[go: up one dir, main page]

CN119269630A - Wing defect detection device and method - Google Patents

Wing defect detection device and method Download PDF

Info

Publication number
CN119269630A
CN119269630A CN202411382546.8A CN202411382546A CN119269630A CN 119269630 A CN119269630 A CN 119269630A CN 202411382546 A CN202411382546 A CN 202411382546A CN 119269630 A CN119269630 A CN 119269630A
Authority
CN
China
Prior art keywords
wing
defect
imaging
section
detection
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202411382546.8A
Other languages
Chinese (zh)
Inventor
杨栋
毛思岩
王伟
张彦杰
栗永利
李天佑
李佳东
梁孟婷
徐智慧
吕建华
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
State Grid Electric Power Research Institute Of Sepc
Taiyuan University of Technology
North China Electric Power University
Original Assignee
State Grid Electric Power Research Institute Of Sepc
Taiyuan University of Technology
North China Electric Power University
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by State Grid Electric Power Research Institute Of Sepc, Taiyuan University of Technology, North China Electric Power University filed Critical State Grid Electric Power Research Institute Of Sepc
Priority to CN202411382546.8A priority Critical patent/CN119269630A/en
Publication of CN119269630A publication Critical patent/CN119269630A/en
Pending legal-status Critical Current

Links

Classifications

    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N21/00—Investigating or analysing materials by the use of optical means, i.e. using sub-millimetre waves, infrared, visible or ultraviolet light
    • G01N21/84—Systems specially adapted for particular applications
    • G01N21/88—Investigating the presence of flaws or contamination
    • 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
    • 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

Landscapes

  • Physics & Mathematics (AREA)
  • Analytical Chemistry (AREA)
  • General Health & Medical Sciences (AREA)
  • Pathology (AREA)
  • Immunology (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • General Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Biochemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Acoustics & Sound (AREA)
  • Transportation (AREA)
  • Manufacturing & Machinery (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Signal Processing (AREA)
  • Investigating Or Analyzing Materials By The Use Of Ultrasonic Waves (AREA)

Abstract

本发明涉及零件缺陷检测技术领域，公开了一种机翼缺陷检测装置及方法，包括升降台和导轨平台，升降台和导轨平台分别固定在地面上且平行设置；旋转组件，包括连接圆盘和主轴，连接圆盘通过主轴转动连接在升降台顶端，连接圆盘远离升降台的一侧固定连接有两转盘接头，机翼与转盘接头连接；检测组件，包括三轴移动台和激光超声探头，三轴移动台设置在导轨平台上，激光超声探头固定连接在三轴移动台上用于对机翼进行检测。本发明采用一种单激发点双检测点的激光超声探头，能够同时测得翼展方向和翼周方向的超声信号，本发明灵敏度、分辨率高，能够在翼展和翼周方向完成亚表面缺陷、表面缺陷检测，及内部缺陷的三维成像，检测效果全面、准确。

The present invention relates to the technical field of parts defect detection, and discloses a wing defect detection device and method, including a lifting platform and a guide rail platform, the lifting platform and the guide rail platform are respectively fixed on the ground and arranged in parallel; a rotating component, including a connecting disc and a main shaft, the connecting disc is connected to the top of the lifting platform through the rotation of the main shaft, and the side of the connecting disc away from the lifting platform is fixedly connected with two turntable joints, and the wing is connected to the turntable joint; a detection component, including a three-axis moving platform and a laser ultrasonic probe, the three-axis moving platform is arranged on the guide rail platform, and the laser ultrasonic probe is fixedly connected to the three-axis moving platform for detecting the wing. The present invention adopts a laser ultrasonic probe with a single excitation point and a double detection point, which can simultaneously measure ultrasonic signals in the wingspan direction and the wing circumference direction. The present invention has high sensitivity and resolution, can complete sub-surface defect and surface defect detection in the wingspan and wing circumference directions, and three-dimensional imaging of internal defects, and the detection effect is comprehensive and accurate.

Description

Wing defect detection device and method
Technical Field
The invention relates to the technical field of part defect detection, in particular to a wing defect detection device and method.
Background
With the rapid development of modern industry, the requirements on the precision and the reliability of parts are higher and higher, and particularly for curved structural parts, the parts play a vital role in the fields of aviation, aerospace, automobiles, precision machinery and the like. Conventional non-destructive inspection techniques face many challenges in inspecting defects due to their complex geometry. The wing is a typical curved structural part, and is also an important component of the aircraft, and the structural integrity of the wing directly influences the safety and performance of the aircraft. Defects may lead to weakening of the wing structure, formation of fatigue cracks and reduced air tightness and stability, which in turn pose a potential threat to the flight safety and performance of the aircraft. Therefore, the accurate and timely detection of the wing defects has great necessity, can help to find and repair potential defects, and ensures the structural integrity and safe operation of the wing, thereby ensuring the safety of the aircraft and passengers thereof.
With the development of the aerospace industry and the advancement of technology, the selection and design of wing materials is increasingly important. The traditional aluminum alloy is replaced by metal materials such as titanium alloy, magnesium alloy and the like and advanced materials such as carbon fiber composite materials, glass fiber composite materials and the like so as to meet the requirements on light weight, high strength and design flexibility. Taking carbon fiber composite materials as an example, since the structure of the carbon fiber composite materials is generally composed of a plurality of layers of fibers and resins, such a multi-layer structure makes it difficult to accurately grasp the position and morphology of defects. Secondly, due to defects such as bubbles, interlayers, fiber breaks and the like which may exist in the manufacturing process of the carbon fiber composite material, the defects are often not easy to observe by naked eyes or detect by a traditional detection method. Therefore, for defect detection of curved structural parts such as composite wings, a high-sensitivity and high-resolution detection method for wing defect detection device and method is needed, and the device and method can go deep into the inside of a multilayer structure of a composite material to carry out comprehensive and accurate detection.
Disclosure of Invention
The invention aims to provide a wing defect detection device and method for solving the problems in the prior art.
In order to achieve the above purpose, the invention provides a wing defect detection device, comprising:
The lifting platform and the guide rail platform are respectively fixed on the ground and are arranged in parallel;
The rotating assembly comprises a connecting disc and a main shaft, the connecting disc is rotationally connected to the top end of the lifting platform through the main shaft, two turntable joints are fixedly connected to one side, away from the lifting platform, of the connecting disc, and the wing is connected with the turntable joints;
the detection assembly comprises a triaxial mobile station and a laser ultrasonic probe, the triaxial mobile station is arranged on the guide rail platform, and the laser ultrasonic probe is fixedly connected to the triaxial mobile station and used for detecting the wing;
The laser ultrasonic probe is a single-excitation-point double-detection-point laser ultrasonic probe.
Preferably, the two turntable joints are respectively positioned at two sides of the connecting disc and positioned on the same diameter line.
Preferably, the lifting table is fixedly connected with a transmission case, a servo motor is fixedly connected in the transmission case, an output shaft of the servo motor is connected with the main shaft through a speed reducer, a coupler and an absolute photoelectric encoder, and a gap is arranged between the main shaft and the lifting table.
A wing defect detection method comprising the steps of:
s1, mounting the wing on the connecting disc for laser ultrasonic scanning;
s2, performing subsurface crack defect detection on the wing;
S3, detecting surface crack defects of the wing;
s4, performing three-dimensional imaging on the wing to obtain a three-dimensional image of the internal defect of the wing.
Preferably, in the step S1, the wing is kept parallel to the horizontal plane in the initial position, the height of the lifting platform is H J, the distance between the main shaft and the top surface of the lifting platform is H z, and the maximum wing width of the wing is W max, so that H J+hz≥1.5Wmax is satisfied;
The height of the guide rail platform is H, the initial height of the Z axis of the triaxial mobile station is Z pt0, and H J+hz＝H+Zpt0 is met.
Preferably, during laser ultrasonic scanning, a global rectangular coordinate system X-Y-Z is firstly established, the X direction points to the wingspan direction of the wing at the initial position, the Y direction points to the wingspan direction vertical to the X direction, the XOY plane is parallel to the horizontal plane, the direction vertical to the XOY plane is the Z direction, then the surface of the wing is scattered into points, laser ultrasonic scanning is carried out along a discretization curve by connecting a plurality of discrete points into a line, a local coordinate system Lm-Ln-Lz is established according to the scanning curve, and a wingspan direction data set p (I 1i,Lm,t),p(I1i, lm, t) and a wingspan direction data set p (J j, ln, t) are obtained and used for imaging defects.
Preferably, the subsurface crack defect is a planar defect, and in the case that a subsurface defect is located in the wingspan section LnOLz corresponding to the wingspan curve J s, the detection of the subsurface defect is realized by utilizing the wingspan data set p (J j, ln, t), and the specific steps of the subsurface crack defect detection process are as follows:
Determining the vertex coordinates Ln 0 of subsurface defects, namely, in the scanning process, only scanning data p (J s, ln, t) on a wing circumferential direction curve J s, generating a defect echo signal RL, and observing the defect echo signal RL of a scanning dataset to determine the wing circumferential section where the subsurface defects are located;
Observing scanning data p (J s, ln, t), and obtaining subsurface defect vertex coordinates Ln 0 when the arrival time t RL of the reflected wave RL obtains the minimum value and the defect vertex is positioned at the midpoint of an excitation point and a detection point II in the Ln direction;
Determination of subsurface defect vertex coordinates Lz 0, wherein the defect vertex coordinates are (Ln 0,Lz0), the coordinates of excitation points are (Ln 1, 0), the coordinates of detection points two are (Ln 1 +l, 0), l is the distance between the excitation points and the detection points two, and c is the wave velocity, then the subsurface crack burial depth Lz 0 can be calculated by the following formula:
Sub-surface defect detection of spanwise cross-sections is performed by scanning data sets p (I 1i, lm, t) and p (I 2i, lm, t).
Preferably, the surface crack defect is a planar defect, and in the case that a surface defect is located in the span section LmOLz corresponding to the span curve I 1s, the specific steps of surface defect detection are as follows:
Sequentially drawing all scanned spanwise cross-section B pictures according to a scanned data set p (I 1i, lm, t);
In the scanning process, the excitation point and the detection point are fixed, when no defect exists between the excitation point and the detection point, the propagation time of the surface acoustic wave from the excitation point to the detection point is the same, and B scanning imaging is carried out to form a continuous straight line;
When a defect exists between the excitation point and the detection point, most waves are reflected when the surface waves are transmitted to the side edge of the defect from the excitation point, the detected signal intensity at the detection point is very low, and the scanning imaging is carried out to form a straight line with a gap, so that the wingspan section I 1s where the position of the surface defect is located is determined;
The notch position in the B scanning chart is the position of the surface defect, and spanwise coordinates Lms1 and Lms2 can be obtained according to the B scanning chart;
surface defect detection of the airfoil circumferential section was performed by p (J s, ln, t).
Preferably, three-dimensional imaging can be achieved in two ways according to the scanned data sets p (I 1i,Lm,t),p(I2i, lm, t) and p (J j, ln, t), and the position and shape of the internal defect are presented;
Extracting a two-dimensional dataset p 1i (Lm, t) corresponding to a spanwise curve I 1i for focused imaging of a two-dimensional spanwise section corresponding to a spanwise curve I 1i, wherein the specific steps include calculating an equivalent velocity in a frequency-wavenumber domain by a numerical calculation method, calculating a phase shift factor according to the equivalent velocity, and calculating a two-dimensional spectrum extrapolation and an imaging matrix, wherein the equivalent velocity can be calculated by the following formula:
Changing imaging depth Lz, repeating the steps until the amplitude value calculation of all imaging points is completed, and obtaining an imaging matrix I (Lm, lz) of a two-dimensional span section corresponding to a span curve I 1i;
Collecting all spanwise cross-section imaging matrixes to obtain a three-dimensional imaging matrix I (I 1i, lm, lz) of the wing in the section L 1;
And carrying out coordinate conversion to obtain a three-dimensional imaging matrix I (x, y, z) under a rectangular coordinate system, and imaging.
Preferably, the specific steps of three-dimensional imaging of the wing based on the wing circumferential scan data set p (J j, ln, t) are as follows:
Dividing the peripheral section of the wing into a plurality of contour sections, expanding the outer contour into a straight line, expanding the peripheral section of the wing in the imaging section into a plane, and performing frequency domain imaging in the imaging section to obtain a plane frequency domain imaging matrix in the contour section;
splicing the curved surface imaging in all the contour sections into a frequency domain imaging matrix I (Ln, lz) of a two-dimensional section of the wing circumference corresponding to a wing circumference curve J j;
And sequentially performing two-dimensional spanwise section imaging corresponding to the peri-wing curve, and collecting all peri-wing section imaging matrixes to obtain a three-dimensional imaging matrix I (J j, ln, lz) of the wing.
Compared with the prior art, the invention has the following advantages and technical effects:
1. According to the wing defect detection device provided by the invention, nondestructive detection is performed on the wing skin defect of the carbon fiber composite material, the wing is arranged on the connecting disc, the main shaft drives the wing to rotate, the triaxial mobile station adjusts the position of the laser ultrasonic probe, so that the omnibearing non-contact detection of the wing is realized, and the tangent line at the excitation point at any moment is kept vertical, thereby facilitating the detection of the laser ultrasonic probe, and further realizing the omnibearing detection of the wing.
2. According to the wing defect detection method provided by the invention, the wing is scattered into a space curve in a discrete mode aiming at the defect of the irregular surface of the wing, which is difficult to detect in a traditional scanning mode, so that the resolution is improved, and the wing defect detection method can go deep into the inside of a multilayer structure of a composite material to carry out comprehensive and accurate detection.
3. According to the invention, the laser ultrasonic probe with single excitation point and double detection points is adopted, ultrasonic signals in the wingspan direction and the wingspan direction can be measured simultaneously, and the wingspan curve scanning data set can be obtained in a simple and convenient manner by matching with the laser ultrasonic scanning mode provided by the invention, so that three-dimensional imaging of defects is performed.
4. The detection method provided by the invention can simultaneously carry out surface defects and subsurface defects in the wingspan direction and the wingspan direction, and avoid missed detection caused by crack orientation.
Drawings
For a clearer description of an embodiment of the invention or of the solutions of the prior art, the drawings that are needed in the embodiment will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art:
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 is a schematic view of a rotary assembly according to the present invention;
FIG. 3 is a schematic view of discrete points on the surface of an airfoil according to the present invention;
FIG. 4 is a schematic diagram of the operation of the laser ultrasonic probe of the present invention;
FIG. 5 is a schematic diagram of subsurface defect detection according to the present invention;
FIG. 6 is a schematic diagram of the surface defect detection of the present invention;
FIG. 7 is a view showing an example of scanning for surface crack defects B according to the present invention;
FIG. 8 is a schematic diagram of an equivalent speed calculation of the present invention;
FIG. 9 is a view of an exemplary two-dimensional cross-sectional focused imaging of a span curve in accordance with the present invention;
FIG. 10 is a three-dimensional imaging exemplary view of a defect in accordance with the present invention;
FIG. 11 is a diagram illustrating an exemplary two-dimensional cross-sectional focused imaging of a peripter curve in accordance with the present invention;
FIG. 12 is a schematic diagram of a second embodiment of the present invention;
FIG. 13 is a schematic view of a second embodiment of a rotary clamping member;
wherein, 1, lifting platform; 2, a guide rail platform, 3, a connecting disc, 4, a main shaft, 5, a turntable joint, 6, a wing, 7, a triaxial mobile station, 8, a laser ultrasonic probe, 9, a transmission case, 10, a servo motor, 11, a speed reducer, 12, a coupler, 13, an absolute photoelectric encoder, 14, a turntable, 15, a mobile clamping slide rail, 16, a mobile slide rail, 17 and a driving motor.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
Embodiment one:
referring to fig. 1 to 11, the present invention provides an apparatus for detecting wing defects, comprising:
the lifting platform 1 and the guide rail platform 2 are respectively fixed on the ground and are arranged in parallel;
the rotating assembly comprises a connecting disc 3 and a main shaft 4, wherein the connecting disc 3 is rotationally connected to the top end of the lifting platform 1 through the main shaft 4, two turntable joints 5 are fixedly connected to one side, away from the lifting platform 1, of the connecting disc 3, and wings 6 are connected with the turntable joints 5;
the detection assembly comprises a triaxial moving table 7 and a laser ultrasonic probe 8, wherein the triaxial moving table 7 is arranged on the guide rail platform 2, and the laser ultrasonic probe 8 is fixedly connected to the triaxial moving table 7 for detecting the wing 6;
the laser ultrasonic probe 8 is a single-excitation-point double-detection-point laser ultrasonic probe.
Further optimizing scheme, two carousel joints 5 are located respectively and connect disc 3 both sides, and are located same diameter line.
According to a further optimization scheme, a transmission case 9 is fixedly connected to the lifting table 1, a servo motor 10 is fixedly connected to the transmission case 9, an output shaft of the servo motor 10 is connected with a main shaft 4 through a speed reducer 11, a coupling 12 and an absolute photoelectric encoder 13, and a gap is formed between the main shaft 4 and the lifting table 1.
A wing defect detection method comprising the steps of:
S1, mounting a wing 6 on a connecting disc 3 for laser ultrasonic scanning;
S2, performing subsurface crack defect detection on the wing 6;
s3, detecting surface crack defects of the wing 6;
s4, performing three-dimensional imaging on the wing 6 to obtain a three-dimensional image of the internal defect of the wing 6.
In one embodiment of the invention, the defect detection is the detection of surface, subsurface, internal defects of the wing 6.
In the further optimization scheme, in the S1, when the wing 6 is in the initial position, the wing 6 is kept parallel to the horizontal plane, the height of the lifting platform 1 is H J, the distance between the main shaft 4 and the top surface of the lifting platform 1 is H z, and the maximum wing width of the wing 6 is W max, so that H J+hz≥1.5Wmax is satisfied;
The height of the guide rail platform 2 is H, the initial height of the Z axis of the triaxial mobile platform 7 is Z pt0, and H J+hz＝H+Zpt0 is satisfied.
In a further optimization scheme, a global rectangular coordinate system X-Y-Z is firstly established during laser ultrasonic scanning, the X direction points to the wingspan direction of the wing 6 at the initial position, the Y direction points to the wingspan direction vertical to the X direction, the XOY plane is parallel to the horizontal plane, the direction vertical to the XOY plane is the Z direction, then the surface of the wing 6 is scattered into points, the laser ultrasonic scanning is carried out along a discretization curve by connecting a plurality of discrete points into a line, a local coordinate system Lm-Ln-Lz is established according to the scanning curve, and a wingspan direction data set p (I 1i,Lm,t),p(I1i, lm, t) and a wingspan direction data set p (J j, ln, t) are obtained and are used for imaging defects.
In one embodiment of the present invention, when a defect is imaged, the surface of the wing 6 is first discretized into points, as shown in fig. 3, by connecting a plurality of discrete points into a line, laser ultrasonic scanning in S1 is facilitated, the spanwise direction of the surface of the wing 6 is M, the circumferential direction of the wing is N, the distance λ between every two discrete points on the left side of the wing 6 in the N direction, the contour line in the direction is discretized into N points, the perimeter c 0 =n×λ of the contour line on the leftmost side is measured once every distance λ along the M direction, the perimeter c n of the contour line on the N direction is measured once every distance λ along the M direction, the perimeter c m of the contour line of the wing 6 at the M λ position on the leftmost side of the wing 6 is recorded, each contour line is discretized into N points, the distance between every two points of the contour line of the wing 6 in the N direction is c mλ/c0, the wing 6 is divided into M segments of contour lines in the M direction, the total length of the wing 6 in the M direction is l=m×x, the wing 6 is divided into two segments of the left and right and the length of the wing 6 is divided into two segments of the m× 1+m2 M (the two discrete points in the m×n directions of the surface of the wing 1＝m1×λ,L2＝m2);
Establishing a coordinate system, namely establishing a global space rectangular coordinate system X-Y-Z at the end part of the wing 6 by taking the joint center point of the two wings 6 as an origin O, wherein the X direction points to the wingspan direction of the wing 6 at an initial position, the Y direction points to the wingspan direction vertical to the X direction, the XOY plane is parallel to a horizontal plane, the direction vertical to the XOY plane is the Z direction, the coordinates (d, e and f) of each discrete point are determined through a secondary coordinate system, when the wing 6 is at the initial position, the transverse maximum plane of the wing 6 is parallel to the XOY plane, the position of the bottom plate of the triaxial moving platform 7 on the X-Y-Z coordinate is (0, e 0,fpt0)-(L,e0,fpt0), L is the wingspan length of the wing 6, e 0 is the distance between the triaxial moving platform 7 and the wing 6, and e 0≥0.5Wmax+0.5Wpt,Wpt is the width of the guide rail platform 2;
Connecting discrete points into a line, namely connecting the discrete points into curves along the N direction in two profile sections of L 1 and L 2 to form a wing 6 wing circumferential section profile curve, connecting the discrete points along the N direction with the discrete points on the next section profile curve closest to each point along the M direction to form a spanwise curve, jointly forming a reticular space curve, defining the curve along the M direction closest to the laser ultrasonic probe 8 in the initial state as I 10, defining the curve along the N direction as I 1i in the L 1 section, defining the curve along the N direction as I 2i in the L 2 section, defining the curve along the leftmost N direction of the wing 6 in the initial state as J 0, and defining the curve along the M direction as J x lambda as J j;
The method comprises the steps of L 1 section scanning, firstly solving a tangent f-f 0＝k0(e-e0 of J 0 at the intersection point (d 0,e0,f0) of J 0 and I 10, calculating the inclination angle of the tangent at the point by k 0, driving the wing 6 to rotate by the connecting disc 3 to keep the tangent vertical, regulating the position of the laser ultrasonic probe 8 by the Z axis to enable a laser path to be vertical to a curve I 10 at the intersection point, scanning the leftmost end of the wing 6 at a speed v along the I 10 to the right, stopping moving when the X-direction scanning position is d=vt=L 1, driving the wing 6 to rotate by the connecting disc 3, enabling the tangent f-f 1＝k1(e-e1 of J 1 at the intersection point (d 1,e1,f1) of J 1 and I 11 to be vertical, regulating the Z axis to enable the ultrasonic laser probe path to be vertical to the I 11 at the intersection point, scanning the scanning along the curve I 11 from the right to the left, and re-timing the scanning time, thus finishing a round of scanning, enabling the excitation point of the ith scanning to be (d i,ei,fi), and repeating the steps until all the scanning steps L 1i curve is completed. The laser ultrasound probe 8 operates in the scanning process as shown in fig. 4. When the laser ultrasonic probe 8 works, 1 excitation point and 2 detection points exist on the surface of the wing 6 at the same time, the coordinates of the excitation point are (d i,ei,fi), a spanwise signal is measured by the first detection point, a wingspan direction signal is measured by the second detection point, a local coordinate system Lm-Ln-Lz is established according to a scanning curve, the Lz direction is the normal direction of the surface of the wing 6 at the excitation point (d i,ei,fi), the normal direction points to the inside of the wing 6, the Lm direction points to the scanning direction of the current wingspan curve I 1i, and Ln points to the wingspan direction at the point. By scanning all L 1i curves, the scan dataset p (I 1i, lm, t) on the spanwise I 1i curve and the upper scan dataset p (J j, ln, t) of the L 1 segment spanwise curve J j can be obtained simultaneously;
L 2 section scanning, namely turning the wing 6 back to the initial position when the L 1 section scanning is finished, calculating a tangent line of J 0 at the intersection point of J 0 and L 20, keeping the tangent line vertical, scanning the tangent line in the spanwise direction along the curve L 20 by adjusting the light path of the laser ultrasonic probe 8 to be perpendicular to L 20 at the intersection point, repeating the L 1 section scanning until all the L 2i scanning is finished, and obtaining scanning data sets p (I 2i, lm, t) on the spanwise I 2i curve and upper scanning data sets p (J j, ln, t) on the L 2 section wingspan direction curve J j.
According to a further optimization scheme, subsurface crack defects are plane defects, the subsurface crack defects are detected by utilizing a peri-wing data set p (J j, ln, t) when the subsurface crack defects are located in a wing span section LnOLz corresponding to a peri-wing curve J s, and the subsurface crack defects are detected by the following steps:
Determining the vertex coordinates Ln 0 of subsurface defects, namely, in the scanning process, only scanning data p (J s, ln, t) on a wing circumferential direction curve J s, generating a defect echo signal RL, and observing the defect echo signal RL of a scanning dataset to determine the wing circumferential section where the subsurface defects are located;
Observing scanning data p (J s, ln, t), and obtaining subsurface defect vertex coordinates Ln 0 when the arrival time t RL of the reflected wave RL obtains the minimum value and the defect vertex is positioned at the midpoint of an excitation point and a detection point II in the Ln direction;
Determination of subsurface defect vertex coordinates Lz 0, wherein the defect vertex coordinates are (Ln 0,Lz0), the coordinates of excitation points are (Ln 1, 0), the coordinates of detection points two are (Ln 1 +l, 0), l is the distance between the excitation points and the detection points two, and c is the wave velocity, then the subsurface crack burial depth Lz 0 can be calculated by the following formula:
Sub-surface defect detection of spanwise cross-sections is performed by scanning data sets p (I 1i, lm, t) and p (I 2i, lm, t).
In one embodiment of the invention, S2 subsurface defect detection, wherein subsurface defects are planar defects, and the scanning process can realize subsurface defect detection on the airfoil circumferential section LnOLz and the span section LmOLz. Assuming that a subsurface defect is located in the spanwise section LnOLz corresponding to the airfoil circumferential curve J s, the subsurface defect detection is performed as follows:
In the scanning process of the section L 1 and the section L 2, only a defect echo signal RL appears when scanning data p (J s, ln, t) of a curve J s in the circumferential direction of the wing, and the section of the wing where the subsurface defect is located can be determined by observing a scanning data set p (J j, ln, t);
Observing scanning data p (J s, ln, t), and obtaining subsurface defect vertex coordinates Ln 0 when the arrival time t RL of the reflected wave RL obtains the minimum value and the defect vertex is positioned at the midpoint of an excitation point and a detection point II in the Ln direction;
Determination of subsurface Defect vertex coordinate Lz 0 As shown in FIG. 5, where defect vertex coordinate is (Ln 0,Lz0), excitation point coordinate is (Ln 1, 0), detection point two is (Ln 1 +l, 0), l is distance between excitation point and detection point two, and c is wave velocity, subsurface crack burial depth Lz 0 can be calculated by:
The sub-surface defect vertex position (J s,Ln0,Lz0) of the peripheral section of the J s wing is obtained through the steps, and the defect vertex position (x 0,y0,z0) under a rectangular coordinate system can be obtained through further coordinate transformation. Similarly, spanwise subsurface defect detection can be performed by scanning the data sets p (I 1i, lm, t) and p (I 2i, lm, t).
In a further optimized scheme, the surface crack defect is a plane defect, and when one surface defect is positioned in the spanwise section LmOLz corresponding to the spanwise curve I 1s, the specific steps of surface defect detection are as follows:
Sequentially drawing all scanned spanwise cross-section B pictures according to a scanned data set p (I 1i, lm, t);
In the scanning process, the excitation point and the detection point are fixed, when no defect exists between the excitation point and the detection point, the propagation time of the surface acoustic wave from the excitation point to the detection point is the same, and B scanning imaging is carried out to form a continuous straight line;
When a defect exists between the excitation point and the detection point, most waves are reflected when the surface waves are transmitted to the side edge of the defect from the excitation point, the detected signal intensity at the detection point is very low, and the scanning imaging is carried out to form a straight line with a gap, so that the wingspan section I 1s where the position of the surface defect is located is determined;
The notch position in the B scanning chart is the position of the surface defect, and spanwise coordinates Lms1 and Lms2 can be obtained according to the B scanning chart;
surface defect detection of the airfoil circumferential section was performed by p (J s, ln, t).
In one embodiment of the present invention, S3 surface defect detection is performed, wherein the surface defect is a planar defect. The location of the defect may be determined by presenting the scan dataset in the form of a B-scan. Assuming that a surface defect is located in the spanwise section LmOLz corresponding to the spanwise curve I 1s, the specific steps for surface defect inspection are as follows:
Sequentially drawing all scanned spanwise cross-section B pictures according to a scanned data set p (I 1i, lm, t);
In the scanning process, the excitation point and the detection point are fixed, when no defect exists between the excitation point and the detection point, the propagation time of the surface acoustic wave from the excitation point to the detection point is the same, and B scanning imaging is carried out to form a continuous straight line;
as shown in fig. 6, when a defect exists between the excitation point and the detection point, most of waves are reflected when the surface wave passes from the excitation point to the side edge of the defect, the detected signal intensity at the detection point is very low, and the detected signal intensity is scanned and imaged into a straight line with a gap, so that the spanwise cross section I 1s where the position of the surface defect is located is determined;
and the notch position in the B scanning chart is the position of the surface defect. As shown in fig. 7, spanwise coordinates Lms1 and Lms2 are obtained from the B-scan. In the same way, the surface defect detection of the airfoil circumferential section can be performed by p (J s, ln, t).
According to a further optimization scheme, three-dimensional imaging can be realized in two ways according to the scanned data sets p (I 1i,Lm,t),p(I2i, lm, t) and p (J j, ln, t), and the positions and the shapes of internal defects are presented;
Extracting a two-dimensional dataset p 1i (Lm, t) corresponding to a span curve I 1i for focusing imaging of a two-dimensional span section corresponding to a span curve I 1i, wherein the specific steps include calculating an equivalent speed in a frequency-wave number domain by a numerical calculation method, calculating a phase shift factor according to the equivalent speed, and calculating a two-dimensional spectrum extrapolation and an imaging matrix, wherein the equivalent speed can be calculated by the following formula:
Changing imaging depth Lz, repeating the steps until the amplitude value calculation of all imaging points is completed, and obtaining an imaging matrix I (Lm, lz) of a two-dimensional span section corresponding to a span curve I 1i;
Collecting all spanwise imaging matrixes to obtain a three-dimensional imaging matrix I (I 1i, lm, lz) of the L 1 -section wing 6;
And carrying out coordinate conversion to obtain a three-dimensional imaging matrix I (x, y, z) under a rectangular coordinate system, and imaging.
Further optimizing scheme, the specific steps of three-dimensional imaging of the wing 6 based on the wing circumferential direction scanning data set p (J j, ln, t) are as follows:
Dividing the peripheral section of the wing into a plurality of contour sections, expanding the outer contour into a straight line, expanding the peripheral section of the wing in the imaging section into a plane, and performing frequency domain imaging in the imaging section to obtain a plane frequency domain imaging matrix in the contour section;
splicing the curved surface imaging in all the contour sections into a frequency domain imaging matrix I (Ln, lz) of a two-dimensional section of the wing circumference corresponding to a wing circumference curve J j;
Sequentially performing two-dimensional spanwise cross-section imaging corresponding to the peri-wing curve, and collecting all peri-wing cross-section imaging matrixes to obtain a three-dimensional imaging matrix I (J j, ln, lz) of the wing 6
In one embodiment of the invention, three-dimensional imaging of defects inside the S4 wing can be realized by scanning the data sets p (I 1i,Lm,t),p(I2i, lm, t) and p (J j, ln, t), so that the defects can be more intuitively presented. An example of three-dimensional imaging of an L 1 -section airfoil 6 of the present invention based on a spanwise scan dataset p (I 1i, lm, t) is shown below:
In step s4.1.1, a two-dimensional dataset p 1i (Lm, t) corresponding to the spanwise curve I 1i is extracted for focused imaging of a two-dimensional spanwise section corresponding to the spanwise curve I 1i. The specific implementation steps of the two-dimensional focusing imaging algorithm are as follows:
At step S4.1.2, an equivalent speed c eq is calculated. The calculation principle of the equivalent speed c eq is shown in fig. 8. The coordinates of the target point G are (Lm 0, lz 0), the coordinates of the excitation point are (LmE, 0), the coordinates of the corresponding detection point I are (LmR, 0), the distance exists between the two points, the equivalent detection point M (LmR-l/2, 0) is positioned at the midpoint of the two points, gamma T is the excitation angle, gamma R is the detection angle, gamma M is the equivalent detection angle, and c is the actual wave velocity. The calculation process of the equivalent speed c eq is as follows:
calculating excitation angles gamma T of different target points when detecting the position change, detecting angles gamma R and equivalent detection angles gamma M, and obtaining a functional relation f (gamma T,γR,γM) of gamma T、γR and gamma M;
the wave number domain excitation angle gamma 'T and the wave number domain detection angle gamma' R are calculated in the wave number domain, and the calculation process can be represented by the following formula:
kLm＝k(sinγ′T+sinγ′R)
Wherein k Lm is the Lm-direction wave number, k is the wave number, k=ω/c, ω is the frequency, determined by the spanwise sweep step;
The calculated wave number domain excitation angle gamma ' T and wave number domain detection angle gamma ' R calculate a wave number domain equivalent detection angle gamma ' M according to a functional relation f (gamma T,γR,γM);
calculating an equivalent wave speed c eq from the wave number domain excitation angle gamma ' T, the wave number domain detection angle gamma ' R, the wave number domain equivalent detection angle gamma ' M and the actual wave speed c, wherein the calculation process is shown in the following formula:
Performing two-dimensional Fourier transform on a two-dimensional dataset P 1i (Lm, t) corresponding to the spanwise curve I 1i to obtain a two-dimensional frequency spectrum P (k Lm, 0, omega) with the detection depth lz=0;
The two-dimensional spectrum of depth lz=0 is extrapolated to the plane of depth Lz, resulting in the two-dimensional spectrum P (k Lm, 0, ω) of depth Lz, calculated as follows:
P(kLm,Lz,ω)＝P(kLm,0,ω)α(kLm,Lz,ω)
Where α (k Lm, lz, ω) is a phase shift factor, which can be calculated by the following formula, where jj represents an imaginary unit:
Performing two-dimensional Fourier transform on Lm and Lz by using a two-dimensional frequency spectrum P (k Lm, lz, omega) of a depth Lz plane to obtain an imaging matrix of the depth Lz, wherein t=0 in the inverse transform process, and the amplitude I (Lm, lz) of an imaging point (Lm, lz) can be calculated by the following formula:
Changing imaging depth Lz, repeating the steps until the amplitude value calculation of all imaging points is completed, obtaining an imaging matrix I (Lm, lz) of a wingspan curve I 1i corresponding to a two-dimensional wingspan section, and drawing a two-dimensional wingspan section focusing imaging as shown in figure 9;
And step S4.1.3, repeating the steps S4.1.1-S4.1.2, and sequentially performing two-dimensional spanwise cross-section imaging corresponding to the spanwise curve. Collecting all spanwise imaging matrixes to obtain a three-dimensional imaging matrix I (I 1i, lm, lz) of the L 1 -section wing 6;
In step S4.1.4, coordinate transformation is performed to obtain a three-dimensional imaging matrix I (x, y, z) under a rectangular coordinate system, and a three-dimensional focusing image of the L 1 -section wing 6 is drawn as shown in fig. 10.
An example of three-dimensional imaging of the wing 6 based on the wing circumferential scan data set p (J j, ln, t) of the present invention is shown below:
S4.2.1, the shape of the wing circumferential section of the wing 6 is irregular, the section is divided into a plurality of contour sections, the outer contour of the wing 6 is unfolded into a straight line, the normal direction is set as the depth direction, the wing circumferential section of the wing 6 in the imaging section is unfolded into a plane, and frequency domain imaging is carried out in the imaging section according to the method in step S4.1.2, so that plane frequency domain imaging in the contour section is obtained;
Step S4.2.2, repeating step S4.2.1 until the curved surface images of all the contour segments are obtained, and splicing the curved surface images in all the contour segments into a frequency domain imaging matrix I (Ln, lz) of a two-dimensional section of the wing circumference corresponding to the wing circumference curve J j, as shown in FIG. 11;
step S4.2.3, repeating the steps S4.2.1-S4.2.2, and sequentially performing two-dimensional spanwise cross-section imaging corresponding to the airfoil circumference curve. Collecting all the imaging matrixes of the wing circumferential sections to obtain a three-dimensional imaging matrix I (J j, ln, lz) of the wing 6 of the L 1 section;
and S4.2.4, carrying out coordinate conversion to obtain a three-dimensional imaging matrix I (x, y, z) under a rectangular coordinate system, and drawing a three-dimensional focusing image of the wing 6.
Embodiment two:
referring to fig. 12-13, the difference between the present embodiment and the first embodiment is that a rotary clamping mechanism is further provided, the rotary clamping mechanism includes a turntable 14, a movable clamping rail 15 is provided on the turntable 14, the turntable 14 is mounted on the movable rail 16 through a supporting frame, and a driving motor 17 is provided on the supporting frame to drive the turntable 14 to rotate.
In one embodiment of the invention, in use, the left end of the wing 6 is mounted on the connecting disc 3, the wing 6 is rotated to the initial position where the maximum section is parallel to the ground, the bottom moving slide rail 16 is moved, the rotary clamping mechanism is aligned with the right end of the wing 6 in the length direction, the turntable 14 is rotated, the clamping slide rail 15 is slid and moved, the right end of the wing 6 is clamped on the moving clamping slide rail 15, and due to the influence of gravity, the right end has a certain deflection deformation in the mounting of the wing 6, the turntable 14 is adjusted again, and the wing 6 is rotated to the initial position where the maximum section is parallel to the ground.
The wing 6 can be clamped in an auxiliary mode through the arranged rotary clamping mechanism, the defect of curvature is reduced, and therefore detection is more accurate.
In the third embodiment, the difference between the present embodiment and the second embodiment is that the moving clamping slide rail 15 and the corresponding turntable 14 are provided with long holes for extending the right end of the wing 6, and the turntable 14 and the laser ultrasonic probe 8 synchronously move along the axial direction, so that the bending deformation of the detection point under gravity is further reduced, and the detection accuracy is further improved.
In the description of the present invention, it should be understood that the terms "longitudinal," "transverse," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present invention, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present invention.
The foregoing embodiments are merely illustrative of the preferred embodiments of the present invention, and the scope of the present invention is not limited thereto, but various modifications and improvements made by those skilled in the art to which the present invention pertains are made without departing from the spirit of the present invention, and all changes and modifications and improvements fall within the scope of the present invention as defined in the appended claims.

Claims (10)

1.一种机翼缺陷检测装置，其特征在于，包括：1. A wing defect detection device, comprising: 升降台(1)和导轨平台(2)，所述升降台(1)和所述导轨平台(2)分别固定在地面上且平行设置；A lifting platform (1) and a guide rail platform (2), wherein the lifting platform (1) and the guide rail platform (2) are respectively fixed on the ground and arranged in parallel; 旋转组件，包括连接圆盘(3)和主轴(4)，所述连接圆盘(3)通过所述主轴(4)转动连接在所述升降台(1)顶端，所述连接圆盘(3)远离所述升降台(1)的一侧固定连接有两转盘接头(5)，机翼(6)与所述转盘接头(5)连接；A rotating assembly comprises a connecting disc (3) and a main shaft (4), wherein the connecting disc (3) is rotatably connected to the top of the lifting platform (1) via the main shaft (4), two rotating disc joints (5) are fixedly connected to a side of the connecting disc (3) away from the lifting platform (1), and the wing (6) is connected to the rotating disc joints (5); 检测组件，包括三轴移动台(7)和激光超声探头(8)，所述三轴移动台(7)设置在所述导轨平台(2)上，所述激光超声探头(8)固定连接在所述三轴移动台(7)上用于对所述机翼(6)进行检测；A detection component, comprising a three-axis moving platform (7) and a laser ultrasonic probe (8), wherein the three-axis moving platform (7) is arranged on the guide rail platform (2), and the laser ultrasonic probe (8) is fixedly connected to the three-axis moving platform (7) for detecting the wing (6); 所述激光超声探头(8)为单激发点双检测点的激光超声探头。The laser ultrasonic probe (8) is a laser ultrasonic probe with a single excitation point and two detection points. 2.根据权利要求1所述的一种机翼缺陷检测装置，其特征在于：两所述转盘接头(5)分别位于所述连接圆盘(3)两侧，且位于同一直径线上。2. A wing defect detection device according to claim 1, characterized in that the two turntable joints (5) are respectively located on both sides of the connecting disc (3) and are located on the same diameter line. 3.根据权利要求1所述的一种机翼缺陷检测装置，其特征在于：所述升降台(1)上固定连接有传动箱(9)，所述传动箱(9)内固定连接有伺服电机(10)，所述伺服电机(10)的输出轴通过减速器(11)、联轴器(12)和绝对式光电编码器(13)与所述主轴(4)连接，所述主轴(4)与所述升降台(1)之间设置有间隙。3. A wing defect detection device according to claim 1, characterized in that: a transmission box (9) is fixedly connected to the lifting platform (1), a servo motor (10) is fixedly connected inside the transmission box (9), the output shaft of the servo motor (10) is connected to the main shaft (4) through a reducer (11), a coupling (12) and an absolute photoelectric encoder (13), and a gap is set between the main shaft (4) and the lifting platform (1). 4.一种机翼缺陷检测方法，适用于权利要求1-4任一所述的一种机翼缺陷检测装置，其特征在于，包括以下步骤：4. A wing defect detection method, applicable to a wing defect detection device according to any one of claims 1 to 4, characterized in that it comprises the following steps: S1、将所述机翼(6)安装在所述连接圆盘(3)上进行激光超声扫查；S1, mounting the wing (6) on the connecting disc (3) and performing laser ultrasonic scanning; S2、对所述机翼(6)进行亚表面裂纹缺陷检测；S2, performing sub-surface crack defect detection on the wing (6); S3、对所述机翼(6)进行表面裂纹缺陷检测；S3, performing surface crack defect detection on the wing (6); S4、对所述机翼(6)进行三维成像，得到所述机翼(6)内部缺陷的三维图像。S4. Perform three-dimensional imaging on the wing (6) to obtain a three-dimensional image of internal defects of the wing (6). 5.根据权利要求4所述的一种机翼缺陷检测方法，其特征在于：5. A wing defect detection method according to claim 4, characterized in that: S1中在初始位置时保持所述机翼(6)与水平面平行，所述升降台(1)的高度为HJ，所述主轴(4)与所述升降台(1)顶面之间的间距为hz，所述机翼(6)的最大翼宽为Wmax，满足：HJ+hz≥1.5Wmax；In S1, at the initial position, the wing (6) is kept parallel to the horizontal plane, the height of the lifting platform (1) is H J , the distance between the main axis (4) and the top surface of the lifting platform (1) is h z , the maximum wing width of the wing (6) is W max , and the following conditions are satisfied: H J +h z ≥1.5W max ; 所述导轨平台(2)的高度为H，所述三轴移动台(7)的Z轴的初始高度为Zpt0，满足：HJ+hz＝H+Zpt0。The height of the guide rail platform (2) is H, and the initial height of the Z axis of the three-axis moving platform (7) is Z pt0 , satisfying: H J +h z =H+Z pt0 . 6.根据权利要求5所述的一种机翼缺陷检测方法，其特征在于：6. A wing defect detection method according to claim 5, characterized in that: 激光超声扫描时首先确立全局直角坐标系X-Y-Z,X方向指向初始位置所述机翼(6)的翼展方向，Y方向指向垂直于X方向的翼宽方向，XOY平面与水平面平行，与XOY平面垂直的方向为Z方向，然后将所述机翼(6)的表面离散成点，在通过将若干离散点连成线，沿离散化曲线进行激光超声扫描，依据扫查曲线建立局部坐标系Lm-Ln-Lz，得到翼展方向数据集p(I1i,Lm,t)，p(I1i,Lm,t)及翼周方向数据集p(Jj,Ln,t)用于对缺陷进行成像。During laser ultrasonic scanning, a global rectangular coordinate system XYZ is first established, wherein the X direction points to the span direction of the wing (6) at the initial position, the Y direction points to the wing width direction perpendicular to the X direction, the XOY plane is parallel to the horizontal plane, and the direction perpendicular to the XOY plane is the Z direction. Then, the surface of the wing (6) is discretized into points, and laser ultrasonic scanning is performed along the discretized curve by connecting a number of discrete points into a line. A local coordinate system Lm-Ln-Lz is established based on the scanning curve, and a span direction data set p(I 1i ,Lm,t) and p(I 1i ,Lm,t) and a circumferential direction data set p(J j ,Ln,t) are obtained for imaging defects. 7.根据权利要求6所述的一种机翼缺陷检测方法，其特征在于：7. A wing defect detection method according to claim 6, characterized in that: 亚表面裂纹缺陷为平面缺陷，亚表面裂纹缺陷在有一亚表面缺陷位于翼周曲线Js所对应翼展截面LnOLz内，利用翼周数据集p(Jj,Ln,t)实现亚表面缺陷的检测，亚表面裂纹缺陷的检测过程具体步骤如下：The subsurface crack defect is a plane defect. There is a subsurface crack defect located in the wing span section LnOLz corresponding to the wing circumference curve Js . The wing circumference data set p( Jj , Ln, t) is used to detect the subsurface defect. The specific steps of the subsurface crack defect detection process are as follows: 亚表面缺陷顶点坐标Ln0的确定：在扫描过程中，只有在翼周方向曲线Js上扫查数据p(Js,Ln,t)时会出现缺陷回波信号RL，观察扫查数据集缺陷回波信号RL确定亚表面缺陷所在翼周截面；Determination of the sub-surface defect vertex coordinates Ln 0 : During the scanning process, the defect echo signal RL will appear only when the data p(J s ,Ln,t) is scanned on the wing circumferential direction curve J s. The defect echo signal RL of the scanned data set is observed to determine the wing circumferential section where the sub-surface defect is located; 亚表面缺陷顶点坐标Ln0的确定：观察扫查数据p(Js,Ln,t)，当反射波RL的到达时间tRL取得最小值时，在Ln方向上缺陷顶点位于激发点和检测点二的中点，从而得到亚表面缺陷顶点坐标Ln0；Determination of the sub-surface defect vertex coordinate Ln 0 : Observe the scanning data p(J s ,Ln,t). When the arrival time t RL of the reflected wave RL reaches the minimum value, the defect vertex in the Ln direction is located at the midpoint between the excitation point and the second detection point, thereby obtaining the sub-surface defect vertex coordinate Ln 0 ; 亚表面缺陷顶点坐标Lz0的确定：缺陷顶点坐标为(Ln0,Lz0)，激发点的坐标为(Ln1,0)，检测点二的坐标为(Ln1+l,0)，l为激发点与检测点二之间的距离，c为波速，则亚表面裂纹埋藏深度Lz0可由下式计算：Determination of the coordinates of the sub-surface defect vertex Lz 0 : The coordinates of the defect vertex are (Ln 0 ,Lz 0 ), the coordinates of the excitation point are (Ln 1 ,0), the coordinates of the second detection point are (Ln 1 +l,0), l is the distance between the excitation point and the second detection point, c is the wave velocity, and the sub-surface crack burial depth Lz 0 can be calculated by the following formula: 通过扫查数据集p(I1i,Lm,t)和p(I2i,Lm,t)进行翼展截面的亚表面缺陷检测。Sub-surface defect detection of the span section is performed by scanning the data sets p(I 1i ,Lm,t) and p(I 2i ,Lm,t). 8.根据权利要求7所述的一种机翼缺陷检测方法，其特征在于：8. A wing defect detection method according to claim 7, characterized in that: 表面裂纹缺陷为平面缺陷，在有一表面缺陷位于翼展曲线I1s所对应翼展截面LmOLz内，表面缺陷检测的具体步骤如下：The surface crack defect is a plane defect. When a surface defect is located in the span section LmOLz corresponding to the span curve I 1s , the specific steps of surface defect detection are as follows: 根据扫查数据集p(I1i,Lm,t)将所有的翼展截面B扫描图依次画出；All the span-section B-scans are drawn sequentially according to the scan data set p(I 1i ,Lm,t); 在扫描过程中激发点和检测点是固定的，当激发点和检测点之间没有缺陷时，声表面波从激发点到检测点之间的传播时间相同，B扫描成像为一条连续的直线；During the scanning process, the excitation point and the detection point are fixed. When there is no defect between the excitation point and the detection point, the propagation time of the surface acoustic wave from the excitation point to the detection point is the same, and the B-scan image is a continuous straight line. 当激发点和检测点之间存在缺陷时，表面波由激发点处传至缺陷侧边时大部分波会发生反射，检测点处检测到的信号强度很低，扫描成像为一条存在缺口的直线，由此确定表面缺陷的位置所在的翼展截面I1s；When there is a defect between the excitation point and the detection point, most of the surface waves will be reflected when they are transmitted from the excitation point to the side of the defect. The signal intensity detected at the detection point is very low, and the scanning image is a straight line with a gap, thereby determining the span section I 1s where the surface defect is located; B扫描图中缺口位置即为表面缺陷的位置，根据B扫描图可得到翼展方向坐标Lms1和Lms2；The position of the notch in the B-scan is the position of the surface defect, and the spanwise coordinates Lms1 and Lms2 can be obtained based on the B-scan. 通过p(Js,Ln,t)进行翼周截面的表面缺陷检测。The surface defect detection of the wing circumferential section is carried out by p(J s ,Ln,t). 9.根据权利要求8所述的一种机翼缺陷检测方法，其特征在于：根据扫查数据集p(I1i,Lm,t)，p(I2i,Lm,t)和p(Jj,Ln,t)可通过两种方式实现三维成像，呈现内部缺陷的位置和形状；9. A wing defect detection method according to claim 8, characterized in that: according to the scanned data sets p(I 1i , Lm, t), p(I 2i , Lm, t) and p(J j , Ln, t), three-dimensional imaging can be achieved in two ways to present the position and shape of the internal defects; 抽取翼展曲线I1i所对应的二维数据集p1i(Lm,t)，用于翼展曲线I1i对应二维翼展截面的聚焦成像，其具体步骤包括通过数值计算的方法，在频率-波数域内计算等效速度，根据等效速度计算相移因子，二维频谱外推及成像矩阵计算，所述等效速度可由下式计算：A two-dimensional data set p 1i (Lm, t) corresponding to the wingspan curve I 1i is extracted for focused imaging of the two-dimensional wingspan section corresponding to the wingspan curve I 1i . The specific steps include calculating the equivalent velocity in the frequency-wave number domain by numerical calculation, calculating the phase shift factor according to the equivalent velocity, two-dimensional spectrum extrapolation and imaging matrix calculation. The equivalent velocity can be calculated by the following formula: 改变成像深度Lz,重复上述步骤直至完成所有成像点的幅值计算，得到翼展曲线I1i对应二维翼展截面的成像矩阵I(Lm,Lz)；Change the imaging depth Lz, repeat the above steps until the amplitude calculation of all imaging points is completed, and obtain the imaging matrix I (Lm, Lz) of the two-dimensional wingspan section corresponding to the wingspan curve I 1i ; 集合所有翼展截面成像矩阵，获得L1段所述机翼(6)的三维成像矩阵I(I1i,Lm,Lz)；Collect all wingspan cross-sectional imaging matrices to obtain a three-dimensional imaging matrix I (I 1i , Lm, Lz) of the wing (6) of section L 1 ; 进行坐标转换，获得直角坐标系下的三维成像矩阵I(x,y,z)，成像。Perform coordinate transformation to obtain the three-dimensional imaging matrix I (x, y, z) in the rectangular coordinate system and perform imaging. 10.根据权利要求9所述的一种机翼缺陷检测方法，其特征在于：10. A wing defect detection method according to claim 9, characterized in that: 基于翼周方向扫描数据集p(Jj,Ln,t)的所述机翼(6)三维成像的具体步骤如下：The specific steps of three-dimensional imaging of the wing (6) based on the wing circumferential direction scanning data set p(J j ,Ln,t) are as follows: 将翼周截面分为数个轮廓段，外轮廓展开为直线，成像段内的翼周截面被展开为平面，对成像段内进行频域成像，获得该轮廓段内的平面频域成像矩阵；The wing circumference section is divided into several contour segments, the outer contour is unfolded into a straight line, the wing circumference section in the imaging segment is unfolded into a plane, and the imaging segment is imaged in the frequency domain to obtain the plane frequency domain imaging matrix in the contour segment; 将所有轮廓段内的曲面成像拼接为翼周曲线Jj对应翼周二维截面频域成像矩阵I(Ln,Lz)；The surface imaging in all contour segments is spliced into the frequency domain imaging matrix I(Ln,Lz) of the 2-dimensional section of the wing circumference curve J j corresponding to the wing circumference; 依次进行翼周曲线对应二维翼展截面成像，集合所有翼周截面成像矩阵，获得所述机翼(6)的三维成像矩阵I(Jj,Ln,Lz)。The two-dimensional wingspan section imaging corresponding to the wing circumference curve is performed in sequence, and all wing circumference section imaging matrices are combined to obtain the three-dimensional imaging matrix I (J j , Ln, Lz) of the wing (6).
CN202411382546.8A 2024-09-30 2024-09-30 Wing defect detection device and method Pending CN119269630A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202411382546.8A CN119269630A (en) 2024-09-30 2024-09-30 Wing defect detection device and method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202411382546.8A CN119269630A (en) 2024-09-30 2024-09-30 Wing defect detection device and method

Publications (1)

Publication Number Publication Date
CN119269630A true CN119269630A (en) 2025-01-07

Family

ID=94119733

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202411382546.8A Pending CN119269630A (en) 2024-09-30 2024-09-30 Wing defect detection device and method

Country Status (1)

Country Link
CN (1) CN119269630A (en)

Similar Documents

Publication Publication Date Title
CN111796028B (en) Ultrasonic water immersion automatic detection device and method for complex ring forgings
US7508971B2 (en) Inspection system using coordinate measurement machine and associated method
EP2400297B1 (en) Inspection system and associated method
US7253908B2 (en) Non-destructive inspection using laser profiling and associated method
JP6445274B2 (en) Equipment for non-destructive inspection of stringers
EP3531123B1 (en) Laser ultrasound scanning for visualizing damage or irregularities
CN108801914A (en) A kind of detection method and detecting system to how groove-shaped panel material forming defects
US20090277269A1 (en) Pulse echo/through transmission ultrasonic testing
CN108226290A (en) A kind of inside parts defect three-dimensional parameter extracting method based on ultrasonic phase array
CN108844978B (en) Novel method for detecting internal defects of honeycomb
CN107255673A (en) High temperature blade internal flaw three dimensional lossless detection method based on ultrasonic phase array
Hopkins et al. Advanced phased-array technologies for ultrasonic inspection of complex composite parts
CN114279361A (en) A three-dimensional measuring system and measuring method for defect size of inner wall of cylindrical parts
Wallentine et al. A study on ground truth data for impact damaged polymer matrix composites
CN105571549A (en) Nondestructive test method of heat wave imaging of cylindrical surface coating
CN114755300B (en) A defect location and quantitative detection method based on ultrasonic nondestructive testing
CN111948211A (en) A composite pressure equipment flaw detection system
CN113899818B (en) Ultrasonic detection method for R-region defects of T-shaped component for airframe structure
CN117092121B (en) Titanium alloy gas cylinder forming quality detection equipment and method
CN119269630A (en) Wing defect detection device and method
CN116256092A (en) A workpiece stress distribution inversion system, method and storage medium based on longitudinal and shear wave fusion
Ullmann et al. In-line quality assurance for the manufacturing of carbon fiber reinforced aircraft structures
Zhu et al. Ultrasonic testing system design for defect visualization of inhomogeneous multi-layered pipes
CN221506800U (en) Composite material delamination defect detection device based on ultrasonic guided wave
CN118275542B (en) Diffraction time difference ultrasonic scanning method and scanning frame for large-thickness butt weld

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination