CN112147071A - Composite material interface bonding force detection method based on laser pulse waveform regulation and control - Google Patents
Composite material interface bonding force detection method based on laser pulse waveform regulation and control Download PDFInfo
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Abstract
The invention provides a composite material interface bonding force detection method based on laser pulse waveform regulation, which comprises the following steps: calculating laser shock wave pressure time distribution curves under different laser pulse waveforms on the basis of a nanosecond laser induced shock wave pressure model; establishing a composite material laser shock wave dynamic propagation numerical simulation model to obtain the influence rule of different laser pulse waveforms on the maximum coupling tensile stress position; reversely determining a laser shock wave pressure time distribution curve required by detection according to the position of a bonding interface of the composite material to be detected; combining a nanosecond laser induced shock wave pressure model, and reversely solving required laser pulse waveform parameters; and setting parameters of a pulse laser through a pulse waveform modulator, and performing a laser shock test on the composite material to be detected so as to finish the detection of the interface bonding force of the composite material. The invention regulates and controls the position of the maximum coupling tensile stress in the material by regulating and controlling the laser pulse waveform so as to complete the detection of the bonding force of bonding interfaces at different depths.
Description
Technical Field
The invention belongs to the technical field of laser application and nondestructive testing of composite materials, and particularly relates to a composite material interface bonding force detection method based on laser pulse waveform regulation.
Background
The fiber reinforced composite material is widely applied to the field of aerospace, and the mechanical property of the composite material is reduced due to the fact that fiber fracture, matrix cracking, layering damage and the like are easily caused by drilling in the process of riveting and bolting the composite material, so that the composite material laminated plate is usually connected by adopting an adhesive. In the process of gluing and serving of the composite material part, the problems of 'kiss' (close contact but no adhesive force of the interface) or 'weak adhesion' and the like exist in the bonded interface due to factors such as uneven bonding, aging of the adhesive or surface pollution and the like, and great hidden dangers are brought to the structural integrity and the safety and the reliability of the airplane.
The bonding part of the composite material is a key part of the structure and is also a weak part of the structural strength. The existing nondestructive detection means such as ultrasonic waves, rays and the like can only detect the defects of layering, debonding, cracks, air holes, inclusions and the like, and can not detect the sizes of 'kissing' defects and interfacial adhesion. In order to quantitatively detect the interfacial adhesion, Zhou Ming et al in patent CN1215320C propose to quantitatively measure the film/substrate interface bonding strength by using a laser delamination method, which uses a laser velocity interferometer to monitor the particle velocity on the back of the material, and thus, determines whether delamination occurs and the bonding strength meets the requirements. Leyinghong et al in patent CN107561004B propose to use laser shock wave to perform on-line rapid detection on the bonding force of a composite material, arrange a piezoelectric sensor on the surface of the material to acquire a stress wave signal, and compare the stress wave signal obtained by monitoring the piezoelectric sensor during two laser shocks by an oscilloscope, thereby detecting and evaluating the interface bonding force of the composite material to be detected.
Although the method realizes quantitative detection of the bonding force of the film/base interface and the bonding interface of the composite material, the difference of detection objects is not considered, so that the specific conditions such as the thickness of a coating/film or the thickness of a composite material laminated plate, the position difference of the bonding interface to be detected and the like need to design laser parameters in a targeted manner to realize accurate detection of the bonding force of a specific interface, and the laser shock wave bonding force detection technology has better applicability in the detection of the interface structure of the composite material. In summary, for differences of bonding structures of composite materials (different depths of bonding interfaces), a method for detecting the interfacial bonding force of the composite material is required to be invented, which can meet the requirements of detecting interfaces with different depths.
Disclosure of Invention
In view of the above drawbacks of the prior art, an object of the present invention is to provide a method for detecting interfacial adhesion of a composite material based on laser pulse waveform regulation, which is used for controlling a laser pulse waveform to realize accurate detection of specific interfacial adhesion, in view of the problem of depth difference of a bonding interface of a composite material.
In order to achieve the above objects and other related objects, the present invention provides a method for detecting interfacial adhesion of a composite material based on laser pulse waveform regulation, comprising the steps of:
s1: on the basis of a nanosecond laser induced shock wave pressure model, calculating laser shock wave pressure time distribution curves under different laser pulse waveforms to obtain different laser shock wave loads;
s2: establishing a composite material laser shock wave dynamic propagation numerical simulation model, applying different laser shock wave loads in the step S1, and obtaining the influence rule of different laser pulse waveforms on the maximum coupling tensile stress position;
s3: reversely determining a laser shock wave pressure time distribution curve required by detection according to the influence rule of the bonding interface position of the composite material to be detected and the maximum coupling tensile stress position in the step S2;
s4: according to the laser shock wave pressure time distribution curve determined in the S3, combining a nanosecond laser induced shock wave pressure model, and reversely solving to obtain corresponding laser pulse waveform parameters;
s5: and (5) according to the laser pulse waveform parameters obtained in the S4, setting pulse laser parameters, and performing a laser shock test on the composite material to be detected to complete the detection of the interface bonding force of the composite material.
Further, the step S2 of establishing a composite material laser shock wave state propagation numerical simulation model includes the following steps:
s21: establishing a finite element model according to the physical and mechanical property parameters of the composite material;
s22: defining and loading different laser shock wave loads obtained in the step S1 through an external subroutine.
Further, in step S5, the setting according to the laser pulse waveform parameters in S4 is realized by a pulse waveform modulator inside the pulse laser.
As described above, the present invention has the following advantageous effects:
the required laser pulse waveform is obtained by reversely drawing according to the influence rule of the maximum coupling tensile stress position of different laser pulse waveforms in the composite material and the bonding interface position of the composite material to be detected, and finally the required laser pulse waveform parameter is obtained, namely the forming position of the maximum coupling tensile stress in the material is quickly and accurately regulated and controlled by regulating and controlling the laser pulse waveform, so that the bonding force detection aiming at the bonding interface at the specific position of the composite material is realized, and the accuracy of the bonding force detection of the corresponding composite material is effectively improved.
Drawings
FIG. 1 is a flow chart of the present invention;
FIG. 2(a) is a schematic diagram of a first laser pulse waveform;
FIG. 2(b) is a schematic diagram of a second laser pulse waveform;
FIG. 2(c) is a schematic diagram of a third laser pulse waveform;
FIG. 2(d) is a diagram illustrating a fourth laser pulse waveform;
FIG. 3(a) is a stress profile of a first shock wave propagation process induced by a first laser pulse waveform;
FIG. 3(b) is a stress distribution diagram of a second shock wave propagation process induced by a second laser pulse waveform;
FIG. 3(c) is a graph of stress distribution during a third shock wave propagation induced by a third laser pulse waveform;
FIG. 3(d) is a stress distribution diagram of a fourth shock wave propagation process induced by a fourth laser pulse waveform;
FIG. 4(a) is a schematic illustration of the propagation of a first shock wave in a composite material;
FIG. 4(b) is a schematic illustration of the propagation of a second shock wave in a composite material;
FIG. 4(c) is a schematic illustration of the propagation of a third shock wave in the composite material;
FIG. 4(d) is a schematic representation of the propagation of a fourth shock wave in the composite material.
Description of reference numerals
1-rising edge of laser energy; 2-laser energy falling edge; 3-a composite material; 4-center of compressive stress shock wave; 5-tensile stress shock wave center; 6-compressive stress wave; 7-tensile stress wave; 8-composite back; 9-reflection of tensile stress waves; 10-maximum coupled tensile stress; 11-position of maximum coupled tensile stress.
Detailed Description
The following description of the embodiments of the present invention is provided for illustrative purposes, and other advantages and effects of the present invention will become apparent to those skilled in the art from the present disclosure.
It should be understood that the structures, ratios, sizes, and the like shown in the drawings and described in the specification are only used for matching with the disclosure of the specification, so as to be understood and read by those skilled in the art, and are not used to limit the conditions under which the present invention can be implemented, so that the present invention has no technical significance, and any structural modification, ratio relationship change, or size adjustment should still fall within the scope of the present invention without affecting the efficacy and the achievable purpose of the present invention. In addition, the terms "upper", "lower", "left", "right", "middle" and "one" used in the present specification are for clarity of description, and are not intended to limit the scope of the present invention, and the relative relationship between the terms and the terms is not to be construed as a scope of the present invention.
Referring to fig. 1, the present invention provides a method for detecting interfacial adhesion of a composite material based on laser pulse waveform regulation, comprising the following steps:
s1: on the basis of a nanosecond laser induced shock wave pressure model, calculating laser shock wave pressure time distribution curves under different laser pulse waveforms to obtain different laser shock wave loads;
s2: establishing a composite material laser shock wave dynamic propagation numerical simulation model, applying different laser shock wave loads in the step S1, and obtaining the influence rule of different laser pulse waveforms on the maximum coupling tensile stress position;
s3: reversely determining a laser shock wave pressure time distribution curve required by detection according to the influence rule of the bonding interface position of the composite material to be detected and the maximum coupling tensile stress position in the step S2;
s4: according to the laser shock wave pressure time distribution curve determined in the S3, combining a nanosecond laser induced shock wave pressure model, and reversely solving to obtain corresponding laser pulse waveform parameters;
s5: and (5) according to the laser pulse waveform parameters obtained in the S4, setting pulse laser parameters, and performing a laser shock test on the composite material to be detected to complete the detection of the interface bonding force of the composite material.
Obtaining the influence rule of the maximum coupling tensile stress position of different laser pulse waveforms in the composite material through numerical simulation, finally reversely solving the required laser shock wave pressure time distribution curve, and then carrying out actual engineering detection according to laser pulse waveform parameters.
In step S1, laser shock wave pressure time distribution curves under different laser pulse waveforms are calculated and obtained according to a nanosecond laser induced shock wave pressure model. Specifically, different laser pulse waveform parameters are preset, and after calculation is performed by a nanosecond laser induced shock wave pressure model, corresponding laser shock wave pressure time distribution curves under different laser pulse waveforms are obtained, so that different laser shock wave loads can be further obtained.
The step S2 of establishing a composite material laser shock wave state propagation numerical simulation model includes the following steps:
s21: establishing a finite element model according to the physical and mechanical property parameters of the composite material;
s22: defining and loading different laser shock wave loads obtained in the step S1 through an external subroutine.
Specifically, a finite element model of the composite material to be detected is established by using finite element software and combining physical and mechanical performance parameters of the composite material to be detected, and then an external subprogram is developed to define and load the laser shock wave load under different laser pulse waveforms obtained in step S1 (i.e., a shock wave pressure time curve is applied to the finite element software in a program mode to apply the shock load to the material), so as to analyze the propagation process of the laser shock wave in the composite material, thereby realizing the propagation numerical simulation of the laser shock wave state inside the composite material to be detected, analyzing the propagation rule of the laser shock wave inside the composite material, and further analyzing and obtaining the influence rule of the laser pulse waveform on the maximum coupling tensile stress position.
Referring to fig. 2(a), fig. 2(b), fig. 2(c) and fig. 2(d), which show the variation of the laser energy rising edge 1 and the laser energy falling edge 2 with time, in fig. 2(a), the duration of the laser energy rising edge 1 of the first laser pulse waveform is equal to the duration of the laser energy falling edge 2, and there is a gentle transition between the laser energy rising edge 1 and the laser energy falling edge 2; in fig. 2(b), the duration of the laser energy rising edge 1 of the second laser pulse waveform is less than the duration of the laser energy falling edge 2; in fig. 2(c), the duration of the rising edge 1 of laser energy of the third laser pulse waveform is equal to the duration of the falling edge 2 of laser energy, and there is a sharp transition between the rising edge 1 of laser energy and the falling edge 2 of laser energy; in fig. 2(d), the duration of the rising edge 1 of laser energy of the fourth laser pulse waveform is greater than the duration of the falling edge 2 of laser energy. In step S1, shockwave pressure time profiles for different laser pulse waveforms are obtained. The laser energy emitted by the laser hits the composite plate, i.e. a pressure-time profile is formed. The energy time distribution curve and the pressure time distribution curve have the same distribution characteristics.
Referring to fig. 3(a), fig. 3(b), fig. 3(c) and fig. 3(d), it can be seen that under different laser pulse waveforms, the difference between the distance between the compressive stress central region 4 and the tensile stress central region 5 during the propagation of the laser shock wave inside the composite material 3 is caused, i.e., L1 > L2 > L3 > L4.
Referring to fig. 4(a), fig. 4(b), fig. 4(c) and fig. 4(d), it can be seen that the time interval between the compressive stress wave 6 and the tensile stress wave 7 is as follows: t1 > T2 > T3 > T4, the compression stress wave 6 forms an emission tensile stress wave 9 after reaching the back surface 8 of the composite material through reflection, the reflection tensile stress wave 9 is coupled with the tensile stress wave 7 to form a maximum coupling tensile stress 10, and the distance from a maximum coupling tensile stress position 11 to the back surface 8 of the composite material is as follows: e1 > E2 > E3 > E4, and the difference of the positions of the maximum coupling tensile stress 10 in the composite material 3 under different shock waves can be seen. Therefore, the maximum coupling tensile stress 10 can be effectively controlled in the composite material 3 by regulating the laser pulse waveform, and the detection requirements of different bonding interface positions (namely the depths of bonding interfaces) can be met.
In step S3, according to the thickness of the composite material to be detected and the position information of the bonding interface (i.e., the depth of the bonding interface), the rule of the influence of the laser pulse waveform on the maximum coupling tensile stress position in step S2 is combined, so that the laser shock wave pressure time distribution curve required for detection can be determined reversely. Specifically, according to the influence rule of the maximum tensile stress position, the maximum tensile stress position is determined to just meet the laser shock wave pressure time curve of the bonding interface position of the composite material to be detected. In step S3, the method further includes verifying a laser shock wave pressure time distribution curve for detection by using a laser shock wave dynamic propagation numerical simulation model, that is, detecting a shock wave propagation condition formed by the pressure time distribution curve according to the detection position and the adhesion threshold range.
In step S4, according to the laser shock wave pressure time distribution curve determined in step S3, the corresponding laser pulse waveform parameters are obtained through reverse solution; in step S4, the inverse solution is to calculate and obtain corresponding laser pulse waveform parameters, such as spot energy, spot area, laser pulse width, etc., by combining the nanosecond laser-induced shock wave pressure model.
In step S5, the setting according to the laser pulse waveform parameters in S4 is realized by a pulse waveform modulator inside the laser. The laser system comprises a pulse waveform modulator, laser pulse waveform parameters are set through the pulse waveform modulator to regulate and control required laser pulse waveforms, the laser outputs required pulse laser beams, a composite material to be detected is subjected to a laser shock test, and the detection of the bonding force of a bonding interface at a specific position (different depth positions) of the composite material is completed. For the concrete operation of detecting the bonding interface adhesion of the composite material by using the laser shock test, reference is made to the method in CN107561004B, and the description is not repeated here.
In summary, according to the method for detecting the bonding force of the composite material interface based on laser pulse waveform regulation and control provided by the embodiment of the invention, the required laser pulse waveform is obtained through the obtained influence rule of the maximum coupling tensile stress position of different laser pulse waveforms in the composite material and through reverse planning according to the thickness of the composite material to be detected and the bonding interface position, and finally the required laser pulse waveform parameter is obtained, that is, the forming position of the maximum coupling tensile stress in the material is controlled through regulating and controlling the laser pulse waveform, so that the bonding force detection of the bonding interface at the specific position of the composite material is realized, and the accuracy of the bonding force detection of the corresponding composite material is effectively improved.
The foregoing embodiments are merely illustrative of the principles and utilities of the present invention and are not intended to limit the invention. Any person skilled in the art can modify or change the above-mentioned embodiments without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which can be made by those skilled in the art without departing from the spirit and technical spirit of the present invention be covered by the claims of the present invention.
Claims (3)
1. A composite material interface bonding force detection method based on laser pulse waveform regulation is characterized by comprising the following steps:
s1: on the basis of a nanosecond laser induced shock wave pressure model, calculating laser shock wave pressure time distribution curves under different laser pulse waveforms to obtain different laser shock wave loads;
s2: establishing a composite material laser shock wave dynamic propagation numerical simulation model, applying different laser shock wave loads in the step S1, and obtaining the influence rule of different laser pulse waveforms on the maximum coupling tensile stress position;
s3: reversely determining a laser shock wave pressure time distribution curve required by detection according to the influence rule of the bonding interface position of the composite material to be detected and the maximum coupling tensile stress position in the step S2;
s4: according to the laser shock wave pressure time distribution curve determined in the S3, combining a nanosecond laser induced shock wave pressure model, and reversely solving to obtain corresponding laser pulse waveform parameters;
s5: and (5) according to the laser pulse waveform parameters obtained in the S4, setting pulse laser parameters, and performing a laser shock test on the composite material to be detected to complete the detection of the interface bonding force of the composite material.
2. The method for detecting the interfacial adhesion of the composite material based on the laser pulse waveform regulation and control as claimed in claim 1, wherein: the step S2 of establishing the composite material laser shock wave state propagation numerical simulation model comprises the following steps:
s21: establishing a finite element model according to the physical and mechanical property parameters of the composite material;
s22: defining and loading different laser shock wave loads obtained in the step S1 through an external subroutine.
3. The method for detecting the interfacial adhesion of the composite material based on the laser pulse waveform regulation and control as claimed in claim 1, wherein: in step S5, the setting according to the laser pulse waveform parameters in S4 is realized by a pulse waveform modulator inside the pulse laser.
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