CN114354350A - Composite material layering damage monitoring method - Google Patents
Composite material layering damage monitoring method Download PDFInfo
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- CN114354350A CN114354350A CN202111593893.1A CN202111593893A CN114354350A CN 114354350 A CN114354350 A CN 114354350A CN 202111593893 A CN202111593893 A CN 202111593893A CN 114354350 A CN114354350 A CN 114354350A
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Abstract
The application provides a composite material layering damage monitoring method, which comprises the following steps: uniformly arranging scattered spots on the surface of the composite material structure by using matt paint; applying a specific load to the composite material structure and performing optical measurement by using three-dimensional optical measurement equipment; obtaining initial damage characteristics of the composite structure; repeatedly applying a specific load to the composite material structure, and carrying out optical measurement on the composite material structure based on a preset period to obtain the expansion characteristic of the layered damage of the composite material structure; according to the method for monitoring the layered damage of the composite material, the layered damage and the expansion state of the composite material structure are monitored through a three-dimensional optical measurement technology, and the position, the size, the shape and other characteristics of the layered damage are accurately determined.
Description
Technical Field
The application belongs to the technical field of aircraft structure health monitoring, and particularly relates to a composite material layered damage monitoring method.
Background
The use ratio of the composite material is an important index of the advancement of the modern airplane, the use amount of the composite material is larger and larger along with more and more parts of the airplane structure composite material, and the damage monitoring and accurate identification of the composite material have important significance on the structural integrity of the airplane. The layered damage and the expansion of the composite material structure are usually difficult to monitor because the layered damage and the expansion of the composite material structure occur in the structure and have strong concealment.
The layered damage and the expansion condition of the current aircraft composite material structure are generally monitored by adopting a nondestructive detection means or prefabricating advanced sensors in the structure to measure the structural response.
However, the non-destructive testing is a traditional testing method, and the applicability of the non-destructive testing is limited by multiple factors, so that the non-destructive testing is limited greatly. The built-in sensor monitoring method is characterized in that an excitation-sensor is generated through a sensor sensing or driver to obtain structural response, the sensors commonly used for monitoring the layered damage of the composite material at present mainly comprise an optical fiber sensor, a piezoelectric guided wave sensor, a sound emission sensor, a metal core-containing guided wave fiber sensor, an intelligent coating sensor and the like, after a large number of optimization algorithms and deep learning are carried out through technologies such as corresponding algorithms, mechanical modeling and the like, the obtained signals of the natural structure or the excitation response correspond to the prefabricated layered damage characteristics of the structure, the damage characterization information of the structure is obtained, and the evaluation and monitoring of the layered damage state and the expansion of the structure are realized by combining the actual measurement result of the structural response.
The method in the relative technology can effectively monitor the positioning of the layered damage and the damage area, and cannot accurately and effectively identify the outline of the damage area and the damage degree.
Disclosure of Invention
In order to solve the technical problem, the invention provides a composite material layering damage monitoring method, which comprises the following steps:
uniformly arranging scattered spots on the surface of the composite material structure by using matt paint;
applying a specific load to the composite material structure and performing optical measurement by using three-dimensional optical measurement equipment;
obtaining an initial damage characteristic of the composite structure.
Preferably, after the matte paint is uniformly arranged on the surface of the composite material structure, the matte paint further comprises:
and carrying out initial calibration on the three-dimensional optical measuring equipment.
Preferably, the initially calibrating the three-dimensional optical measurement device includes:
and when the composite material structural member is in a free state, performing initial calibration on the three-dimensional optical measurement equipment as an initial value.
Preferably, the method further comprises:
repeatedly applying a specific load to the composite structure and performing optical measurement with the three-dimensional optical measurement device.
Preferably, the repeatedly applying a specific load to the composite material structure and performing optical measurement with the three-dimensional optical measurement apparatus includes:
repeatedly applying a specific load to the composite structure, and optically measuring the composite structure based on a preset period.
Preferably, after the repeatedly applying the specific load to the composite material structure and performing the optical measurement on the composite material structure based on the preset period, the method further comprises:
and acquiring the extension characteristic of the layered damage of the composite material structure.
Preferably, the extended characteristics include location, size, and contour of the layered lesion generation.
Preferably, the free state is a state in which the composite structure is not under load.
The beneficial technical effect of this application:
according to the method for monitoring the layered damage of the composite material, the layered damage and the expansion state of the composite material structure are monitored through a three-dimensional optical measurement technology, and the position, the size, the shape and other characteristics of the layered damage are accurately determined.
Drawings
FIG. 1 is a schematic diagram of a structured surface speckle arrangement provided by an embodiment of the present application;
FIG. 2 is a schematic view of a defect area of a structural member according to an embodiment of the present disclosure;
FIG. 3 is a schematic diagram of an out-of-plane deformation of a layered defect region provided by an embodiment of the present application;
FIG. 4 is a schematic view of a lesion extension area provided by an embodiment of the present application;
FIG. 5 is a schematic diagram of a measurement offset correction provided by an embodiment of the present application;
FIG. 6 is a schematic three-dimensional optical measurement contour line provided by an embodiment of the present application;
fig. 7 is a diagram of a damage expansion of a composite structure layer provided in an embodiment of the present application.
Detailed Description
The method is used for monitoring the layered damage and the expansion state of the composite material structure through a three-dimensional optical measurement technology and accurately determining the position, size, shape and other characteristics of the layered damage.
Referring to fig. 1-7, firstly, uniformly arranging scattered spots on the surface of the composite material structure by using a matte paint, and performing initial calibration on a three-dimensional optical measurement device as shown in fig. 1; applying a certain load to the structure and carrying out optical measurement, wherein the initial damage characteristic of the structure is obtained due to the change of the local structural rigidity and displacement of the layered damage area of the structure; and measuring the structure at regular intervals along with the repeated loading action of the structure, thereby obtaining the expansion characteristic of the layered damage of the structure.
Compare in combined material structure layering damage monitoring prior art, this application has following advantage:
1, a sensor does not need to be prefabricated in a structure, so that a complex process flow is avoided, and the problem that measurement cannot be carried out or accurate measurement cannot be carried out due to the damage of the sensor is avoided;
2, the monitoring area is wide and the position is variable, different from the fixed position of the sensor, the monitoring area is limited;
3, non-contact measurement is carried out, the deformation of the measured surface is interfered without contacting the measured piece, the precision of the measurement result is influenced, and the processes of complicated installation, acquisition, analysis and the like are avoided;
4, the position, the size, the degree, the outline and the like of the layered damage are directly measured to form a three-dimensional view, the data processing is simple, and the damage is not required to be calibrated or calibrated in the early stage through a large amount of data and deep machine learning;
5, the measurement automation is high, and the measurement process and the operation are simple.
The three-dimensional optical measurement is non-contact measurement, the layered damage and the expansion condition of a test piece are represented by observing the out-of-plane deformation of a defect area on the surface of the composite material structure under the condition that the defect area is subjected to pneumatic pressure, and as shown in fig. 2, the circled part in the graph is a defect area and a damaged area after the defect is expanded.
It should be noted that, when the structure is in a free state (without load), three-dimensional optical measurement calibration is performed, as an initial 0 value, when the structure is subjected to an axial compressive load, a local out-of-plane deformation occurs in a surface defect region, as shown in fig. 3, the out-of-plane deformation degree is represented by a Z-directional displacement Δ Z (Δ Z ═ Z-0), a deformation Δ Z0 corresponding to an edge of an initial defect region of the structure is used as a reference, when the defect damage is expanded after N cycles of loading, a region corresponding to a contour position of Δ Z0 is used as an expanded damage region, and a damage expansion length when the longest axial distance L of the damage region is N cycles at this time is recorded, as shown in fig. 4.
In one possible implementation, as shown in FIG. 5, the test piece surface will have an overall slight offset Δ Z during each optical measurement due to the loading experienced by the structure during the measurement processmI.e. contour Δ Z per measurementiMeasurement and actual contour line Δ ZiWith the same slight offset Δ Z between realitymTherefore, the actual value and the measured value of the damage extension length L are different due to the deviation of the contour line, so Δ Z should be considered when the contour line is obtainedmOffset which can be determined by measuring the minimum offset value deltaZ of the surface of the test piece each timeminThe variation of (a) is characterized, then the contour value after the deviation is considered as:
ΔZireality＝ΔZi measurement+ΔZm
ΔZm＝ΔZi-min-ΔZ0-min
In the formula:
ΔZireality-actual displacement contour, mm, at cycle i;
ΔZi measurement-displacement contour, mm, measured at cycle i;
ΔZmthe surface of the test piece wholly deviates slightly by mm when the cycle number is i;
ΔZi-min-the minimum value of the integral surface offset of the test piece of the ith cycle number, mm;
ΔZ0-min-initial loading test piece surface global offset minimum, mm.
After the contour line value of each measurement is determined, the corresponding long-axis distance of the contour line value is taken as the damage expansion length L, and the area surrounded by the contour lines is a layered damage expansion area.
The method has good effect in practical application to layered damage and extension monitoring of the composite material honeycomb sandwich structure, and the obtained composite material structure layered damage extension monitoring result graph can clearly and definitely obtain key parameters such as position, size, degree and outline generated by layered damage.
The application is applied to a plurality of subjects and projects, can effectively and accurately measure the position, size, shape, development state and the like of the layered damage of the composite material, and has a good effect on monitoring the layered damage and the extension of the composite material structure.
Claims (8)
1. A composite delamination damage monitoring method, the method comprising:
uniformly arranging scattered spots on the surface of the composite material structure by using matt paint;
applying a specific load to the composite material structure and performing optical measurement by using three-dimensional optical measurement equipment;
obtaining an initial damage characteristic of the composite structure.
2. The method of claim 1, wherein after uniformly disposing the speckles on the surface of the composite structure with the matte paint, further comprising:
and carrying out initial calibration on the three-dimensional optical measuring equipment.
3. The method of claim 2, wherein said initially calibrating the three-dimensional optical measurement device comprises:
and when the composite material structural member is in a free state, performing initial calibration on the three-dimensional optical measurement equipment as an initial value.
4. The method of claim 1, further comprising:
repeatedly applying a specific load to the composite structure and performing optical measurement with the three-dimensional optical measurement device.
5. The method of claim 4, wherein said repeatedly applying a specific load to said composite structure and optically measuring with said three-dimensional optical measuring device comprises:
repeatedly applying a specific load to the composite structure, and optically measuring the composite structure based on a preset period.
6. The method of claim 5, wherein after repeatedly applying a specific load to the composite structure and optically measuring the composite structure based on a predetermined period, further comprising:
and acquiring the extension characteristic of the layered damage of the composite material structure.
7. The method of claim 6, wherein the extended characteristics include location, size, and contour of layered lesion generation.
8. The method of claim 3, wherein the free state is a state in which the composite structure is not under load.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111593893.1A CN114354350A (en) | 2021-12-23 | 2021-12-23 | Composite material layering damage monitoring method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115859708A (en) * | 2022-11-16 | 2023-03-28 | 大连理工大学 | Honeycomb sandwich structure damage model correction method based on distributed optical fiber measurement |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115859708A (en) * | 2022-11-16 | 2023-03-28 | 大连理工大学 | Honeycomb sandwich structure damage model correction method based on distributed optical fiber measurement |
| CN115859708B (en) * | 2022-11-16 | 2024-03-19 | 大连理工大学 | Honeycomb sandwich structure damage model correction method based on distributed optical fiber measurement |
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