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WO2018165999A1 - Procédé d'identification de paramètre de matériau composite renforcé par des fibres fondé sur un balayage non destructeur au laser et dispositif - Google Patents

Procédé d'identification de paramètre de matériau composite renforcé par des fibres fondé sur un balayage non destructeur au laser et dispositif Download PDF

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Publication number
WO2018165999A1
WO2018165999A1 PCT/CN2017/078513 CN2017078513W WO2018165999A1 WO 2018165999 A1 WO2018165999 A1 WO 2018165999A1 CN 2017078513 W CN2017078513 W CN 2017078513W WO 2018165999 A1 WO2018165999 A1 WO 2018165999A1
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Prior art keywords
vibration
laser
platform
excitation
composite beam
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PCT/CN2017/078513
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Chinese (zh)
Inventor
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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Northeastern University China
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Priority to JP2019548923A priority Critical patent/JP7109798B2/ja
Publication of WO2018165999A1 publication Critical patent/WO2018165999A1/fr
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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

Definitions

  • the invention relates to the field of machinery, in particular to a fiber reinforced composite material parameter identification method and device.
  • Structural composites are widely used in aviation, aerospace, marine, sports equipment due to their high specific strength, high specific modulus, designability, thermal stability, and high bearing capacity and light weight. , electrical equipment, medicine, weapons industry and chemical industry.
  • fiber reinforced composite thin-walled members such as composite blades, composite whole leaf discs and composite cylindrical shells, often work in harsh environments such as high-speed rotation, high temperature, corrosive gas erosion, etc.
  • the resulting vibration fatigue and vibration failure problems are becoming more and more prominent, making it impossible to perform the functions that people have previously envisaged.
  • Patent CN201610166104.9 invented a new type of composite material parameter identification instrument. By changing the structure of the identification instrument, the identified parameters are more accurate. However, the principle is still to measure the composite material by traditional methods such as pressing, shearing and pulling. The parameters do not fundamentally solve the waste, there are certain security risks and other issues.
  • the detection method of fiber reinforced composites needs to be improved, and the application of vibration and laser non-destructive scanning technology can solve the related problems well.
  • the present invention provides a fiber reinforced composite structural material parameter tester based on laser non-destructive scanning and a working method thereof.
  • the specific technical solutions are as follows:
  • a method for identifying a fiber reinforced composite material based on laser non-destructive scanning includes the following steps:
  • Step 1 Open the vacuum casing, adjust the tightening screw, and install the test piece of the composite beam to be tested in the reference position of the clamping mechanism in sequence;
  • Step 2 Gradually adjust the pressure of the clamping mechanism by adjusting the tightening screw, according to the pressure output by the pressure sensor After the judgment, it is judged that the appropriate clamping force has been reached, and the adjustment is stopped;
  • Step 3 Adjust the lifting platform to a suitable position, tighten the vacuum casing; exhaust the gas inside the casing with an air extractor to create a vacuum environment;
  • Step 4 The position of the laser spot emitted by the laser vibrometer is moved by the laser scanning vibration measuring device to be in the free end position of the composite beam test piece to be tested; then, the excitation device is turned on, and the sine sweep is performed in a large frequency range.
  • the frequency excitation test monitors the time domain waveform data of the frequency sweep excitation signal according to the acceleration sensor on the movable clamp body, and obtains the spectrum of the vibration response signal of the free end position of the composite beam test piece to be tested by the laser vibration meter, and passes the half power
  • the bandwidth method identifies the frequency corresponding to each peak and the frequency of the half power point, thereby obtaining the first three natural frequencies and damping ratios of the composite beam specimen to be tested;
  • Step 5 Adjust the frequency of the excitation device to the first-order natural frequency, and the excitation composite beam test piece reaches the first-order resonance state, and the excitation amplitude corresponding to the first-order resonance state is determined by the acceleration sensor on the vibration platform; meanwhile, the laser is turned on.
  • the control switch of the scanning vibration measuring device moves the position of the laser spot emitted by the laser vibrometer by the laser scanning vibration measuring device, and realizes the scanning test of the test piece of the composite beam from the cantilever end position to the free end position, and obtains the composite beam test to be tested.
  • the amplitude of the vibration response signal at each scanning point position, and then the curve of the vibration amplitude of the composite beam specimen with the length of the first-order resonance state is plotted as a first-order resonance amplitude curve.
  • the horizontal axis of the first-order resonance amplitude curve is the length, and the vertical axis is the vibration amplitude;
  • Step 6 adjusting the frequency of the excitation device to the second-order natural frequency and the third-order natural frequency, and illuminating the steps used in step 5 to obtain a second-order resonance amplitude curve and a third-order resonance amplitude curve;
  • Step 7 According to the parameter identification method of the fiber reinforced composite structural material, input the first three natural frequencies, the damping ratio and the resonance amplitude curve, and set the allowable value of the recognition error to 10% to obtain the longitudinal elastic modulus E 1 of the fiber and the transverse elasticity of the fiber.
  • the modulus E 2 , the shear modulus G 12 , the Poisson's ratio is ⁇ 21 and the fiber longitudinal loss factor ⁇ 11 , the fiber transverse loss factor ⁇ 22 and the shear loss factor ⁇ 12 .
  • the invention further discloses a device for realizing the method, which is mainly composed of a double working platform, a lifting platform, a clamping mechanism, an excitation device, a laser scanning vibration measuring system and a vacuum device;
  • the double working platform comprises a first working platform And the second working platform, the two platforms are supported by the "work" word supporting steel, and the bottom is supported by the base;
  • the clamping mechanism is used for fixing and monitoring the composite beam test piece to be tested, including the reference platform and the upper pressing block thereof, The pressure block is driven by bolts to fix the composite beam test piece to be tested;
  • two circular hole structures are arranged on the reference platform for placing the circular pressure sensing gasket of the pressure sensor, and quantitatively adjusting according to the value of the pressure sensor Acting on the pressure of the tested composite material, the quantitative characterization test of the constraint condition is realized;
  • the excitation device consists of two parts: the vibration exciter and the vibration platform, the function of which is to generate the excitation force and transmit the vibration to the test piece of the
  • the laser scanning vibration measuring system comprises a laser scanning vibrometer, a lead screw, a coupling and an electric motor; the platform carrying the laser scanning vibrometer is penetrated by a set of lead screws, and the lead screw is connected with the coupling to form a transmission mechanism; Under the power of the motor, the laser scanning vibrometer can realize the horizontal movement of the laser vibration measuring device through the transmission mechanism; the position of the laser spot emitted by the laser vibrometer can realize the test specimen of the composite beam from the cantilever at a certain scanning speed.
  • the scanning test from the end position to the free end position obtains the amplitude of the vibration response signal of the composite beam test piece at each scanning measuring point position, and then draws a corresponding resonance amplitude curve; the laser scanning vibration measuring system is arranged on the lifting platform
  • the adjustment of the position of the laser scanning vibrometer in the vertical direction can be realized, and the lifting frame of the lifting platform is fixed on the second working platform.
  • a vacuum device is arranged outside the tester, which is composed of a casing and a baffle; the baffle is tightly connected with the casing to prevent air from entering; and the baffle has a circular hole structure connected to the air pump to extract the gas inside the device, thereby creating Vacuum environment reduces experimental error.
  • An advantage of the present invention is that the present invention provides a fiber reinforced composite structural material parameter tester based on laser non-destructive scanning.
  • the parameter test method combining vibration transmission and laser displacement sensing technology was designed, which broke the traditional measurement mode by stretching and other physical methods, and achieved the goal of measuring the mechanical properties of the material to be tested in all directions at one time.
  • the earth reduces the workload of related work;
  • the instrument does not have any impact on the material during the whole process of testing, saves raw materials, reduces economic losses, and is more environmentally friendly; in addition, the external vacuum housing design makes The test process is carried out under vacuum, avoiding the influence of air damping, and the measurement result is more accurate.
  • the work is easy to assemble and disassemble, and the quality of each component is not large, and can be loaded into the pull box for better portability. .
  • the parameters of the composite materials can be measured at different locations according to actual conditions, which provides great convenience for production measurement.
  • FIG. 1 is a front elevational view of a fiber reinforced composite structural material parameter tester according to an embodiment of the present invention
  • FIG. 2 is a top plan view of a fiber reinforced composite structural material parameter tester according to an embodiment of the present invention
  • FIG. 3 is a schematic structural diagram of a fiber reinforced composite structural material parameter tester according to an embodiment of the present invention.
  • Figure 4 is a theoretical model of the fiber reinforced composite beam specimen under the basic excitation of Figure 1;
  • Figure 5 is a theoretical and experimental obtained first-order resonance amplitude curve of the composite beam and its error upper and lower limits
  • the device of the present invention mainly comprises a double working platform, a lifting platform, a clamping mechanism, an excitation device, a laser scanning vibration measuring system and a vacuum device;
  • the compound working platform comprises a first working platform 4 and a second working platform 2, wherein the two platforms are connected by the "work" word supporting steel 3, and the lower part is supported by the base 1;
  • the clamping mechanism 8 is used for fixing and monitoring the composite beam test piece to be tested 15, comprising a reference platform 17 and an upper pressing block 18, the pressing block is driven by a bolt to press the composite beam test piece to be tested;
  • the upper surface of the reference platform 17 is provided with two circular hole structures for placing a circular pressure sensing gasket of the pressure sensor, and quantitatively adjusting the pressure acting on the composite material according to the value of the pressure sensor to realize quantitative characterization of the constraint condition. test.
  • the excitation device is composed of two parts, the vibration exciter 16 and the vibration platform 5, and the function is to generate an excitation force and transmit vibration to the test piece of the composite beam to be tested; the vibration exciter is connected with the signal source to generate vibration of a certain frequency, and the vibration passes through the vibration.
  • the platform 5 and the clamping mechanism 8 are transmitted to the beam test piece 15 to be tested; in order to realize the monitoring of the excitation vibration state, an acceleration sensor 9 is mounted on the upper portion of the clamping mechanism 8 for measuring the magnitude of the vibration amplitude.
  • the vibration exciter 16 is fixed to the first working platform 4 by bolt connection for generating an excitation force and applying it to the vibration platform 5; under the excitation platform 5, there are four shock-absorbing screws uniformly distributed at the four corners, The shock spring 6 can be inserted into the shock absorbing screw to be connected with the second working platform 2, and only the displacement in the direction of the spring axis can be generated between the two.
  • the laser scanning vibration measuring system includes a laser scanning vibrometer 11, a lead screw 10, a coupling, and an electric motor.
  • the platform carrying the laser scanning vibrometer is penetrated by a set of lead screws, and the lead screw is connected with the coupling to form a transmission mechanism; under the power of the motor, the laser scanning vibrometer can realize the horizontal direction of the laser vibration measuring device through the transmission mechanism. exercise.
  • the laser spot position of the laser vibrometer is used to scan the test specimen from the cantilever end position to the free end position at a certain scanning speed, and obtain the position of the composite beam test piece to be tested at each scanning point.
  • the vibration responds to the amplitude of the signal, which in turn plots the corresponding resonance amplitude curve.
  • the laser scanning vibration measuring system is disposed on the lifting platform 14 to adjust the position of the laser scanning vibrometer in the vertical direction.
  • the lifting platform of the lifting platform 14 is fixed on the second working platform 2, and the two cross-hinged Supporting beams, one fixed on the working platform 2, the other one is connected with the sliding block 13, and the sliding block is connected with the motor through the screw; under the driving of the motor, the screw drives the sliding block 13 to slide on the working platform to drive the lifting The platform moves up and down;
  • a vacuum device is provided on the outside of the tester, which is composed of a casing and a baffle.
  • the baffle can be tightly connected to the casing to prevent air from entering; the baffle has a circular hole structure that can be connected to the air pump to extract gas from the device, create a vacuum environment, and reduce experimental errors.
  • the fiber reinforced composite structural material parameter identification method is:
  • the composite beam specimen is composed of n layers of fibers with orthogonal anisotropy characteristics and matrix materials; assuming that the layers are firmly bonded, there is no slip between the layers, no relative displacement, solid can be ignored
  • the effect of the interlayer coupling effect first, the midplane is used as the reference plane, and the xoy coordinate system is established; the angle between the fiber direction and the x-axis direction of the global coordinate system is ⁇ , the plate length is a, the plate width is b, and the plate thickness is For h, each layer is located between the lower surface h k-1 of the z coordinate axis and the higher surface h k , and the thickness of each layer is the same; 1 in the figure represents the longitudinal direction of the fiber, 2 represents the transverse direction of the fiber, and 3 represents the vertical direction. 1-2 plane direction;
  • i a virtual unit
  • the elastic modulus of the composite material is expressed as follows
  • the Poisson's ratio of the directional strain is ⁇ 21 ;
  • z represents the displacement in the z-axis direction
  • u, v, w represents the displacement of any point in the plate
  • u 0 , v 0 , w 0 represents the surface displacement of the plate
  • h is the thickness of the composite beam test piece
  • t represents time
  • ⁇ x represents the positive strain of the point in the x direction
  • ⁇ y represents the positive strain of the point in the y direction
  • ⁇ xy indicates the shear strain of the point on the xy plane
  • the bending curvature and the twist rate of the middle surface of the thin plate can be expressed as
  • k x represents the flexural curvature of the point in the x direction
  • k y represents the flexural curvature of the point in the y direction
  • k xy represents the distortion rate of the point on the xy plane
  • ⁇ x z ⁇ x
  • ⁇ y z ⁇ y
  • ⁇ xy z ⁇ xy
  • 1 indicates the longitudinal direction of the fiber
  • 2 indicates the transverse direction of the fiber
  • 6 indicates the direction of the vertical plate surface
  • Q* indicates the elastic modulus
  • the stress-strain relationship of the k-th layer in the global coordinate system is calculated by the stress-strain rotation formula.
  • k represents the k-th layer of the composite beam test piece
  • ⁇ k represents the angle between the fiber direction of the k-th layer plate and the x-axis of the global coordinate system
  • M x represents the bending moment in the x-axis direction
  • M y represents the bending moment in the y-axis direction
  • M xy represents the torque on the xy plane
  • D* represents the bending stiffness coefficient
  • the basic excitation of the composite beam specimen is equivalent to the uniform inertial force external load.
  • the kinetic energy of the vibration of the thin plate can be expressed by the following formula
  • ⁇ is the density of the thin plate and h is the thickness of the thin plate
  • the strain energy stored in the bending of the thin plate is expressed by the following formula
  • the uniform inertial force of the thin plate is the uniform inertial force of the thin plate.
  • W ij ( ⁇ , ⁇ ) is a vibration mode function, and has the following form
  • M ⁇ N non-homogeneous linear algebraic equations can be obtained. For the convenience of solving, write it as a matrix form.
  • the natural frequency and mode shape of the composite beam specimen can be obtained; further, it is assumed that the fiber reinforced composite beam specimen is subjected to the basic excitation load and the vibration response ⁇ (x, y) is solved under the fundamental excitation. , t) expression; taking into account the experimental test to obtain the absolute vibration response of the composite beam specimen, that is, including the sum of its own vibration response and the base excitation displacement; therefore, the vibration response of the composite beam specimen under the foundation excitation ⁇ (x, y, t) is expressed as
  • Equation (26) gives the expression of the vibration response of the fiber reinforced composite beam specimen under the basic excitation.
  • the composite can be calculated. The vibration response of the beam test piece at any point;
  • R is the modal order
  • ⁇ f i is the theoretically calculated ith order natural frequency and the experimentally obtained ith order natural frequency difference, The i-th order natural frequency obtained for the experimental test;
  • the material parameters are iterated in a manner of arrangement and combination.
  • the least squares relative error function e fre takes a minimum value
  • the material parameters E 1 , E 2 , G 12 , ⁇ 12 are obtained by preliminary calculation;
  • ⁇ r is the modal damping ratio obtained by the experiment.
  • the strain energies U 1 , U 2 and U 12 of the fiber longitudinal direction, the fiber transverse direction and the shear direction are respectively
  • the modal loss factor and the loss factor in all directions of the fiber have the following relationship
  • the first three natural frequencies and damping ratios of the composite beam specimens are obtained through experimental tests, and the composite beam specimens are excited to reach the resonance state by the above-mentioned natural frequencies, and then the first three-order resonance amplitudes of the composite beams are obtained by laser non-destructive scanning experiments.
  • the identification process includes:
  • the position of the laser spot emitted by the laser vibrometer is moved by the laser scanning vibration measuring device to be at the free end position of the test piece of the composite beam to be tested; then, the excitation device is turned on, and the sine sweep excitation is performed in a large frequency range.
  • Test monitor the time domain waveform data of the sweep excitation signal according to the acceleration sensor on the vibration platform, and obtain the spectrum of the vibration response signal of the free end position of the test specimen to be tested by the laser vibration measuring instrument, and pass the half power bandwidth
  • the method identifies the frequency corresponding to each peak and the frequency of the half power point, thereby obtaining the first three natural frequencies and damping ratios of the composite beam specimen to be tested;
  • the material parameter vector is constructed with the mean value of the material parameters provided by the manufacturer, and the material parameters are iterated in a way of arrangement and combination.
  • the relative error function of the i-th natural frequency obtained by theoretical calculation and the experimentally obtained i-th natural frequency is obtained.
  • the longitudinal elastic modulus E 1 , the transverse elastic modulus E 2 , the shear modulus G 12 and the Poisson's ratio ⁇ 12 of the fiber can be preliminarily calculated.
  • the experiment is obtained.
  • the results of the third-order modal loss factor of the composite beam specimen were calculated, and the longitudinal loss factor ⁇ 1 , the transverse loss factor ⁇ 2 and the shear loss factor ⁇ 12 were calculated.
  • the first three-order resonance amplitude curve of the composite beam is obtained by accurate test, and the frequency of the excitation device is adjusted to the first-order natural frequency, and the test beam of the composite beam is excited to reach the first-order resonance state, and the vibration is passed.
  • the acceleration sensor on the platform determines the excitation amplitude corresponding to the first-order resonance state; at the same time, the control switch of the laser scanning vibration measuring device is turned on, and the position of the laser spot emitted by the laser vibrometer is moved by the laser scanning vibration measuring device at a certain scanning speed.
  • step size constructs the material parameter vector and iterates the parameters in a permutation and combination manner.
  • a set of resonance amplitude curves corresponding to the first three natural frequencies can be obtained by theoretical calculation; then, a theoretical calculation is obtained.
  • the material parameters used at the time are the final material parameters obtained by the identification.

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Abstract

L'invention concerne un procédé d'identification de paramètre de matériau composite renforcé par des fibres basé sur un balayage non destructeur au laser. Le procédé consiste : à introduire une première fréquence naturelle d'ordre trois, un rapport d'amortissement et une courbe d'amplitude de résonance et à régler une valeur d'erreur autorisée d'identification à 10 %, de sorte que le module d'élasticité longitudinale de fibre E 1, le module d'élasticité transversale de fibre E 2, le module de cisaillement G 12, le coefficient de Poisson ν 21, le facteur de perte longitudinal de fibre η 22, le facteur de perte transversale de fibre η 22 et le facteur de perte de cisaillement η 12 soient obtenus. L'invention concerne également un dispositif permettant de mettre en œuvre ledit procédé. Le procédé combine une transmission de vibration avec une technologie de détection de déplacement au laser afin d'obtenir une mesure en une fois des propriétés mécaniques du matériau de test dans toutes les directions, ce qui permet de réduire la charge de travail associée.
PCT/CN2017/078513 2017-03-16 2017-03-29 Procédé d'identification de paramètre de matériau composite renforcé par des fibres fondé sur un balayage non destructeur au laser et dispositif Ceased WO2018165999A1 (fr)

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JP2019548923A JP7109798B2 (ja) 2017-03-16 2017-03-29 非破壊のレーザー走査による繊維強化複合材料パラメータ同定の方法及び装置

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CN201710155498.2A CN106950280B (zh) 2017-03-16 2017-03-16 基于激光无损扫描的纤维增强复合材料参数辨识方法
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