CN115876883B - Method and system for detecting layered damage position of composite material laminated plate - Google Patents
Method and system for detecting layered damage position of composite material laminated plate Download PDFInfo
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Abstract
The invention discloses a method and a system for detecting a layered damage position of a composite material laminated plate, wherein the method comprises the following steps: measuring the out-of-plane velocity field of the composite material laminated plate; calculating the curvature of the out-of-plane velocity field; calculating the curvature energy of the out-of-plane velocity field; and determining the layering position according to the singular peak position in the curvature energy diagram of the out-of-plane velocity field. The method can be used for analyzing the out-of-plane velocity field of the composite material laminated plate so as to judge whether layering damage exists or not and position the layering damage. The method can be matched with advanced instruments such as a laser scanning vibration meter and the like for use, and is widely applied to the layered damage detection of the composite material laminated plate.
Description
Technical Field
The invention discloses a method for detecting a layering damage position of a composite material laminated plate, and particularly relates to the technical field of structural state monitoring of composite material laminated plates.
Background
The composite material laminated plate is easy to generate layering damage under the action of external force impact, and if the layering damage cannot be detected and repaired in time, the safe and reliable operation of the integral structure can be influenced. Against this background, some nondestructive inspection techniques have been rapidly developed in recent years and are used to detect damage in structures. Nondestructive inspection methods such as ultrasonic inspection have been widely used for composite laminate delamination damage inspection. However, these methods generally require prediction of the approximate location of the delamination damage, and the delamination location must be easily accessible, which is difficult to satisfy in practical applications.
Disclosure of Invention
Aiming at the defects of the prior art, the application aims to provide a composite material laminated plate layering damage position detection method based on the out-of-plane velocity field analysis, which can cover a larger detection area, strengthen the information characteristics of layering damage areas, accurately judge layering and determine layering positions.
The invention adopts the following technical scheme for solving the technical problems:
the method for detecting the layered damage position of the composite material laminated plate comprises the following specific steps:
measuring the out-of-plane velocity field of the composite material laminated plate;
step two, calculating curvature of the off-plane velocity field;
step three, calculating the curvature energy of the off-plane velocity field;
and fourthly, positioning layering damage according to the position of the occurrence of the singular peak value in the curvature energy diagram of the off-plane velocity field.
As a further preferable scheme of the invention, the specific calculation mode of the first step is as follows:
measuring the out-of-plane velocity field v (i, j, r) of the composite material laminated plate,
wherein i=1, 2, …, M and j=1, 2, …, N are the station numbers in the x and y directions, respectively; r=1, 2, …, T is a discrete time series.
As a further preferable scheme of the invention, the specific calculation mode of the second step is as follows:
w(i,j,r)＝v(i+1,j,r)+v(i-1,j,r)+v(i,j+1,r)+v(i,j-1,r)-4v(i,j,r)，
wherein w represents the curvature of the out-of-plane velocity field and is calculated by a second-order center difference method of out-of-plane velocity field signals, as shown in the above formula.
As a further preferable scheme of the invention, the specific calculation mode of the third step is as follows:
where E (i, j) represents the out-of-plane velocity field curvature energy.
As a further preferable scheme of the invention, the method for acquiring the out-of-plane velocity field of the composite material laminated plate in the first step is specifically as follows:
excitation is applied to the geometrical center position of the back side of the composite material laminated plate by using an excitation sensor, and meanwhile, the off-plane velocity field of the front side of the composite material laminated plate is measured by using a laser scanning vibration meter.
As a further preferred embodiment of the present invention, the laser sensor uses a PSV-400 laser scanning vibration meter, and the excitation sensor is a piezoelectric ceramic sensor.
Compared with the prior art, the technical scheme provided by the invention has the following technical effects:
the detection method provided by the invention can be used for realizing layering damage positioning by analyzing the out-of-plane velocity field of the composite material laminated plate. Compared with the conventional local nondestructive testing technology, the method does not need to predict layering positions, is simple to operate, and has obvious effects of eliminating the influence of environmental noise and strengthening damage characteristics. The method can be matched with advanced sensors such as a laser scanning vibration meter and the like for use, and is highly effective for detecting layered damage of the composite material laminated plate structure in a noise environment.
Drawings
FIG. 1 is a schematic flow diagram of the method of the present invention;
FIG. 2 is a schematic view of the out-of-plane velocity field of a plate in accordance with the present invention;
FIG. 3 is a schematic view of the out-of-plane velocity field curvature of a plate in accordance with the present invention;
fig. 4 is a graph of out-of-plane velocity field curvature energy for a plate in accordance with the present invention.
Detailed Description
The technical scheme of the invention is further described in detail below with reference to the accompanying drawings:
it will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs.
Example 1
The embodiment is a composite material laminated plate layering damage position detection system, as shown in fig. 1, the system includes: the excitation sensor is positioned at the geometric center position of the back surface of the composite material laminated plate to be detected, the laser scanning vibration meter is positioned at the front surface of the composite material laminated plate to be detected, and the distance between the laser scanning vibration meter and the composite material laminated plate to be detected is set to be the same as the distance between the excitation sensor and the composite material laminated plate to be detected.
Example 2
Based on the detection system provided in the foregoing embodiment, this embodiment is a method for detecting a layered damage position of a composite material laminated board, including the following steps:
step 1, measuring the out-of-plane velocity field v (i, j, r) of the composite material laminated plate,
wherein i=1, 2, …, M and j=1, 2, …, N are the station numbers in the x and y directions, respectively; r=1, 2, …, T is a discrete time series.
Step 2, calculating curvature of the out-of-plane velocity field:
w(i,j,r)＝v(i+1,j,r)+v(i-1,j,r)+v(i,j+1,r)+v(i,j-1,r)-4v(i,j,r)，
(1)
wherein w represents the curvature of the out-of-plane velocity field, and is calculated by a second-order center difference method of out-of-plane velocity field signals, as shown in formula (1).
Step 3, calculating the curvature energy of the out-of-plane velocity field:
where E (i, j) represents the out-of-plane velocity field curvature energy.
And 4, judging the layering damage of the composite material laminated plate according to whether a singular peak value appears in E (i, j), and determining the layering damage position according to the peak value position.
The working principle of the invention is as follows: the composite laminated plate layering damage can lead the out-of-plane velocity field at the layering damage to be singular, and accordingly, the layering damage can be identified through singular components in the out-of-plane velocity field. However, slight, localized delamination damage only causes singularities in the out-of-plane velocity field that are not readily observable. In order to fully reveal the singular of the off-plane velocity field, the curvature of the off-plane velocity field is obtained by a center difference method, so that singular components at the layering damage position are amplified. And further calculating the curvature energy of the out-of-plane velocity field, judging the layering damage of the composite material laminated plate according to whether a singular peak value appears in the curvature energy diagram of the out-of-plane velocity field, and determining the layering damage position according to the peak value position.
Compared with the conventional local nondestructive testing method, the out-of-plane speed field is used as the vibration parameter of the composite material laminated plate, can cover a larger testing area, can strengthen the information characteristics of the layered damage area, accurately judges the occurrence of layering and determines the layering position.
The following describes a detection method according to the present invention in one embodiment:
the GFRP composite laminate used in the examples was 50 cm long, 50 cm wide and 0.3 cm thick, with a preformed 15 mm long and 15 mm wide layered lesion at 125 mm distance from each of the two adjacent edges of the laminate. A piezoelectric sensor is used as an exciter to apply five-period sine excitation modulated by a Hanning window with the center frequency of 50kHz at the geometric center position of the back of the plate, and a laser scanning vibration meter is used for measuring the out-of-plane velocity field of the front of the plate. The off-plane velocity field measuring area is a 375×375 square measuring point grid covering the whole front surface of the plate, and 1 millisecond of velocity response signals are collected at each measuring point with a sampling frequency of 512kHz to obtain an off-plane velocity field consisting of 512 time sequences.
The measured out-of-plane velocity field of the composite laminate at time series 103 is shown in fig. 2, where the horizontal axis x represents the coordinates along the length of the panel, the vertical axis y represents the coordinates along the width of the panel, and the vertical axis v represents the out-of-plane velocity field. The out-of-plane velocity field curvature of the composite laminate at time series 103 is found according to equation (1), as shown in FIG. 3, where the vertical axis w represents the out-of-plane velocity field curvature. The energy of the out-of-plane velocity field curvature of the composite laminate is obtained according to equation (2), as shown in fig. 4. From fig. 4, it can be seen that there is a singular peak at 125 mm from each of the two adjacent sides of the plate, indicating the presence of damage. And the peak value corresponding position is consistent with the actual layering damage position, so that layering damage detection is realized.
In summary, the invention provides a method for detecting the layered damage position of a composite material laminated plate, which is simple to operate and can accurately realize layered damage detection without predicting the layered damage position compared with the conventional local nondestructive detection technology.
The above embodiments are only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited thereto, and any modification made on the basis of the technical scheme according to the technical idea of the present invention falls within the protection scope of the present invention.
Claims (3)
1. A method for detecting a layered damage position of a composite material laminated plate, the method comprising:
measuring the out-of-plane velocity field of the composite material laminated plate; the method for acquiring the out-of-plane velocity field of the composite material laminated plate in the first step comprises the following specific steps: the specific calculation mode of the first step is as follows:
the out-of-plane velocity field v (i, j, r0,
wherein i=1, 2, …, M and j=1, 2, …, N are the measurement point numbers in the x and y directions of the composite material laminated plate, respectively; r=1, 2, …, T is a discrete time series;
applying excitation to the geometrical center position of the back side of the composite material laminated plate by using an excitation sensor, and simultaneously measuring the out-of-plane velocity field of the front side of the composite material laminated plate by using a laser scanning vibration meter;
calculating and measuring the curvature of the out-of-plane velocity field of the composite material laminated plate; the specific calculation mode of the second step is as follows:
w(i,j,r)＝v(i+1,j,r)+v(i-1,j,r)+v(i,j+1,r)+v(i,j-1,r)-4v(i,j,r)，
wherein w represents the curvature of the wave field and is calculated by a second-order center difference method of the wave field signal;
step three, calculating the curvature energy of the off-plane velocity field, wherein the specific calculation mode is as follows:
wherein E (i, j) represents the out-of-plane velocity field curvature energy;
and fourthly, positioning layering damage according to the position of the occurrence of the singular peak value in the curvature energy diagram of the off-plane velocity field.
2. The method for detecting the layering damage position of the composite material laminated plate according to claim 1, wherein the laser scanning vibration meter is a PSV-400 laser scanning vibration meter, and the excitation sensor is a piezoelectric ceramic sensor.
3. A detection system for a method of detecting a delamination damage location of a composite laminate according to claim 1 or 2, the system comprising: the excitation sensor is positioned at the geometric center position of the back surface of the composite material laminated plate to be detected, the laser scanning vibration meter is positioned at the front surface of the composite material laminated plate to be detected, and the distance between the laser scanning vibration meter and the composite material laminated plate to be detected is set to be the same as the distance between the excitation sensor and the composite material laminated plate to be detected.
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