KR101757581B1 - Automatic Inspection Method of Corrosion and Fatigue Cracks around the Aircraft Rivet Jointing and Nondestructive Testing Equipment - Google Patents
Automatic Inspection Method of Corrosion and Fatigue Cracks around the Aircraft Rivet Jointing and Nondestructive Testing Equipment Download PDFInfo
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- KR101757581B1 KR101757581B1 KR1020160023917A KR20160023917A KR101757581B1 KR 101757581 B1 KR101757581 B1 KR 101757581B1 KR 1020160023917 A KR1020160023917 A KR 1020160023917A KR 20160023917 A KR20160023917 A KR 20160023917A KR 101757581 B1 KR101757581 B1 KR 101757581B1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/30—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight
- G01N3/317—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight generated by electromagnetic means
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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
- G01M13/00—Testing of machine parts
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- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N17/00—Investigating resistance of materials to the weather, to corrosion, or to light
- G01N17/02—Electrochemical measuring systems for weathering, corrosion or corrosion-protection measurement
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- 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
- G01N27/90—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws using eddy currents
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/006—Crack, flaws, fracture or rupture
- G01N2203/0067—Fracture or rupture
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0073—Fatigue
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Abstract
The present invention relates to a nondestructive inspection apparatus for automatically detecting backside corrosion and fatigue cracks around an rivet of an aircraft, and more particularly, to a non-destructive inspection apparatus for applying a uniform electromagnetic field to a predetermined region of an aircraft structure fastened with a metallic rivet, A sensor unit for measuring a distortion of an electromagnetic field generated by the presence; A signal processing unit for processing the electromagnetic field distribution measured through the sensor unit; A defect reader for estimating the backside corrosion and fatigue cracks around the rivet through distribution of the electromagnetic field processed through the signal processor; A display unit for visually confirming a defect estimated through the defect reading unit; A control unit for controlling the sensor unit, the signal processing unit, the defect reading unit, and the display unit; And a power supply unit for supplying power to the sensor unit, the signal processing unit, the defect reading unit, and the display unit.
Description
The present invention relates to a nondestructive inspection apparatus for automatically detecting backside corrosion and fatigue cracks around an rivet of an aircraft, and more particularly, to a structure of a long-term operational aircraft, particularly to a rivet used for fastening a skeleton of a plane to an aircraft And to a nondestructive inspection apparatus for automatically detecting backside corrosion and fatigue cracks around an aircraft rivet for automatically detecting backside corrosion and fatigue cracks.
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.
Therefore, it is inevitable to develop an efficient equipment or algorithm for detecting damage or defects existing around the rivet joint portion of the aircraft structure.
Disclosure of Invention Technical Problem [8] Accordingly, the present invention has been made to solve the above-mentioned problems, and it is an object of the present invention to provide a method of detecting defects such as back corrosion or fatigue cracks existing around a rivet fastening portion of an aircraft structure, It is an object of the present invention to provide a nondestructive inspection apparatus for automatically detecting backside corrosion and fatigue cracks around an aircraft rivet which can improve worker efficiency and improve reliability of detection results.
In addition, it is possible to database the defect detection results and to detect the backside corrosion and fatigue crack around the aircraft rivet which can forecast the possibility of occurrence of defects and replacement cycle of the rivet fastening part through the database- It is another purpose to provide the inspection apparatus.
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-mentioned objects, a nondestructive inspection apparatus for automatically detecting backside corrosion and fatigue cracks around an airplane rivet according to an embodiment of the present invention, A sensor section for measuring the distortion of the electromagnetic field generated by the presence of the rivet, and a signal processing section for processing the electromagnetic field distribution measured through the sensor section. A defect reading unit for estimating a backside corrosion and a fatigue crack around the rivet through a distribution of electromagnetic fields processed through the signal processing unit, a display unit for visually confirming a defect estimated through the defect reading unit, A control unit for controlling the signal processing unit, the defect reading unit, and the display unit, and a power supply unit for supplying power to the sensor unit, the signal processing unit, the defect reading unit, and the display unit.
Preferably, the sensor unit includes a yoke exciter for applying the electromagnetic field, a linear array magnetic sensor linearly arranged between the poles of the yoke exciter to measure a distortion of an electromagnetic field generated by the presence of the rivet, A transfer device for scanning the aircraft structure at a constant speed while maintaining a uniform height with the aircraft structure fastened with the rivet, and an encoder for generating a signal when the transfer device moves at a predetermined interval, And an elastic structure for bringing the yoke exciter, the linear array magnetic sensor, the transfer device, and the encoder into close contact with the surface of the aircraft structure.
Preferably, the linear array magnetic sensor may be any one selected from the group consisting of a coil sensor, a hall sensor, and a giant magnetoresistive sensor.
Preferably, the Hall sensor may be composed of 64 InSb sensors arranged linearly at intervals of 0.52 mm.
Preferably, the signal processing unit includes an analog signal processing device for amplifying, filtering, smoothing, and converting an electrical signal measured through the linear array magnetic sensor into a digital signal, and an analog signal processing device for synchronizing the analog signal processing device with a signal generated by the encoder And a digital signal processing device for inputting a digital signal reflecting the electromagnetic field distribution around the rivet.
Preferably, the defect reading unit includes a backside corrosion discriminating means for estimating the presence, the position and the size of the backside corrosion, and the fatigue crack discriminating means for estimating the presence, the position and the size of the fatigue crack.
Preferably, the backside corrosion determination means estimates the center position of the rivet in the electromagnetic field distribution input from the digital signal processing apparatus, compares the predetermined number of electromagnetic field distributions with the center position of the rivet, Location, and size of the image.
Preferably, the fatigue crack discriminating means estimates the center position of the rivet in the electromagnetic field distribution input from the digital signal processor, compares an average of a predetermined number of maximum and minimum values with data of a defect-free specimen selected in advance The presence, position, and size of fatigue cracks can be estimated.
The present invention has the following excellent effects.
First, defects such as backside corrosion or fatigue cracks existing around the rivet fastening portion of the aircraft structure can be automatically detected easily and easily through the nondestructive inspection.
Further, 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 a defect and replacement cycle of the rivet fastening portion can be predicted in advance through a database-based detection result.
1 is a block diagram showing the overall configuration of a nondestructive inspection apparatus for automatically detecting backside corrosion and fatigue cracks around an aircraft rivet according to an embodiment of the present invention.
2 is a perspective view showing a yoke-type exciter and a linear array magnetic sensor according to an embodiment of the present invention.
3 to 7 are images showing the detection results of defects according to the position and size of the periphery of the rivet using the nondestructive inspection apparatus for automatically detecting the backside corrosion and the fatigue crack around the airplane rivet shown in FIG.
8 is an image showing a comparison result between a case where no defect exists in the vicinity of the rivet and a case where a defect exists.
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 overall configuration of a nondestructive test apparatus for automatically detecting backside corrosion and fatigue cracks in the vicinity of an aircraft rivet according to an embodiment of the present invention; FIG. 3 is a perspective view showing a yoke-type exciter and a linear array magnetic sensor according to an embodiment of the present invention. FIG. 3 to FIG. FIG. 8 is an image showing a result of detection of a defect according to the position and size of the periphery, and FIG. 8 is an image showing a comparison result between a case where no defect exists in the vicinity of the rivet and a case where a defect exists.
1 to 8, a nondestructive inspection apparatus for automatically detecting backside corrosion and fatigue cracks in the vicinity of an aircraft rivet according to an embodiment of the present invention includes a nondestructive inspection apparatus for automatically detecting a backside corrosion and a fatigue crack in an aircraft structure having a metal rivet And a sensor portion for applying a uniform electromagnetic field to a predetermined region 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 may include a yoke exciter 120 for applying a uniform electromagnetic field to a certain region of the aircraft structure to which the rivet is fixed. .
At this time, the
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
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 the rivet, the eddy current flow is distorted in the periphery of the defect to cause a change in the magnetic field distribution and the linear array
In this case, the linear array
However, in the preferred embodiment of the present invention, the Hall sensor is used. In this case, the Hall sensor is composed of 64 InSb sensors linearly arranged at intervals of 0.52 mm.
Meanwhile, the sensor unit according to an embodiment of the present invention includes the yoke-
At this time, the transfer device is separately provided and moves along a flexible guide plate, where the yoke exciter 120 and the linear array
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 includes an encoder for generating a signal when the transfer device moves at a predetermined interval, and the yoke exciter 120, the linear array
At this time, the elastic structure is configured to adhere the yoke exciter 120, the linear array
Meanwhile, a non-destructive testing apparatus for automatically detecting backside corrosion and fatigue cracks around an aircraft 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.
The signal processing unit includes an analog signal processing unit for amplifying, filtering, smoothing, and converting an electric signal measured through the linear array
Meanwhile, the nondestructive inspection apparatus for automatically detecting the backside corrosion and the fatigue crack in the vicinity of the aircraft rivet according to an embodiment of the present invention is characterized in that the backside corrosion and the fatigue cracks around the rivet through the distribution of the electromagnetic field processed through the signal processing unit And a defect reading unit for estimating a defect.
At this time, the backside corrosion discrimination means can read the backside corrosion or the fatigue crack around the rivet or the rivet through various methods, but in one embodiment of the present invention, the backside corrosion discrimination software provided inside the backside corrosion discrimination means Position, and size of backside corrosion by estimating the center position of the rivet in the electromagnetic field distribution input from the digital signal processing apparatus and comparing the predetermined number of electromagnetic field distributions with the center position of the rivet.
In addition, the fatigue crack discrimination means according to an embodiment of the present invention estimates the center position of the rivet in the electromagnetic field distribution input from the digital signal processing apparatus through the fatigue crack discrimination software provided in the fatigue crack discrimination means, Position, and size of the fatigue crack by comparing the average of the predetermined maximum and minimum value positions with the data of the previously selected defect-free specimen.
Meanwhile, a non-destructive testing apparatus for automatically detecting backside corrosion and fatigue cracks around an aircraft rivet according to an embodiment of the present invention includes a display unit for visually confirming a defect estimated through the defect reading unit.
At this time, the display unit can use various means of monitors including an LED and an LCD monitor, so that it is not limited thereto.
Meanwhile, a non-destructive testing apparatus for automatically detecting backside corrosion and fatigue cracks around an aircraft rivet according to an embodiment of the present invention includes a sensor unit, a signal processing unit, a defect reading unit, a controller for controlling the display unit, , A signal processing unit, a defect reading unit, and a power supply unit for supplying power to the display unit.
At this time, the control unit comprises a computer in which a control program is installed.
In addition, since the power supply unit can use various power supply units having DC and AC stabilization circuits, it is not limited thereto.
3, which is an image showing the result of detection of defects according to the position and size of the circumference of the rivet using a nondestructive testing apparatus for automatically detecting the backside corrosion and the fatigue crack around the rivet in accordance with the embodiment of the present invention, To 7, when the backside corrosion defects are located forward and backward in the scanning direction, the groups extend or move in the same direction.
When the backside corrosion defect is present on the left or right side of the scanning direction, the phenomenon of widening in the corresponding direction can be seen.
Referring to FIG. 7, it can be seen that when the fatigue crack exists, the group extends to the left or both sides. As the length of the fatigue crack increases, the relative extension of the corresponding group increases.
In this case, the abscissa indicates the diameter of the defect hole, and the ordinate indicates the depth of the defect.
As a result, the nondestructive inspection apparatus for automatically detecting the backside corrosion and the fatigue crack around the airplane rivet according to the embodiment of the present invention, through the above-described technical constructions, Defects such as fatigue cracks can be automatically and easily detected by nondestructive testing.
Further, 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 a defect and replacement cycle of the rivet fastening portion can be predicted in advance through a database-based 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.
110: Power supply
120: yoke type girl
130: linear array magnetic sensor
Claims (8)
A signal processing unit for processing the electromagnetic field distribution measured through the sensor unit;
A defect reader for estimating the backside corrosion and fatigue cracks around the rivet through distribution of the electromagnetic field processed through the signal processor;
A display unit for visually confirming a defect estimated through the defect reading unit;
A control unit for controlling the sensor unit, the signal processing unit, the defect reading unit, and the display unit; And
And a power supply unit for supplying power to the sensor unit, the signal processing unit, the defect reading unit, and the display unit. The non-destructive inspection apparatus for automatically detecting backside corrosion and fatigue cracks around an rivet of an aircraft.
The sensor unit
A yoke exciter for applying the electromagnetic field;
A linear array magnetic sensor arranged linearly between poles of the yoke exciter to measure a distortion of an electromagnetic field generated by the presence of the rivet;
A transfer device for scanning the aircraft structure at a constant speed while maintaining the uniform height of the yoke-type exciter and linear array magnetic sensor with the elliptical aircraft structure;
An encoder for generating a signal when the transfer device moves at a predetermined interval; And
And a resilient structure for bringing the yoke exciter, the linear array magnetic sensor, the transfer device, and the encoder into close contact with the surface of the aircraft structure. The non-destructive method for automatically detecting backside corrosion and fatigue cracks around an aircraft rivet Inspection device.
Wherein the linear array magnetic sensor uses any one selected from the group consisting of a coil sensor, a Hall sensor, and a giant magnetoresistive sensor. The non-destructive testing apparatus for automatically detecting backside corrosion and fatigue cracks around an rivet of an aircraft.
Wherein the Hall sensor comprises 64 InSb sensors linearly arranged at intervals of 0.52 mm. A nondestructive inspection apparatus for automatically detecting backside corrosion and fatigue cracks around an rivet of an aircraft.
The signal processing unit:
An analog signal processing device for amplifying, filtering, smoothing and converting an electrical signal measured through the linear array magnetic sensor into a digital signal; And
And a digital signal processing device for synchronizing the analog signal processing device with a signal generated by the encoder to input a digital signal reflecting the electromagnetic field distribution around the rivet, wherein the backside corrosion and fatigue cracks around the rivet A non-destructive testing device for detecting.
The defect reading unit
A backside corrosion discriminating means for estimating the presence / absence, position and size of the backside corrosion; And
And a fatigue crack discriminating means for estimating the presence / absence, the position and the size of the fatigue cracks. The nondestructive test apparatus for automatically detecting backside corrosion and fatigue cracks around an aircraft rivet.
The backside corrosion determination means estimates the center position of the rivet in the electromagnetic field distribution input from the digital signal processing apparatus and compares the predetermined number of electromagnetic field distributions between the center positions of the rivets to determine the presence or absence of backside corrosion, Wherein the non-destructive inspection apparatus automatically estimates the backside corrosion and fatigue cracks around the rivet of the aircraft.
Wherein the fatigue crack discriminating means estimates the center position of the rivet in the electromagnetic field distribution input from the digital signal processing apparatus and compares an average of a predetermined number of maximum and minimum positions with data of a previously selected defect sample, Position, and size of the rivet around the rivet of the aircraft. The non-destructive inspection apparatus for automatically detecting the backside corrosion and the fatigue crack around the rivet of the aircraft.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR1020160023917A KR101757581B1 (en) | 2016-02-29 | 2016-02-29 | Automatic Inspection Method of Corrosion and Fatigue Cracks around the Aircraft Rivet Jointing and Nondestructive Testing Equipment |
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| Application Number | Priority Date | Filing Date | Title |
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| KR1020160023917A KR101757581B1 (en) | 2016-02-29 | 2016-02-29 | Automatic Inspection Method of Corrosion and Fatigue Cracks around the Aircraft Rivet Jointing and Nondestructive Testing Equipment |
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| KR101757581B1 true KR101757581B1 (en) | 2017-07-13 |
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Non-Patent Citations (2)
| Title |
|---|
| Eddy Current Testing and Evaluation of Far-Side Corrosion Around Rivet in Jet-Engine Intake of Aging Supersonic Aircraft, Jungmin Kim, J Nondestruct Eval, 2014, Vol.33, pp.471-480 |
| 전자기장의 왜곡을 이용한 내열합금 점용접부 이면균열 검출 및 평가, 김세진, 대한기계학회 2015년도 춘계학술대회 논문집 |
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