KR101740909B1 - Nondestructive Testing Equipment for Automatic Rivet Center Positioning and Rivet Defect Inspection - Google Patents
Nondestructive Testing Equipment for Automatic Rivet Center Positioning and Rivet Defect Inspection Download PDFInfo
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- KR101740909B1 KR101740909B1 KR1020160023918A KR20160023918A KR101740909B1 KR 101740909 B1 KR101740909 B1 KR 101740909B1 KR 1020160023918 A KR1020160023918 A KR 1020160023918A KR 20160023918 A KR20160023918 A KR 20160023918A KR 101740909 B1 KR101740909 B1 KR 101740909B1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N27/00—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means
- G01N27/72—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables
- G01N27/82—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D5/00—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable
- G01D5/12—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable using electric or magnetic means
- G01D5/14—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage
- G01D5/142—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage using Hall-effect devices
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
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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
- G01N29/06—Visualisation of the interior, e.g. acoustic microscopy
- G01N29/0609—Display arrangements, e.g. colour displays
- G01N29/0645—Display representation or displayed parameters, e.g. A-, B- or C-Scan
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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
- G01N29/06—Visualisation of the interior, e.g. acoustic microscopy
- G01N29/0654—Imaging
- G01N29/069—Defect imaging, localisation and sizing using, e.g. time of flight diffraction [TOFD], synthetic aperture focusing technique [SAFT], Amplituden-Laufzeit-Ortskurven [ALOK] technique
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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
- G01N29/22—Details, e.g. general constructional or apparatus details
- G01N29/225—Supports, positioning or alignment in moving situation
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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
- G01N29/36—Detecting the response signal, e.g. electronic circuits specially adapted therefor
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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
- G01N29/44—Processing the detected response signal, e.g. electronic circuits specially adapted therefor
- G01N29/4463—Signal correction, e.g. distance amplitude correction [DAC], distance gain size [DGS], noise filtering
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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
- G01N29/44—Processing the detected response signal, e.g. electronic circuits specially adapted therefor
- G01N29/449—Statistical methods not provided for in G01N29/4409, e.g. averaging, smoothing and interpolation
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- Investigating Or Analyzing Materials By The Use Of Magnetic Means (AREA)
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Abstract
The present invention relates to a nondestructive inspection apparatus for automatically detecting a center position of an aircraft rivet and a defect of the rivet, and more particularly, to a non-destructive inspection apparatus for automatically detecting a center position of an aircraft rivet and a defect of the rivet by applying a uniform electromagnetic field to a predetermined region of the aircraft structure, A sensor unit for measuring a distortion of an electromagnetic field generated by the sensor; A signal processing unit for processing the electromagnetic field distribution measured through the sensor unit; A computer for receiving a digital signal reflecting the electromagnetic field distribution measured through the signal processing unit and analyzing a distortion distribution of an electromagnetic field caused by the rivet to estimate a center position of the rivet and a defect of the rivet; A display unit for indicating a center position of the rivet estimated through the computer unit and a defect of the detected rivet; And a power supply unit for supplying power to the sensor unit.
Description
The present invention relates to a nondestructive inspection apparatus for automatically detecting a center position of an rivet of an aircraft and a defect of a rivet, and particularly relates to a structure of a long-term operational aircraft, in particular, a center position of a rivet used for fastening a skeleton of an aircraft To a nondestructive inspection apparatus for automatically detecting a center position of an rivet and an rivet of an aircraft for automatically detecting a defect of a rivet existing at an estimated position.
A multi-layered structure is utilized to cover and secure the aluminum alloy sheet (skins) to the aircraft fuselage.
The rivet fastening part of the multi-layered structure is a part where stress is concentrated, and it becomes a starting point of corrosion defect and fatigue crack due to permeation of salt and water in the atmosphere together with repetitive load change over a long period such as aircraft takeoff and landing.
However, in a multilayered structure, corrosion defects are easily generated on the back surface, and in the case of fatigue cracks, it is difficult to detect them with the naked eye.
Therefore, there is a continuing need for a new concept of NDT for detection, position estimation and quantitative evaluation of backside corrosion and fatigue cracks around rivet joints.
NDT is an efficient way to inspect damage without damaging the object being inspected.
Of the various non-destructive testing methods, eddy current testing (ECT) has been used as a basic technology in the aerospace field, and ECT has the principle of using eddy current flow penetrating the subject.
That is, damage or defects that are hidden or behind can be detected by measuring the distortion of the eddy current through the sensor.
On the other hand, a conventional ECT system using a coil has high reliability and good inspection performance.
However, since damage to multiple structures is generally located around the rivet joint, there is a great difficulty in analyzing the vicinity of the joint.
That is, when measuring a signal corresponding to a damage, the ECT system measures the signal of the rivet fastening portion, which is much higher than the damage signal, and as a result, it is very difficult to evaluate the damage.
Particularly, fatigue cracks and corrosion defects of the rivet itself are not easy to inspect by the conventional eddy current because the damage or defect signal around the rivet hole and the rivet joint is relatively large.
Therefore, a method of inserting ultrasonic waves into the rivet and analyzing and examining the acoustic waves reflected from the damage or defects of the rivet is utilized.
However, ultrasonic inspection of thousands of rivets by one person lowers the working efficiency, and it is possible to obtain desirable experimental results only when the ultrasonic sensor is precisely positioned at the center of the rivet, do.
In addition, when the head portion of the rivet is hidden by the paint, it is difficult to find the position of the rivet, and it is also difficult to derive the correct ultrasonic inspection result.
Therefore, it is inevitable to develop an efficient equipment or algorithm for detecting damage or defects present in the rivet portion of the aircraft structure.
Disclosure of Invention Technical Problem [8] Accordingly, the present invention has been made in view of the above problems, and it is an object of the present invention to provide a method and apparatus for detecting a rivet center position and a rivet defect of an aircraft structure easily and easily by non- It is an object of the present invention to provide a nondestructive inspection apparatus for automatically detecting a center position of an rivet and an rivet of an aircraft which can improve the reliability of detection results.
A nondestructive inspection method for automatically detecting defects of a rivet and a center position of an aircraft rivet which can predict a defect occurrence result and a replacement cycle of a rivet fastening part in advance through a database, The provision of a device is another purpose.
In the meantime, the objects of the present invention are not limited to the above-mentioned objects, and other objects not mentioned can be clearly understood by those skilled in the art from the following description.
In order to achieve the above objects, the present invention provides a sensor unit for applying a uniform electromagnetic field to a predetermined region of an aircraft structure having a metal rivet and measuring a distortion of an electromagnetic field generated by the presence of a rivet, A signal processing unit for processing the measured electromagnetic field distribution, a digital signal reflecting the electromagnetic field distribution measured through the signal processing unit, receiving the digital signal, and analyzing the distortion distribution of the electromagnetic field caused by the rivet to estimate a center position of the rivet, A display unit for displaying a center position of the rivet estimated by the computer unit and a defect of the detected rivet, and a power supply unit for supplying power to the sensor unit.
Preferably, the yoke-type exciter for applying the electromagnetic field, the linear array magnetic sensor arranged linearly between the poles of the yoke exciter to measure the distortion of the electromagnetic field generated by the presence of the rivet, And a linear array magnetic sensor for scanning the aircraft structure at a constant speed while maintaining a uniform height with the elliptical aircraft structure, an encoder for generating a signal when the transfer device moves at a predetermined interval, An elastic structure for adhering a linear exciter, a linear array magnetic sensor, a conveying device and an encoder to the surface of the aircraft structure, and a control unit for moving to a center position of the rivet estimated by the computer unit, And an ultrasonic sensor.
Preferably, the linear array magnetic sensor may use a Hall sensor, and the hall sensor may be composed of 64 InSb sensors linearly arranged at intervals of 0.52 mm.
Preferably, the ultrasonic sensor is provided behind the yoke-type exciter and the linear array magnetic sensor, and is provided with an ultrasonic sensor moving device for reciprocating in a direction perpendicular to the traveling direction of the transfer device, To the center position of the rivet.
Preferably, the ultrasonic sensor is capable of automatically detecting the input surface reflection signal and the bottom reflection signal, and detecting the presence or absence of a defect of the rivet by extracting a defect reflection signal.
The ultrasonic sensor may be a membrane type ultrasonic sensor.
Preferably, the signal processing unit amplifies, filters, smoothes, and converts an electric signal generated in the linear array magnetic sensor into a digital signal.
Preferably, the power supply unit includes an alternating-current stabilized power supply for stably supplying alternating-current power to the yoke-type exciter, and a controller for stably supplying the alternating-current power to the elastic structure, the transfer device, the linear array magnetic sensor, the ultrasonic sensor, DC stabilized power supply.
Preferably, the computer unit may be provided with imaging software for imaging the electromagnetic field distribution signal processed through the signal processing unit and displaying the electromagnetic field distribution signal on the display unit.
Preferably, the computer unit may estimate the center position of the rivet by analyzing a distortion distribution of an electromagnetic field due to the rivet by synchronizing the signal processing unit with a signal generated from the encoder.
The present invention has the following excellent effects.
First, the rivet center position of the aircraft structure and the rivet defect are automatically and easily detected by the nondestructive inspection, thereby improving the work efficiency of the operator in defect detection and improving the reliability of the detection result.
In addition, the defect detection result can be converted into a database, and the possibility of occurrence of defects and the replacement cycle of the rivet fastening part can be predicted in advance through the database detection result.
1 is a block diagram showing an entire configuration of a nondestructive inspection apparatus for automatically detecting a center position of an aircraft rivet and a defect of a rivet.
2 is an image showing the entire configuration of a nondestructive inspection apparatus for automatically detecting a center position of an aircraft rivet and a defect of a rivet according to an embodiment of the present invention.
Fig. 3 is an algorithm for center position estimation of rivets and rivets, Fig. 4 is an algorithm for front and rear defect detection of rivets estimated by Fig. 3, and Fig. It is an algorithm for detection.
6 and 7 are images showing the electromagnetic field distortion distribution measured by the linear array magnetic sensor.
8 is a defect detection image of a rivet detected through a non-destructive inspection apparatus for automatically detecting a center position of an aircraft rivet and a rivet defect according to an embodiment of the present invention.
The term used in the present invention is a general term that is widely used at present. However, in some cases, there is a term selected arbitrarily by the applicant. In this case, the term used in the present invention It is necessary to understand the meaning.
Hereinafter, the technical structure of the present invention will be described in detail with reference to preferred embodiments shown in the accompanying drawings.
1 is a block diagram showing an entire configuration of a non-destructive testing apparatus for automatically detecting a center position of an aircraft rivet and a defect of a rivet, FIG. 2 is a block diagram showing the center position of an aircraft rivet according to an embodiment of the present invention Fig. 3 is an algorithm for estimating the center position of a rivet and a rivet, Fig. 4 is a view showing an example of an elliptic curve of the rivet front and rear defects estimated by Fig. 3, Fig. 5 is an algorithm for detecting left and right defects of a rivet estimated by Fig. 3, Figs. 6 and 7 are images showing electromagnetic field distortion distributions measured by a linear array magnetic sensor, Fig. 8 Is a defect detection image of a rivet detected through a nondestructive inspection apparatus for automatically detecting a center position of an aircraft rivet and a rivet defect according to an embodiment of the present invention.
Referring to FIGS. 1 to 8, a nondestructive inspection apparatus for automatically detecting a center position of an aircraft rivet and a defect of a rivet according to an embodiment of the present invention includes: And a sensor portion for applying an electromagnetic field and measuring a distortion of the electromagnetic field generated by the presence of the rivet.
In this case, the aircraft structure refers to a structure in which an aluminum alloy sheet is fastened to a fuselage of an aircraft with a plurality of rivets, and the fastening portion of the rivet has a long period of repeated load change such as takeoff and landing of an aircraft, Or the penetration of moisture is the starting point of defects such as corrosion or fatigue cracks.
The sensor unit includes a yoke type exciter for applying a uniform electromagnetic field to a certain region of the aircraft structure to which the rivet is fastened.
At this time, the yoke exciter generates an eddy current around the rivet at the time of power supply, and the eddy current generated at this time is a skin effect by the following equation (also called propagation effect, and when induction logging is performed from a conductive material, (Which means a decrease in conductivity or an increase in electrical resistivity) of the rivet in the depth direction from the surface around the rivet.
In this case, J s and J t mean the current density at the surface and depth t around the rivet, and δ, f, μ and σ denote the penetration depth, frequency, permeability and conductivity, respectively.
The sensor unit includes a linear array magnetic sensor arranged linearly between the poles of the yoke exciter to measure a distortion of an electromagnetic field generated by the presence of the rivet.
On the other hand, if there is a defect such as a backside corrosion or a fatigue crack in the vicinity of the rivet or rivet, the eddy current flow is distorted around the defect to cause a change in the magnetic field distribution, and the linear array magnetic sensor has the above- It plays a role of measuring.
In this case, the linear array magnetic sensor can use sensors of various types, but in the embodiment of the present invention, a Hall sensor can be used.
However, in the preferred embodiment of the present invention, 64 InSb sensors are arranged linearly at 0.52 mm intervals.
Meanwhile, the sensor unit according to an embodiment of the present invention includes a transfer device for scanning the aircraft structure at a constant speed while maintaining the uniform height of the aircraft structure fastened with the rivet to the yoke type exciter and the linear array magnetic sensor .
At this time, the transfer device is separately provided and moves along a flexible guide plate, at which time the yoke exciter and the linear array magnetic sensor are maintained at a height of 0.5 mm from the surface of the aircraft structure.
Meanwhile, the moving or scanning speed of the transfer device can be variously selected according to need, but it is specified at a speed of 6 mm / s in one embodiment of the present invention.
Meanwhile, the sensor unit according to an embodiment of the present invention may include an encoder for generating a signal when the conveying device moves at a predetermined interval, and a yoke exciter, a linear array magnetic sensor, a conveying device, and an encoder on the surface of the aircraft structure And further comprises an elastic structure for bringing the elastic member into close contact with the elastic member.
At this time, the elastic structure is configured to adhere the yoke exciter, the linear array magnetic sensor, the transfer device and the encoder to the surface of the aircraft structure without being affected by the bending of the surface of the aircraft structure, The structure may be constructed of various elastic bodies in order to achieve the above-mentioned object. Therefore, the present invention is not limited thereto.
Meanwhile, the sensor unit includes an ultrasonic sensor for detecting a defect of the rivet, which is moved to a center position of the rivet estimated by a computer unit, which will be described later.
At this time, the ultrasonic sensor according to an embodiment of the present invention is provided at the rear of the yoke-type exciter and the linear array magnetic sensor, and has an ultrasonic sensor moving device for reciprocating in the direction perpendicular to the traveling direction of the transfer device And is moved to the center position of the rivet estimated by the computer section.
In addition, the ultrasonic sensor automatically distinguishes the input surface reflection signal and the bottom reflection signal and extracts a defect reflection signal to detect the presence or absence of a defect in the rivet.
The ultrasonic sensor may be various ultrasonic sensors, but it is preferable to use a membrane type ultrasonic sensor in one embodiment of the present invention.
Meanwhile, a non-destructive testing apparatus for automatically detecting a center position of an aircraft rivet and a defect of a rivet according to an embodiment of the present invention includes a signal processing unit for processing an electromagnetic field distribution measured through the sensor unit.
At this time, the signal processing unit amplifies, filters, smoothes, and converts electrical signals generated in the linear array magnetic sensor into digital signals.
Meanwhile, a non-destructive testing apparatus for automatically detecting a center position of an aircraft rivet and a defect of a rivet according to an embodiment of the present invention receives a digital signal reflecting the electromagnetic field distribution measured through the signal processing unit, And a computer for analyzing the distortion distribution of the electromagnetic field to estimate the center position of the rivet and to detect a defect of the rivet.
In this case, the computer unit estimates the center position of the rivet by synchronizing the signal processing unit with the signal generated from the encoder to analyze the distortion distribution of the electromagnetic field caused by the rivet. Hereinafter, Will be described in detail.
Referring to FIGS. 6 and 7, it can be seen that two peaks are generated when the X-axis graph of V RMS (FIG. 7 (a)) shows the distortion distribution of the electromagnetic field measured by the linear array magnetic sensor At this time, the center point of the two peak maximum values becomes the center of the X axis of the rivet.
Referring to FIG. 7 (b), N maximum values (N in the embodiment of the present invention) in the distribution of | DELTA V RMS | (absolute value of V RMS ) = 10) is centered on the Y axis of the rivet.
When the information about the center position (X, Y axis) of the rivet obtained by the above-described method is transmitted to the ultrasonic sensor moving device, the ultrasonic sensor moving device moves the ultrasonic sensor .
At this time, the ultrasonic sensor detects the defect of the rivet by irradiating ultrasonic waves while passing the center position of the rivet as described above.
8, a nondestructive inspection apparatus for automatically detecting a center position of a rivet and an rivet of an aircraft according to an embodiment of the present invention includes a rivet surface in a signal shown in FIG. 8, Only the signals between the bottoms can be extracted to determine whether the rivets are defective or not.
That is, if the first peak after the surface peak is above a certain value, it means that there is a defect in the rivet irradiated with ultrasound. In particular, the difference between the first peak and the second peak means the depth from the surface of the rivet defect do.
As a result, the nondestructive inspection apparatus for automatically detecting the center position of the aircraft rivet and the defect of the rivet according to the embodiment of the present invention estimates the center position of the rivet and moves the ultrasonic sensor to the estimated position It is possible to automatically detect the defect of the rivet by irradiating ultrasonic waves while passing the center position of the rivet.
Meanwhile, the computer unit is provided with imaging software for imaging an electromagnetic field distribution signal processed through the signal processing unit and displaying the electromagnetic field distribution signal on a display unit to be described later, and the imaging software can use various software. .
The nondestructive inspection apparatus for automatically detecting the center position of the aircraft rivet and the defect of the rivet according to an embodiment of the present invention may further include a center position of the rivet estimated through the computer unit and a defect of the detected rivet And a power supply unit for supplying power to the sensor unit.
At this time, the display unit can use various monitors including an LED and an LCD, so that the display unit is not limited thereto.
The power supply unit may be implemented by a variety of means. In a preferred embodiment of the present invention, the power supply unit includes an AC stabilized power supply unit for stably supplying AC power to the yoke- , A conveying device, a linear array magnetic sensor, an ultrasonic sensor, and a DC stabilized power supply for stably supplying DC power to the encoder.
As a result, the nondestructive inspection apparatus for automatically detecting the center position of the aircraft rivet and the defects of the rivet according to the embodiment of the present invention, through the technical constructions described above, firstly detects the rivet center position of the aircraft structure and the rivet defect, It is possible to improve the work efficiency of the operator in defect detection and improve the reliability of the detection result.
In addition, the defect detection result can be converted into a database, and the possibility of occurrence of defects and the replacement cycle of the rivet fastening part can be predicted in advance through the database detection result.
While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it is clearly understood that the same is by way of illustration and example only and is not to be taken by way of limitation in the present invention. Various changes and modifications may be made by those skilled in the art.
Claims (11)
A signal processing unit for processing the electromagnetic field distribution measured through the sensor unit;
A computer for receiving a digital signal reflecting the electromagnetic field distribution measured through the signal processing unit and analyzing a distortion distribution of an electromagnetic field caused by the rivet to estimate a center position of the rivet and a defect of the rivet;
A display unit for indicating a center position of the rivet estimated through the computer unit and a defect of the rivet detected; And
And a power supply unit for supplying power to the sensor unit,
The sensor unit
A yoke exciter for applying the electromagnetic field;
An InSb Hall sensor 64 arranged linearly at intervals of 0.52 mm between the poles of the yoke exciter to measure the distortion of the electromagnetic field caused by the presence of the rivet;
A transfer device for scanning the aircraft structure at a speed of 6 mm / s while maintaining the uniform height of the yoke-type exciter and the InSb Hall sensor with the rivet-mounted aircraft structure;
An encoder for generating a signal when the transfer device moves at a predetermined interval;
An elastic structure for bringing the yoke exciter, the InSb Hall sensor, the conveying device, and the encoder into close contact with the surface of the aircraft structure; And
An ultrasonic sensor moving device provided behind the yoke-type exciter and the InSb Hall sensor for reciprocating in a direction perpendicular to the moving direction of the conveying device, and moving to a center position of the rivet estimated by the computer And a membrane type ultrasonic sensor for detecting whether or not the rivet is defective.
The power supply unit includes an AC stabilized power supply unit for stably supplying AC power to the yoke exciter and a DC stabilization unit for stably supplying DC power to the elastic structure, the transfer device, the InSb Hall sensor, the membrane type ultrasonic sensor, Power supply unit,
Wherein the computer unit is provided with imaging software for imaging the electromagnetic field distribution signal processed through the signal processing unit and displaying the electromagnetic field distribution signal on the display unit,
Wherein the signal processing unit amplifies, filters, smoothes, and converts an electric signal generated by the InSb Hall sensor into a digital signal. A nondestructive inspection apparatus for automatically detecting a center position of a rivet and an rivet defect.
Wherein the membrane type ultrasonic sensor automatically detects the input surface reflection signal and the bottom surface reflection signal and extracts a defect reflection signal to detect the presence or absence of a defect in the rivet. A non-destructive testing device for detecting.
Wherein the computer unit estimates the center position of the rivet by synchronizing the signal processing unit with the signal generated by the encoder to analyze the distortion distribution of the electromagnetic field caused by the rivet, For automatically detecting the non-destructive inspection apparatus.
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| KR1020160023918A KR101740909B1 (en) | 2016-02-29 | 2016-02-29 | Nondestructive Testing Equipment for Automatic Rivet Center Positioning and Rivet Defect Inspection |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112132773A (en) * | 2019-06-24 | 2020-12-25 | 曜科智能科技（上海）有限公司 | Airplane head cover riveting point defect detection method, device, equipment and storage medium |
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2016
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112132773A (en) * | 2019-06-24 | 2020-12-25 | 曜科智能科技（上海）有限公司 | Airplane head cover riveting point defect detection method, device, equipment and storage medium |
| CN112132773B (en) * | 2019-06-24 | 2024-04-12 | 曜科智能科技（上海）有限公司 | Method, device, equipment and storage medium for detecting riveting point defect of aircraft head cover |
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