• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A method of non-destructive ultrasonic testing of a bonded assembly (1), it comprises two steps consisting of measuring a thickness of an adhesive joint (7) of the bonded assembly (1) by means of an ultrasonic transducer ( 9) disposed on the glued assembly (1) in a determined position, and measuring the adhesion level of pieces of the bonded assembly (1) by means of the same ultrasonic transducer (9) held in said determined position, the level adhesion being measured using Lamb waves at ZGV (13).
    公开号:FR3057957A1
    申请号:FR1660355
    申请日:2016-10-25
    公开日:2018-04-27
    发明作者:Loic Ducousso Mathieu；Nicolas Cuvillier
    申请人:Safran SA；
    IPC主号:
    专利说明:

    TECHNICAL FIELD The present invention relates to a non-destructive testing process (CND) of an anisotropic multilayer medium, composite type, and in particular a quantitative monitoring process for the level of adhesion of an adhesive joint of a bonded assembly intended to withstand mechanical stress.
    STATE OF THE ART [0002] Composite materials offer numerous advantages over metallic materials conventionally used in the aeronautical field. Among the advantages of these composite materials, one can cite their high stiffness / mass ratio, their good resistance to fatigue and to corrosion, and the good adaptability of their mechanical properties to the specific stresses they encounter during their use.
    The use of composite materials therefore allows a significant reduction in structures. For example, in civil aviation, the use of composite materials allows a reduction in the mass of parts by 20% for an equal or even greater structural stiffness. This leads to an estimated saving of 6% on the total weight of the aircraft, equivalent to significant fuel savings.
    However, composite materials, by their intrinsic characteristics, hardly support bolting or riveting and cannot be welded. They therefore need to be glued to be assembled. To meet safety standards, these assembled structures must be inspected regularly and reliably, with a diagnostic to quantify the mechanical strength of the bonded assembly. In this context, the ability to quickly assess the condition of a structure assembled by bonding presents difficulties: it is necessary to partially disassemble certain members to allow access to internal structures, thus requiring an inspected aircraft to be immobilized in the workshop. Although there are many non-destructive evaluation methods, the simplest being probably visual inspection, current conventional methods do not allow a real quantification of the mechanical strength of a bonded assembly.
    In the absence of an appropriate method to quantitatively control the quality of bonding, it is difficult (if not impossible) to measure the level of adhesion of these assembled structures, and thus to test, prove and guarantee their quality and reliability. This prevents a generalization of bonding techniques as a means of assembly and therefore a generalization of the use of structural parts made of composite materials in the aeronautical industry.
    To overcome this lack, NDT techniques performed using ultrasonic waves have been studied for a few years. Being mechanical waves, these waves would be the most likely to probe a mechanical behavior (or level of adhesion). In recent years, studies have focused in particular on a category of ultrasonic waves, Lamb waves at zero group speed (Lamb Waves at ZGV).
    In a medium of finite thickness (case of a plate in a vacuum, for example) two surface waves can propagate without interacting on each of the free interfaces as long as the thickness of the plate is large compared to the length wave λ of the surface wave. When the thickness of the plate is of the same order of magnitude as λ, other waves appear which result from the coupling of the different partial waves to the solid / vacuum interfaces of the plate. These plate waves, the Lamb waves, are dispersive and have the particularity of creating a displacement field in the entire thickness of the structure.
    Leaking Lamb waves are called a special case of Lamb waves propagating in the structure from the place of their generation; as opposed to Lamb waves at zero group speed (Lamb Waves at ZGV) whose acoustic energy remains confined under the place of acoustic generation.
    Conventionally and known per se, the study of the propagation of Lamb waves requires the calculation of the dispersion curves, which can be represented by the phase velocity profiles as a function of a frequency-thickness product.
    Non-destructive testing of plates and tubes of glued assemblies can thus be ensured by leaking Lamb waves propagating in the environment studied. In a manner known per se, for a given material, there is a set of wave resonances from Lamb to ZGV and their detection provides an absolute and local measure of the Poisson's ratio. These non-propagative modes can thus be exploited to characterize multilayer structures.
    PRESENTATION OF THE INVENTION This application for invention proposes a new method for carrying out a non-destructive and quantitative evaluation of collages using, in particular, leaking Lamb waves or Lamb waves at ZGV.
    Thus, the present invention relates to a non-destructive ultrasonic testing process for a bonded assembly, characterized in that it comprises the steps consisting in:
    - measure a thickness of an adhesive joint of the bonded assembly by means of an ultrasonic transducer placed on the bonded assembly in a determined position,
    - measure the level of adhesion of parts of the bonded assembly by means of the same ultrasonic transducer maintained in said determined position, the level of adhesion being measured by means of waves from Lamb to ZGV.
    This method thus allows with a single transducer to measure the thickness of the adhesive joint in the bonded assembly and to quantify its mechanical strength (level of adhesion). These two parameters are essential to guarantee the correct design of a bonded assembly. To do this, the method proposes an innovative use of the transducer: the characterization of mechanical strength (level of adhesion) of the bonded assembly by waves of Lamb to ZGV is possible by means of the knowledge of the thicknesses considered in the bonded assembly, in especially that of the glue joint. However, the first step of the process consists precisely in measuring this thickness. This new use of the transducer therefore makes it possible to carry out the two measurements successively without touching the experimental device. Control is then very simple and quick to perform in an industrial environment.
    The method according to the invention may include one or more of the following characteristics, taken in isolation from one another or in combination with each other:
    - the procedure can measure the thicknesses of different layers of the bonded structure by means of an ultrasonic transducer placed on the bonded assembly in a determined position, the ultrasonic transducer is a multi-element transducer, the thickness of the joint is measured at by means of an acoustic time-of-flight measurement method in reflection, at least two emitting elements of the transducer are used to emit waves from Lamb to ZGV in the adhesive joint and are spatially positioned so as to create a so-called periodic spatial comb sliding, and in which at least one other element of the transducer is used to acquire the waves of Lamb to ZGV emitted,
    - the acquisition is made in the temporal and spatial domain so as to obtain dispersion curves intended to be compared with a simulation model allowing the modeling of parameters of the level of adhesion or with an abacus of dispersion curves taking into account the thicknesses of the assembly and the quantification of the mechanical strength of the bonding, this comparison making it possible to quantify the mechanical strength of the bonded assembly,
    - the dispersion curves are obtained by inversion of the waves detected according to a Bi-FFT approach or a decomposition method in singular values (SVD), the acquisition of waves from Lamb to ZGV is made, in particular, in the time domain of so as to obtain a B-scan type image of the ultrasonic signal of the Lamb waves at ZGV.
    the wave dispersion curves from Lamb to ZGV associated with the recorded B-Scans are obtained either by simple Bi-FFF from the B-scan or by a so-called singular value decomposition (SVD) approach.
    the dispersion curves thus obtained are intended to be compared with a simulation model allowing the modeling of parameters of the level of adhesion, and several sliding combs are successively created to successively generate different ZGV modes, the parameters of each level of adhesion as well measured being used to superimpose the simulations on the experiments and thus measure the level of adhesion of the adhesive joint.
    DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will appear more clearly on reading the following description given by way of non-limiting example and with reference to the accompanying drawings in which :
    FIG. 1 is a diagram illustrating the course of the first step of a method according to the invention carried out by means of a method of measuring acoustic flight time in reflection, FIG. 2 is a diagram illustrating the course of the second step of a method according to the invention, FIG. 3 is an acquisition diagram with a sliding comb necessary for obtaining the dispersion curves to observe the modes at ZGV of the Lamb waves considered.
    DETAILED DESCRIPTION [0016] We now refer to Figures 1. It shows a sample of a bonded assembly 1 subjected to the first step of the process described. The bonded assembly 1 is an assembly composed of a first layer 3 consisting of a first composite material and a second layer 5 consisting of the same or a second composite material or not, assembled together by an adhesive joint 7.
    An ultrasonic device 9 is placed in contact with the bonded assembly sample 1. In fact, the ultrasonic device 9 of the example illustrated is a multi-element ultrasonic transducer 9 operating on contact. The intrinsic characteristics of the transducer 9 (flat or flexible, number of elements 11, dimensions, central frequency, etc.) may differ depending on the bonded assembly 1 considered to optimize the generation / detection of the physical phenomena involved, in particular the transmission and acquisition of an ultrasonic signal 12 transmitted. The whole process is carried out by putting a single multi-element transducer 9 11 in contact with the glued assembly 1. This transducer 9 is used for the whole process (the two stages) and is not moved before the end of the process.
    The first step of the method is intended to measure the thickness of the adhesive joint 7 of the bonded assembly 1 using the emission and the acquisition of an ultrasonic signal 12. This first step is performed using a conventional pulse / echo and time of flight measurement method.
    Figure 1 this step. It consists in carrying out an acoustic time-of-flight measurement in reflection, t1, t2. This approach is well described in the UT COSAC procedures. It is a question of measuring the time t1, t2 necessary for a return acoustic journey and, knowing the acoustic speed in the materials 3, 5, 7 traveled, it is easy to quantify the thicknesses e1, e2 of the materials 3, 5 , 7 under the transducer 9. This method is applicable to a multi-element transducer 9.
    Figures 2 and 3 illustrate the operation of the second step of the process. This second step is a measurement of adhesion by Lamb waves to ZGV 13. Lamb waves to ZGV 13 are ultrasonic resonances of structures which remain confined under the source of excitation. The energy of these waves 13 is therefore very little dissipated spatially and these waves 13 have a long lifespan and a strong interaction with matter. As mentioned above, it has been shown that these waves 13 can make it possible to probe the quality of a bonded assembly 1 by means of knowing the characteristic thicknesses of the different layers of the bonded assembly 1. It is therefore necessary to know the thickness of the adhesive joint 7. This thickness is known from the first step of the process.
    These waves 13 are difficult to emit / detect and to date, only laser ultrasound has allowed them to emit / detect. Thus, to generate the Lamb modes at ZGV 13 in the bonded assembly 1, the method uses the same multi-element transducer 9 as that used to carry out the first step of the method. The second step of the method is carried out just after the thickness measurement of the adhesive joint 7 and the transducer 9 has neither been touched nor moved between the two steps of the method.
    Part of the elements 11 of the transducer 9 is used as transmitting elements 15 and the other part of the elements 11 is used in reception mode.
    To optimize the generation of Lamb modes at ZGV 13, the elements 15 of the transducer 9 working in emission mode are spatially positioned so that they create a spatially periodic excitation (along the Z axis parallel to the different layers of materials 3, 5, 7 of the bonded assembly 1), as illustrated in FIGS. 2 and 3. This spatially periodic excitation according to Z is called "a spatial generation comb".
    The comb period is chosen to correspond to the wavelength of the ZGV mode of the Lamb waves to ZGV 13 desired. The emitting elements 15 of the transducer 9 therefore have a comb-shaped spatial distribution, distributed over the entire surface of the transducer 9. The other elements 11 of the multi-element transducer 9 operate in reception mode and record a signal resolved in time.
    The acquisition 17 is made in the time domain for each element 11 and makes it possible to obtain an image in B-Scan mode of the propagation of the ultrasonic signal 19. A mathematical transformation in the reciprocal space (wavelength and ultrasonic frequencies) is then carried out to obtain dispersion curves of the Lamb waves at ZGV 13 emitted by the transmitting element 15. The transformation is preferably done using a mathematical approach SVD (Singular Value Decomposition) but can also be carried out in using a simple mathematical approach called bi-FFT. To be reversed using an SVD approach, the comb must be sliding, as illustrated in FIG. 5. That is to say that during each acquisition 17, the emitting elements 15 change position. Hatched, there is shown, for each transmission / acquisition 17, the transmitter element 15 while the receiver elements 11 are shown in white.
    The dispersion curves are obtained in the same way as during the first step by carrying out a reverse transformation of the signal 13, according to a mathematical approach which can be Bi-FFT or SVD. To be reversed using an SVD approach, the comb must be slippery, as shown in Figure 3.. In other words, during each acquisition 17, the emitting elements 15 change position.
    The dispersion curves of the modes of Lamb to ZGV 13 are then used by comparison with a simulation model where an interface stiffness (level of adhesion) is modeled. Several different combs can be successively created to successively generate different ZGV modes.
    The parameters of the interface stiffness are used to superimpose the simulations on the experiments and thus measure these levels of adhesion which include a signature of the quality of the bonding produced and therefore of the reliability of the adhesive joint 7 and therefore of the bonded assembly 1.
    权利要求:
    Claims (7)
    [1" id="c-fr-0001]
    1. A method of non-destructive ultrasonic testing of a bonded assembly (1), characterized in that it comprises the stages consisting in:
    - measure a thickness of an adhesive joint (7) of the bonded assembly (1) by means of an ultrasonic transducer (9) disposed on the bonded assembly (1) in a determined position,
    - measure the level of adhesion of parts of the bonded assembly (1) by means of the same ultrasonic transducer (9) maintained in said determined position, the level of adhesion being measured by means of waves from Lamb to ZGV (13 ).
    [2" id="c-fr-0002]
    2. Method according to the preceding claim, wherein the ultrasonic transducer (9) is a multi-element transducer (11).
    [3" id="c-fr-0003]
    3. Method according to one of the preceding claims, in which the thickness measurement of the adhesive joint (7) is carried out by means of a method of measuring acoustic flight time in reflection.
    [4" id="c-fr-0004]
    4. Method according to any one of the preceding claims, in which at least one emitting element (15) of the transducer (9) is used to emit waves from Lamb to ZGV (13) in the adhesive joint (7) and is spatially positioned so as to create a so-called sliding periodic space comb, and in which at least one other element (11) of the transducer (9) is used to acquire (17) the waves of Lamb to ZGV (13) emitted.
    [5" id="c-fr-0005]
    5. Method according to the preceding claim, wherein the acquisition (17) is made in the time and space domain so as to obtain dispersion curves intended to be compared with a simulation model allowing the modeling of parameters of the level of adhesion or with an abacus of dispersion curves.
    [6" id="c-fr-0006]
    6. Method according to the preceding claim wherein the dispersion curves are obtained by inversion of the waves (19, 13) detected according to a BiFFT approach or a decomposition method into singular values (SVD).
    [7" id="c-fr-0007]
    7. Method according to the preceding claim, in which several sliding combs are successively created to successively generate different ZGV modes, the parameters of each level of adhesion thus measured being
    5 used to superimpose the simulations on the experiments and thus measure the level of adhesion of the adhesive joint (7).
    1/1
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    WO2018078272A1|2018-05-03|
    US11047829B2|2021-06-29|
    CN109964122A|2019-07-02|
    FR3057957B1|2018-11-02|
    CA3041166A1|2018-05-03|
    RU2019114195A|2020-11-27|
    JP2019531484A|2019-10-31|
    RU2742230C2|2021-02-03|
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    引用文献:
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    FR3097315A1|2019-06-17|2020-12-18|Safran Aircraft Engines|NON-DESTRUCTIVE CONTROL PROCESS OF A GLUED ASSEMBLY|SU1019312A1|1981-07-10|1983-05-23|Предприятие П/Я Р-6209|Method of ultrasonic checking of glued articles of dielectric materials|
    SU1427292A1|1986-12-16|1988-09-30|Кемеровский государственный университет|Method of checking adhesive joints|
    SU1439489A1|1987-04-20|1988-11-23|Кемеровский государственный университет|Method of inspecting glued joints of composite articles|
    US4944185A|1989-01-17|1990-07-31|Westinghouse Electric Corp.|System and method for qualitatively and nondestructively inspecting adhesive joints and other materials|
    US6843130B2|2002-12-03|2005-01-18|The Boeing Company|System and method for the inspection of adhesive|
    US7798000B1|2005-10-28|2010-09-21|Trustees Of Boston University|Non-destructive imaging, characterization or measurement of thin items using laser-generated lamb waves|
    US8087298B1|2009-03-10|2012-01-03|Sandia Corporation|Ultrasonic probe deployment device for increased wave transmission and rapid area scan inspections|
    RU2451289C2|2009-12-24|2012-05-20|Открытое акционерное общество "АВТОВАЗ"|Method of detecting defects in adhesive joints and apparatus for realising said method|
    JP6067590B2|2011-02-25|2017-01-25|メイヨ フォンデーシヨン フォー メディカル エジュケーション アンド リサーチ|Ultrasonic vibration method using unfocused ultrasonic waves|
    US9507464B2|2013-03-15|2016-11-29|Elo Touch Solutions, Inc.|Acoustic touch apparatus and methods using touch sensitive lamb waves|
    US20180340858A1|2017-05-23|2018-11-29|The Boeing Company|Application of Ultrasonic Guided Waves for Structural Health Monitoring of Bonded Joints|WO2020130150A1|2018-12-21|2020-06-25|三菱重工業株式会社|Adhesive layer evaluation system and adhesive layer evaluation method|
    CN110109124B|2019-05-28|2021-02-09|中国科学院声学研究所|Device and method for sensing target at bottom of solid plate based on leaky lamb wave|
    法律状态:
    2017-09-20| PLFP| Fee payment|Year of fee payment: 2 |
    2018-04-27| PLSC| Search report ready|Effective date: 20180427 |
    2018-09-19| PLFP| Fee payment|Year of fee payment: 3 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 4 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 5 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1660355|2016-10-25|
    FR1660355A|FR3057957B1|2016-10-25|2016-10-25|METHOD FOR NON-DESTRUCTIVE CONTROL OF A GLUE ASSEMBLY|FR1660355A| FR3057957B1|2016-10-25|2016-10-25|METHOD FOR NON-DESTRUCTIVE CONTROL OF A GLUE ASSEMBLY|
    CN201780069707.XA| CN109964122A|2016-10-25|2017-10-24|Method for carrying out nondestructive inspection by component of the ultrasound to bonding|
    RU2019114195A| RU2742230C2|2016-10-25|2017-10-24|Method of non-destructive ultrasonic inspection of adhesive joint|
    JP2019521410A| JP6932187B2|2016-10-25|2017-10-24|Ultrasonic non-destructive inspection method for joined assemblies|
    US16/343,893| US11047829B2|2016-10-25|2017-10-24|Method for nondestructive inspection by ultrasound of a bonded assembly|
    CA3041166A| CA3041166A1|2016-10-25|2017-10-24|Method for nondestructive inspection by ultrasound of a bonded assembly|
    BR112019008167A| BR112019008167A2|2016-10-25|2017-10-24|non-destructive ultrasonic control process of a bonded set|
    PCT/FR2017/052926| WO2018078272A1|2016-10-25|2017-10-24|Method for nondestructive inspection by ultrasound of a bonded assembly|
    EP17797405.2A| EP3532832A1|2016-10-25|2017-10-24|Method for nondestructive inspection by ultrasound of a bonded assembly|
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