the laser spot position issued by the mobile laser vibration measurer of laser scanning vibration detecting device is to be measured The free end position of composite beam test specimen；Then, exciting device is opened, the survey of sine sweep exciting is carried out in larger frequency range Examination according to the time domain waveform data for the acceleration transducer monitoring scanning frequency excitation signal being equipped on clamping device top, and passes through Laser vibration measurer obtains the frequency spectrum of the vibration response signal of the free end position of composite beam test specimen to be measured, passes through half-power bandwidth method The frequency of the corresponding frequency of each peak value and half power points is recognized, and then obtains the intrinsic frequency of first three rank of composite beam test specimen to be measured Rate and damping ratio；
Step 5: the frequency for adjusting exciting device is first natural frequency, and composite beam test specimen to be measured is excited to reach the first rank Resonance state determines the corresponding excitation amplitude of the first rank resonance state by acceleration transducer on shaking platform；Meanwhile it opening The control switch of laser scanning vibration detecting device, the laser point issued by the mobile laser vibration measurer of laser scanning vibration detecting device It sets, realizes to composite beam test specimen to be measured from cantilever end position to the sweep test of free end position, obtain composite beam test specimen to be measured In the vibration response signal amplitude of each scanning point position, and then draws out composite beam test specimen under the first rank resonance state and vibrate Amplitude is with the change curve with its length, referred to as the first rank resonance amplitude curve, the first rank resonance amplitude curve horizontal axis For length, the longitudinal axis is vibration amplitude；
Step 6: the frequency for adjusting exciting device is second-order intrinsic frequency and third rank intrinsic frequency, is adopted according to step 5 With the step of, obtain second-order resonance amplitude curve and third rank resonance amplitude curve；
Step 7: according to fiber-reinforced composite structural material parameter identification method, inputting first three rank intrinsic frequency, damping ratio With resonance amplitude curve, it is 10% that identification error permissible value, which is arranged, can obtain fiber longitudinal modulus of elasticity E1, fiber transverse direction bullet Property modulus E2, shear modulus G12, Poisson's ratio ν21And fiber longitudinal direction fissipation factor η11, fiber lateral loss factor η22With cut Cut fissipation factor η12。
The present invention further discloses a kind of devices for realizing the method, mainly flat by compound workbench, lifting Platform, clamping device, exciting device, laser scanning vibration measuring system and vacuum plant composition；Compound workbench includes the first work Platform and the second workbench are connected by " work " word supporting steel between two platforms, and lower section is supported by pedestal；Clamping device is for fixing And monitoring composite beam test specimen to be measured, the briquetting including reference platform and upper part, the briquetting are driven by bolt and are pushed, it will be to be measured Composite beam test specimen is fixed；Two borehole structures are provided on reference platform, the round pressure for placement force sensor senses Gasket quantifies adjustment effect according to the numerical value of pressure sensor in the pressure of composite beam test specimen to be measured, realizes constraint condition Quantization signifying test；Exciting device is made of vibration excitor and shaking platform two parts, and effect is to generate exciting force and to tested The transmitting vibration of composite beam test specimen；Vibration excitor is connect with signal source, generates the vibration of certain frequency, and vibration passes through shaking platform and folder It holds mechanism and passes to beam test specimen to be measured；To realize the monitoring to excited vibration state, passed on clamping device top equipped with acceleration Sensor, for measuring the size of Oscillation Amplitude；Vibration excitor, which is bolted, to be fixed on the first workbench, sharp to generate Power is encouraged, and is applied it on shaking platform；There are four the damping screw rod for being evenly distributed on quadrangle, damping bullets below shaking platform Spring can pack into damping screw rod, and realization is connected with the first workbench, can only generate the position on axle of spring direction between the two It moves；
Laser scanning vibration measuring system includes laser scanning vialog, lead screw, shaft coupling and motor；Carry laser scanning The platform of vialog is run through by one group of lead screw, and lead screw is connected with shaft coupling, constitutes transmission mechanism；Under the power of motor, Laser scanning vialog can realize the movement of vibration measurement with laser device horizontal direction by transmission mechanism；What laser vibration measurer issued Laser spot position is realized to composite beam test specimen to be measured under certain scanning speed from cantilever end position to free end position Sweep test obtains composite beam test specimen to be measured in the vibration response signal amplitude of each scanning point position, and then draws out phase The resonance amplitude curve answered；Laser scanning vibration measuring system, which is arranged on hoistable platform, can be achieved laser scanning vialog in vertical side The adjustment of upward position, the crane of the hoistable platform are fixed on the second workbench.
It is equipped with vacuum plant in the outside of tester, is made of shell and baffle；Baffle is closely connect with shell, prevents sky Gas enters；There is borehole structure on baffle, be connected with air pump, so that gas in withdrawing device, creates vacuum environment, reduces experiment Error.
The invention has the advantages that the present invention provides a kind of fiber-reinforced composite structural materials based on the lossless scanning of laser Parameter tester.Parameter test method of the vibration transmitting in conjunction with laser displacement sensing technology is devised first, has broken tradition The mode measured by physical methods such as stretchings, and realize the mechanical property of disposable measurement detected materials in all directions The target of energy, considerably reduces the workload of related work；Secondly, instrument will not generate material in the whole process of test Any influence has saved raw material, reduces economic loss, more environmentally protective；In addition, external install setting for vaccum case additional Meter, so that test process carries out under vacuum, avoids the influence of air damping, measurement result is more acurrate；Finally, this work Product are convenient for assembly and disassembly, and the quality of each component is little, can be packed into drawing case, have preferable portability.It can be according to reality Situation is provided a great convenience in the parameter of different location measurement composite material for production measurement.
Detailed description of the invention
Fig. 1 is the front view of the fiber-reinforced composite structural material parameter tester of the specific embodiment of the invention；
Fig. 2 is the top view of the fiber-reinforced composite structural material parameter tester of the specific embodiment of the invention；
Fig. 3 is the structure diagram of the fiber-reinforced composite structural material parameter tester of the specific embodiment of the invention；
Fig. 4 is the theoretical model of fiber-reinforced composite beam test specimen under Fig. 1 basic excitation；
Fig. 5 is theoretical and experiment obtains composite beam the first rank resonance amplitude curve and its error bound figure；
In figure: 1- pedestal, the second workbench of 2-, 3- " work " word supporting steel, the first workbench of 4-, 5- shaking platform, 6- damping spring, 7- baffle, 8- clamping device, 9- acceleration transducer, 10- lead screw, 11- laser scanning vialog, 12- shell Body, 13- sliding block, 14- hoistable platform, 15- beam test specimen to be measured, 16- vibration excitor, 17- reference platform, 18- briquetting, 19- are scalable Platform, 20- gas vent, 21- reference platform.
Specific embodiment
The present invention is illustrated with reference to the accompanying drawing.
1. tester Design of Hardware Architecture
As shown, the device of the invention mainly by compound workbench, hoistable platform, clamping device, exciting device, Laser scanning vibration measuring system and vacuum plant composition；
Compound workbench includes the first workbench 4 and the second workbench 2, by " work " word supporting steel 3 between two platforms Connection, lower section is supported by pedestal 1；Clamping device 8 for fixing and monitor composite beam test specimen 15 to be measured, including reference platform 17 and The briquetting 18 of upper part, the briquetting are driven by bolt and are pushed, composite beam test specimen to be measured is fixed；
17 upper surface of reference platform is provided with two borehole structures, the round pressure sensor mat for placement force sensor Piece quantifies adjustment effect according to the numerical value of pressure sensor in the pressure of composite beam test specimen to be measured, realizes the amount of constraint condition Change characterization test.
Exciting device is made of vibration excitor 16 and 5 two parts of shaking platform, and effect is to generate exciting force and answer to tested Close the transmitting vibration of beam test specimen；Vibration excitor is connect with signal source, generates the vibration of certain frequency, and vibration passes through shaking platform 5 and folder It holds mechanism 8 and passes to beam test specimen 15 to be measured；To realize the monitoring to excited vibration state, on 8 top of clamping device equipped with acceleration Sensor 9 is spent, for measuring the size of Oscillation Amplitude.Vibration excitor 16, which is bolted, to be fixed on the first workbench 4, is used To generate exciting force, and apply it on shaking platform 5；There are four the dampings for being evenly distributed on quadrangle for 5 lower section of shaking platform Screw rod, damping spring 6 can pack into damping screw rod, and realization is connected with the first workbench 4, can only generate spring shaft between the two Displacement on line direction.
Laser scanning vibration measuring system includes laser scanning vialog 11, lead screw 10, shaft coupling and motor.Carry laser The platform of scanning vialog is run through by one group of lead screw, and lead screw is connected with shaft coupling, constitutes transmission mechanism；In the power of motor Under, laser scanning vialog can realize the movement of vibration measurement with laser device horizontal direction by transmission mechanism.Laser vibration measurer hair Laser spot position out, under certain scanning speed, realization position from cantilever end position to free end to composite beam test specimen to be measured The sweep test set obtains composite beam test specimen to be measured in the vibration response signal amplitude of each scanning point position, and then draws Corresponding resonance amplitude curve out.Laser scanning vibration measuring system is arranged on hoistable platform 14 achievable laser scanning vialog and exists The adjustment of position on vertical direction, the crane of the hoistable platform 14 are fixed on the second workbench 2, two cross-articulations Supporting beam, one is fixed on workbench 2, and in addition one connects with 13 axis of sliding block, and sliding block is connected to motor by lead screw；? Under motor driven, lead screw band movable slider 13 slides on workbench and then hoistable platform is driven to move up and down；
It is equipped with vacuum plant in the outside of tester, is made of shell and baffle.Baffle can closely be connect with shell, be prevented Air enters；There is borehole structure on baffle, can be connected with air pump, so that gas in withdrawing device, creates vacuum environment, reduces Experimental error.
2. the fiber-reinforced composite structural material parameter identification method is:
2.1 vibratory response solves under fiber-reinforced composite beam test specimen inherent characteristic and basic excitation；
Composite beam test specimen is that had the characteristics that made of the fiber of orthotropy and matrix material combinations as n-layer；Assuming that It is secure bond between each layer, interlayer is without sliding, no relative displacement, admittedly it can not consider the influence of proximity effects；It is first First, wherein as a reference plane, and xoy coordinate system will be established in face；Assuming that the angle of machine direction and global coordinate system x-axis direction For θ, a length of a of plate, plate width is b, plate thickness h, and each layer is located at the lower surface h of z coordinate axisk-1With high surfaces hkBetween, every layer Thickness it is all the same；1 in figure represents fiber longitudinal direction, and 2 represent fiber transverse direction, and 3 represent the direction perpendicular to 1-2 plane；
Assuming that composite beam test specimen is influenced by basic excitation load, and the movement expression formula of the basic excitation be y (t)= Yeiωt (1)
I indicates empty unit
T indicates the time
Wherein, Y is excitation amplitude, and ω is driving frequency；
The influence for considering machine direction, is expressed as form for the elasticity modulus of composite material
Wherein,The complex modulus in parallel fibers direction and vertical fibers direction is respectively represented,It is flat to represent 1-2 Complex shear modulus in face, E1'、E2' and G1'2Complex modulus respectively And complex shear modulusReal part；And 1 side The Poisson's ratio for causing 1,2 directions to strain to applied stress is ν12, 2 direction applied stress cause 1,2 directions strain Poisson's ratio be ν21；
Based on Classical lamination theory, the displacement field of fiber-reinforced composite beam test specimen can be written as following form
Wherein, z indicates displacement in the z-axis direction；U, v, w represent the displacement at any point in plate；
u0,v0,w0Face in plate is represented to be displaced；H is the thickness of composite beam test specimen；T indicates the time；
Due to being that there is no couplings for Analysis of Symmetric Laminated Plates, in plane vibration and oscillation crosswise, therefore need to only consider the transverse direction of thin plate Vibration, that is, ignore middle face displacement components u0And v0；According to the hypothesis of Classical lamination theory it is found that normal strain εzWith shearing strain γyz、 γxzIt is all 0, i.e. εz=γyz=γxz=0, by the relationship for straining and being displaced, the strain at any point can be expressed as in plate
εxIndicate the normal strain of point in the x direction
εyIndicate the normal strain of point in y-direction
γxyIndicate shearing strain of this on x/y plane
Face bending deflection rate and twisting coefficient are represented by thin plate
kxIndicate the deflection rate of point in the x direction
kyIndicate the deflection rate of point in y-direction
kxyIndicate twisting coefficient of this on x/y plane
I.e.
εx=z κx, εy=z κy, γxy=z κxy
For orthotropic material, the strain-stress relation of material major axes orientation is
1 indicates that fiber is longitudinal, and 2 indicate that fiber is lateral, and 6 indicate vertical board direction, and Q* indicates coefficient of elasticity
Wherein,
When having certain angle theta between material major axes orientation and global coordinate system, calculated with stress-strain rotation axis formula It is as follows to strain-stress relation of the kth laminate under global coordinate system
Wherein,
Wherein, k indicates the kth layer of composite beam test specimen, θkIndicate the machine direction and global coordinate system x-axis of kth laminate Angle；
Thin plate institute's bending moment and torque are
MxIndicate the moment of flexure in x-axis direction
MyIndicate the moment of flexure on y-axis direction
MxyIndicate the torque on x/y plane
D* indicates bending stiffness coefficient
Wherein,
For the ease of theory analysis modeling, basic excitation suffered by composite beam test specimen is equivalent to carry outside uniformly distributed inertia force
The displacement amplitude of Y expression basic excitation
Then the kinetic energy of thin plate vibration can be indicated with following formula
Wherein, ρ is the density of thin plate, and h is gauge of sheet；
Then the strain energy of thin plate bending storage is indicated with following formula
Uniformly distributed inertia force, which does work, suffered by thin plate is
Wq=∫ ∫Rq(t)w0dxdy (13)
Assuming that the vibration displacement of thin plate oscillation crosswise can be expressed as
w0(x, y, t)=eiωtW(ξ,η) (14)
Wherein, ω is the circular frequency of thin plate vibration, W identical as driving frequencyij(ξ, η) is model function of vibration, there is following form
Wherein, aijFor undetermined coefficient, pi(ξ) (i=1 ..., M) and qj(η) (j=1 ..., N) it is a series of orthogonal Multinomial；
A series of orthogonal polynomial is obtained by being orthogonalized processing to the polynomial function for meeting boundary condition
P1(ξ)=χ (ξ), P1(η)=κ (η)
P2(ζ)=(ζ-B2)P1(ζ)
Pk(ζ)=(ζ-Bk)Pk-1(ζ)-CkPk-2(ζ)
ζ=ξ, η, k > 2 (16)
Wherein, BkAnd CkFor coefficient function, expression formula is respectively
Wherein, W (ζ) is weight function, usually takes W (ζ)=1；And χ (ξ) and κ (η) be meet clamped, freely-supported, freely it is equilateral The polynomial function of boundary's condition, and there is following form
χ (ξ)=ξp(1-ξ)q, κ (η)=ηr(1-η)s
ξ=x/a, η=y/b (18)
Due to being cantilever, so p=2 is taken, r=0, q=0, s=0；By formula (15) substitute into formula (11), (12) and in (13), the maximum kinetic energy T of available composite beam test specimen vibrationmax, maximum strain energy UmaxIt is done with uniformly distributed inertia force Function maximum value WqmaxRespectively
Wqmax=ρ hY ω2∫∫RWdxdy (21)
The expression formula for defining Lagrangian energy function L is
L=Tmax+Wqmax-Umax (22)
By making energy function L to undetermined coefficient aijPartial derivative be equal to zero, i.e.,
M × N number of Nonhomogeneous Linear algebraic equation can be obtained, in order to solve conveniently, being written as matrix form is (K+ iC-ω2M) (24) a=F
Wherein, K, C and M are respectively structural stiffness matrix, material damping matrix and architecture quality matrix, generalized displacement vector A=(a11,a12,…aij)T, F is exciting force vector；
For the vibration problems of composite beam test specimen, only need to enable material damping Matrix C and exciting force vector F is zero, i.e.,
(K -ω2M) (25) a=0
The intrinsic frequency and Mode Shape of composite beam test specimen can be acquired by formula (25)；Further, it is assumed that fiber reinforcement is multiple It closes beam test specimen to be acted on by basic excitation load, and solves the expression formula of its vibratory response λ (x, y, t) under basic excitation；Consider What it is to experiment test acquisition is the response of composite beam test specimen absolute vibration, i.e., is displaced including the vibratory response of its own and basic excitation The sum of；Therefore, the vibratory response λ (x, y, t) of composite beam test specimen under basic excitation can be expressed as
λ (x, y, t)=y (t)+w0(x,y,t) (26)
Formula (26) gives the solution expression formula of fiber-reinforced composite beam test specimen vibratory response under basic excitation, clear In the case where basic excitation expression formula (1) and thin plate vibration response expression formula (14), it is any that acquisition composite beam test specimen can be calculated The vibratory response of a bit；
2.2 obtain composite material parameter based on first three rank intrinsic frequency and damping test result primary Calculation
Firstly, the material parameter mean value provided with manufacturerCentered on, consider Rerr=10%~20% misses Difference, the value range for providing material parameter are as follows
Suitable step-length building material parameter vector E is chosen in each value range of material parameters1,E2,G12,ν12, specifically Expression formula is
On the basis of obtaining the theoretical intrinsic frequency with experiment respectively, relative difference on frequency letter is constructed based on least square method Number efre:
Wherein, R is rank number of mode, Δ fiThe i-th rank that the i-th rank intrinsic frequency and experiment obtained for theoretical calculation obtains is solid There is frequency difference,The the i-th rank intrinsic frequency obtained for experiment test；
Material parameter is iterated in a manner of permutation and combination, as least square relative error function efreIt obtains minimum When value, i.e., primary Calculation obtains material parameter E1,E2,G12,ν12；
Then, each rank modal loss factor η can be obtained by the relationship of damping ratio and fissipation factorrFor
ηr=2 ζr (42)
Wherein, ζrThe damping ratios obtained for experiment；
According to modal strain energy method, fiber is longitudinal, fiber transverse direction and shear direction strain energy U1、U2And U12Respectively
The fissipation factor of modal loss factor and fiber all directions has following relationship
Wherein, U is the total strain energy of composite beam test specimen；
By formula (44) as long as it is found that 3 rank damping ratios are as a result, preliminary before obtaining composite beam test specimen by experiment Determine the fissipation factor η of fiber longitudinal direction, fiber transverse direction and shear direction1、η2And η12；
In this way, can be by first three rank intrinsic frequency and damping test as a result, primary Calculation obtains E1,E2,G12,ν12η1、η2 And η12Deng 7 material parameters；
2.3 are based on the lossless scanning experimental data accurate recognition composite material parameter of laser
Firstly, obtaining first three rank intrinsic frequency and damping ratio of composite beam test specimen, and by experiment test with above-mentioned intrinsic Frequency excitation composite beam test specimen reaches resonance state, then obtains first three rank of composite beam respectively by the lossless scanning experiment of laser Resonance amplitude curve；Then, fiber longitudinal modulus of elasticity E is being primarily determined1, fiber transverse modulus of elasticity E2, shear modulus G12、 Poisson's ratio ν12, fiber longitudinal direction fissipation factor η1, fiber lateral loss factor η2With shearing fissipation factor η12On the basis of, consider more Small error range (such as 10%), with smaller step-length building material parameter vector, and to parameter in a manner of permutation and combination It is iterated, every iteration is primary, and the corresponding resonance amplitude curve of one group of first three rank intrinsic frequency can be obtained by theoretical calculation；
Finally, comparing the corresponding resonance amplitude curve of first three rank intrinsic frequency and the test acquisition of certain theoretical calculation acquisition First three rank resonance amplitude curve deviation；For comparing the first rank resonance amplitude curve, when the curve that theoretical calculation obtains When in error bound curve ranges, i.e., it is believed that above-mentioned material parameter be accurately, at this time used by material parameter As recognize the final material parameter of acquisition.
Recognizing process includes:
(1) inherent characteristic and vibratory response of fiber-reinforced composite beam test specimen are solved
Firstly, establish the theoretical model of fiber-reinforced composite beam test specimen based on Classical lamination theory, and by its material Parameter is expressed as the form of complex modulus；Then, inherent characteristic and the basis of composite beam test specimen have been solved based on Ritz energy method Motivate the vibratory response of lower composite beam test specimen；
(2) test obtains first three rank intrinsic frequency and damping ratio of composite beam test specimen
The laser spot position issued by the mobile laser vibration measurer of laser scanning vibration detecting device, is at composite beam to be measured The free end position of test specimen；Then, exciting device is opened, the test of sine sweep exciting is carried out in larger frequency range, according to The time domain waveform data of acceleration transducer monitoring scanning frequency excitation signal on shaking platform, and obtained by the test of laser vibration measurer part The frequency spectrum for obtaining the vibration response signal of the free end position of composite beam test specimen to be measured, recognizes each peak value by half-power bandwidth method The frequency of corresponding frequency and half power points, and then obtain first three rank intrinsic frequency and damping ratio of composite beam test specimen to be measured；
(3) primary Calculation composite material parameter
First centered on the material parameter mean value that manufacturer provides, building material parameter vector, in a manner of permutation and combination Material parameter is iterated, when the phase for the i-th rank intrinsic frequency that the i-th rank intrinsic frequency that theoretical calculation obtains is obtained with experiment It, can primary Calculation acquisition fiber longitudinal modulus of elasticity E when being minimized to error function1, fiber transverse modulus of elasticity E2, cut Shear modulu G12With Poisson's ratio ν12；Then, it is based on modal strain energy method, passes through 3 rank modal losses before experiment acquisition composite beam test specimen Factor outcomes, primary Calculation fiber longitudinal direction fissipation factor η1, fiber lateral loss factor η2With shearing fissipation factor η12；
(4) by the lossless scanning experiment of laser, accurate test obtains first three rank resonance amplitude curve of composite beam, adjusts and swash The frequency of vibrating device is first natural frequency, and composite beam test specimen to be measured is excited to reach the first rank resonance state, flat by vibrating Acceleration transducer determines the corresponding excitation amplitude of the first rank resonance state on platform；Meanwhile opening laser scanning vibration detecting device Control switch, the laser spot position issued by the mobile laser vibration measurer of laser scanning vibration detecting device, in certain scanning speed Under, it realizes to composite beam test specimen to be measured from cantilever end position to the sweep test of free end position, obtains composite beam test specimen to be measured In the vibration response signal amplitude of each scanning point position, and then draw out the first rank resonance amplitude curve；The step is repeated, Second-order resonance amplitude curve and third rank resonance amplitude curve can successively be obtained；
(5) composite material parameter is accurately recognized
Centered on the material parameter tentatively obtained in step 3, smaller error range (such as 10%) is considered, with smaller Step-length building material parameter vector, and parameter is iterated in a manner of permutation and combination, every iteration is primary, can pass through reason The corresponding resonance amplitude curve of one group of first three rank intrinsic frequency is obtained by calculating；Then, before comparing the acquisition of certain theoretical calculation The deviation for first three rank resonance amplitude curve that the corresponding resonance amplitude curve of three rank intrinsic frequencies and test obtain；Work as theoretical calculation When the curve of acquisition is located in error bound curve ranges, i.e., it is believed that above-mentioned material parameter is accurately, to be used at this time Material parameter be recognize obtain final material parameter.

Claims (2)

1. the fibre reinforced composites parameter identification method based on the lossless scanning of laser, it is characterised in that the following steps are included:
Step 1: opening vacuum casting, adjusting screws screw rod, composite beam test specimen to be measured is successively installed on to the benchmark of clamping device Position；
Step 2: screwing screw rod by adjusting, gradually tighten the pressure of clamping device, shown according to the pressure that pressure sensor exports Number after judgement arrived suitable clamping force, stops adjusting；
Step 3: adjusting hoistable platform to suitable position, tighten vacuum casting；The gas in shell is discharged with air exhauster, manufacture Vacuum environment；
Step 4: the laser spot position issued by the mobile laser vibration measurer of laser scanning vibration detecting device is to be measured compound The free end position of beam test specimen；Then, exciting device is opened, the test of sine sweep exciting, root are carried out in larger frequency range According to the time domain waveform data for the acceleration transducer monitoring scanning frequency excitation signal being equipped on clamping device top, and pass through Laser Measuring Vibration Meter obtains the frequency spectrum of the vibration response signal of the free end position of composite beam test specimen to be measured, is recognized by half-power bandwidth method every The frequency of the corresponding frequency of a peak value and half power points, and then obtain first three rank intrinsic frequency and resistance of composite beam test specimen to be measured Buddhist nun's ratio；
Step 5: the frequency for adjusting exciting device is first natural frequency, and composite beam test specimen to be measured is excited to reach first order resonant State determines the corresponding excitation amplitude of the first rank resonance state by acceleration transducer on shaking platform；Meanwhile opening laser The control switch for scanning vibration detecting device, the laser spot position issued by the mobile laser vibration measurer of laser scanning vibration detecting device are real Composite beam test specimen to be measured now is obtained each from cantilever end position to the sweep test of free end position to composite beam test specimen to be measured Scan the vibration response signal amplitude of point position, so draw out under the first rank resonance state composite beam test specimen vibration amplitude with With the change curve of its length, referred to as the first rank resonance amplitude curve, the first rank resonance amplitude curve horizontal axis is length, The longitudinal axis is vibration amplitude；
Step 6: the frequency for adjusting exciting device is second-order intrinsic frequency and third rank intrinsic frequency, is used according to step 5 Step obtains second-order resonance amplitude curve and third rank resonance amplitude curve；
Step 7: according to fiber-reinforced composite structural material parameter identification method, inputting first three rank intrinsic frequency, damping ratio and be total to Shake amplitude curve, and setting identification error permissible value is 10%, can obtain fiber longitudinal modulus of elasticity E1, fiber transverse elasticity mould Measure E2, shear modulus G12, Poisson's ratio ν21And fiber longitudinal direction fissipation factor η11, fiber lateral loss factor η22It is damaged with shearing Consume factor η12；
The fiber-reinforced composite structural material parameter identification method is:
Vibratory response solves under fiber-reinforced composite beam test specimen inherent characteristic and basic excitation；
Composite beam test specimen is that had the characteristics that made of the fiber of orthotropy and matrix material combinations as n-layer；Assuming that each layer Between be secure bond, interlayer is without sliding, no relative displacement, admittedly can not consider the influence of proximity effects；Firstly, will Wherein xoy coordinate system as a reference plane, and is established in face；Assuming that the angle of machine direction and global coordinate system x-axis direction is θ, The a length of a of plate, plate width are b, plate thickness h, and each layer is located at the lower surface h of z coordinate axisk-1With high surfaces hkBetween, every layer of thickness It spends all the same；1 represents fiber longitudinal direction, and 2 represent fiber transverse direction, and 3 represent the direction perpendicular to 1-2 plane；
Assuming that composite beam test specimen is influenced by basic excitation load, and the movement expression formula of the basic excitation is y (t)=Yeiωt
I indicates empty unit
T indicates the time
Wherein, Y is excitation amplitude, and ω is driving frequency；
The influence for considering machine direction, is expressed as form for the elasticity modulus of composite material
Wherein,The complex modulus in parallel fibers direction and vertical fibers direction is respectively represented,It represents in 1-2 plane Complex shear modulus, E '1、E′2With G '12Complex modulus respectively And complex shear modulusReal part；And 1 direction is made It is ν with the Poisson's ratio that stress causes 1,2 directions to strain12, the Poisson's ratio that 2 direction applied stress cause 1,2 directions to strain is ν21；
The Poisson's ratio of direction strain is ν21；
Based on Classical lamination theory, the displacement field of fiber-reinforced composite beam test specimen can be written as following form
W (x, y, z, t)=w0(x,y,t)
Wherein, z indicates displacement in the z-axis direction；U, v, w represent the displacement at any point in plate；u0,v0,w0Represent face in plate Displacement；H is the thickness of composite beam test specimen；T indicates the time；
Due to being that there is no couplings for Analysis of Symmetric Laminated Plates, in plane vibration and oscillation crosswise, therefore need to only consider the oscillation crosswise of thin plate, Ignore middle face displacement components u0And v0；According to the hypothesis of Classical lamination theory it is found that normal strain εzWith shearing strain γyz、γxzAll it is 0, i.e. εz=γyz=γxz=0, by the relationship for straining and being displaced, the strain at any point can be expressed as in plate
εxIndicate the normal strain of point in the x direction
εyIndicate the normal strain of point in y-direction
εxyIndicate shearing strain of this on x/y plane
Face bending deflection rate and twisting coefficient are represented by thin plate
kxIndicate the deflection rate of point in the x direction
kyIndicate the deflection rate of point in y-direction
kxyIndicate twisting coefficient of this on x/y plane
I.e.
εx=z κx, εy=z κy, γxy=z κxy
For orthotropic material, the strain-stress relation of material major axes orientation is
1 indicates that fiber is longitudinal, and 2 indicate that fiber is lateral, and 6 indicate vertical board direction, and Q* indicates coefficient of elasticity
Wherein,
When there is certain angle theta between material major axes orientation and global coordinate system When, it is as follows that strain-stress relation of the kth laminate under global coordinate system is calculated with stress-strain rotation axis formula
Wherein,
Wherein, k indicates the kth layer of composite beam test specimen, θkIndicate the machine direction of kth laminate and the angle of global coordinate system x-axis；
Thin plate institute's bending moment and torque are
MxIndicate the moment of flexure in x-axis direction
MyIndicate the moment of flexure on y-axis direction
MxyIndicate the torque on x/y plane
D* indicates bending stiffness coefficient
Wherein,
For the ease of theory analysis modeling, basic excitation suffered by composite beam test specimen is equivalent to carry outside uniformly distributed inertia force
The displacement amplitude of Y expression basic excitation
Then the kinetic energy of thin plate vibration can be indicated with following formula
Wherein, ρ is the density of thin plate, and h is gauge of sheet；
Then the strain energy of thin plate bending storage is indicated with following formula
Uniformly distributed inertia force, which does work, suffered by thin plate is
Wq=∫ ∫Rq(t)w0dxdy
Assuming that the vibration displacement of thin plate oscillation crosswise can be expressed as
w0(x, y, t)=eiωtW(ξ,η)
Wherein, ω is the circular frequency of thin plate vibration, W identical as driving frequencyij(ξ, η) is model function of vibration, there is following form
Wherein, aijFor undetermined coefficient, pi(ξ) (i=1 ..., M) and qj(η) (j=1 ..., N) it is a series of orthogonal multinomial Formula；
A series of orthogonal polynomial is obtained by being orthogonalized processing to the polynomial function for meeting boundary condition
P1(ξ)=χ (ξ), P1(η)=κ (η)
P2(ζ)=(ζ-B2)P1(ζ)
Pk(ζ)=(ζ-Bk)Pk-1(ζ)-CkPk-2(ζ)
ζ=ξ, η, k > 2
Wherein, BkAnd CkFor coefficient function, expression formula is respectively
Wherein, W (ζ) is weight function, usually takes W (ζ)=1；And χ (ξ) and κ (η) are to meet the perimeter strips such as clamped, freely-supported, freedom The polynomial function of part, and there is following form
χ (ξ)=ξp(1-ξ)q, κ (η)=ηr(1-η)s
ξ=x/a, η=y/b
Due to being cantilever, so p=2 is taken, r=0, q=0, s=0；Formula (15) are substituted into formula (11), (12) (13) in, the maximum kinetic energy T of available composite beam test specimen vibrationmax, maximum strain energy UmaxMost with the acting of uniformly distributed inertia force Big value WqmaxRespectively
Wqmax=ρ hY ω2∫∫RWdxdy
The expression formula for defining Lagrangian energy function L is
L=Tmax+Wqmax-Umax
By making energy function L to undetermined coefficient aijPartial derivative be equal to zero, i.e.,
M × N number of Nonhomogeneous Linear algebraic equation can be obtained, in order to solve conveniently, being written as matrix form is
(K+iC-ω2M) a=F
Wherein, K, C and M are respectively structural stiffness matrix, material damping matrix and architecture quality matrix, generalized displacement vector a= (a11,a12,…aij)T, F is exciting force vector；
For the vibration problems of composite beam test specimen, only need to enable material damping Matrix C and exciting force vector F is zero, i.e.,
(K-ω2M) a=0
The intrinsic frequency and Mode Shape of composite beam test specimen can be acquired；Further, it is assumed that fiber-reinforced composite beam test specimen by The effect of basic excitation load, and solve the expression formula of its vibratory response λ (x, y, t) under basic excitation；In view of experiment test obtains What is obtained is the response of composite beam test specimen absolute vibration, that is, includes the sum of its own vibratory response and basic excitation displacement；Therefore, may be used The vibratory response λ (x, y, t) of composite beam test specimen under basic excitation is expressed as
λ (x, y, t)=y (t)+w0(x,y,t)
The solution expression formula of fiber-reinforced composite beam test specimen vibratory response under basic excitation is given, in clear basic excitation table In the case where formula and thin plate vibration response expression formula, the vibratory response for obtaining composite beam test specimen any point can be calculated；
Composite material parameter is obtained based on first three rank intrinsic frequency and damping test result primary Calculation
Firstly, the material parameter mean value provided with manufacturerCentered on, consider Rerr=10%~20% error, provides The value range of material parameter is as follows:
Suitable step-length building material parameter vector E is chosen in each value range of material parameters1,E2,G12,ν12, embody Formula are as follows:
On the basis of obtaining the theoretical intrinsic frequency with experiment respectively, relative difference on frequency function is constructed based on least square method efre:
Wherein, R is rank number of mode, Δ fiThe intrinsic frequency of the i-th rank that the i-th rank intrinsic frequency and experiment obtained for theoretical calculation obtains Rate difference,The the i-th rank intrinsic frequency obtained for experiment test；
Material parameter is iterated in a manner of permutation and combination, as least square relative error function efreWhen obtaining minimum value, I.e. primary Calculation obtains material parameter E1,E2,G12,ν12；
Then, each rank modal loss factor η can be obtained by the relationship of damping ratio and fissipation factorrFor
ηr=2 ζr
Wherein, ζrThe damping ratios obtained for experiment；
According to modal strain energy method, fiber is longitudinal, fiber transverse direction and shear direction strain energy U1、U2And U12Respectively
The fissipation factor of modal loss factor and fiber all directions has following relationship
Wherein, U is the total strain energy of composite beam test specimen；
It is found that as long as 3 rank damping ratios are as a result, primarily determine that fiber is vertical before obtaining composite beam test specimen by experiment To, the fissipation factor η of fiber transverse direction and shear direction1、η2And η12；
In this way, can be by first three rank intrinsic frequency and damping test as a result, primary Calculation obtains E1,E2,G12,ν12η1、η2And η12 Deng 7 material parameters；
Realize that the device of the method is mainly swept by compound workbench, hoistable platform, clamping device, exciting device, laser Retouch vibration measuring system and vacuum plant composition；Compound workbench includes the first workbench and the second workbench, between two platforms It is connected by " work " word supporting steel, lower section is supported by pedestal；Clamping device is for fixing and monitoring composite beam test specimen to be measured, including base The briquetting of quasi- platform and upper part, the briquetting are driven by bolt and are pushed, composite beam test specimen to be measured is fixed；It is set on reference platform Set two borehole structures, for placement force sensor round pressure sense gasket, according to the numerical value of pressure sensor come Quantitative adjustment effect realizes the quantization signifying test of constraint condition in the pressure of composite beam test specimen to be measured；Exciting device is by exciting Device and shaking platform two parts composition, effect are to generate exciting force and transmit to tested composite beam test specimen to vibrate；Vibration excitor with Signal source connection, generates the vibration of certain frequency, and vibration passes to beam test specimen to be measured by shaking platform and clamping device；For reality Now to the monitoring of excited vibration state, acceleration transducer is housed on clamping device top, for measuring the size of Oscillation Amplitude； Vibration excitor, which is bolted, to be fixed on the first workbench, to generate exciting force, and is applied it on shaking platform； There are four the damping screw rod for being evenly distributed on quadrangle below shaking platform, damping spring can be packed into damping screw rod, be realized and the One workbench is connected, and can only generate the displacement on axle of spring direction between the two；
Laser scanning vibration measuring system includes laser scanning vialog, lead screw, shaft coupling and motor；Carry laser scanning vibration measuring The platform of instrument is run through by one group of lead screw, and lead screw is connected with shaft coupling, constitutes transmission mechanism；Under the power of motor, laser The movement of vibration measurement with laser device horizontal direction can be realized by transmission mechanism by scanning vialog；The laser that laser vibration measurer issues It realizes to composite beam test specimen to be measured under certain scanning speed from cantilever end position to the scanning of free end position point position Test obtains composite beam test specimen to be measured in the vibration response signal amplitude of each scanning point position, and then draws out corresponding Resonance amplitude curve；Laser scanning vibration measuring system, which is arranged on hoistable platform, can be achieved laser scanning vialog in the vertical direction The adjustment of position, the crane of the hoistable platform are fixed on the second workbench.
2. fibre reinforced composites parameter identification method according to claim 1, it is characterised in that: in the outer of tester Portion is equipped with vacuum plant, is made of shell and baffle；Baffle is closely connect with shell, prevents air from entering；There is circle on baffle Pore structure is connected with air pump, so that gas in withdrawing device, creates vacuum environment, reduces experimental error.
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