CN113879558A

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Info

Publication number: CN113879558A
Application number: CN202111037527.8A
Authority: CN
Inventors: 阚艳; 张小辉; 范鑫; 朱萌; 程宗辉; 赵勃; 邓森
Original assignee: Harbin Institute of Technology Shenzhen; State Run Wuhu Machinery Factory
Current assignee: Harbin Institute of Technology Shenzhen; State Run Wuhu Machinery Factory
Priority date: 2021-09-06
Filing date: 2021-09-06
Publication date: 2022-01-04

Abstract

The invention discloses an ultrasonic shape reconstruction method for a T-shaped R region of a wing, which comprises the following steps: the method comprises the steps of placing a linear array ultrasonic phased array probe on a structural member to be detected, taking one side of the probe as a zero sampling position, sequentially selecting five sampling positions from left to right, placing the probe on six sampling positions in sequence, respectively exciting an ultrasonic probe transducer to emit ultrasonic waves, receiving ultrasonic echo data on each sampling position, performing time domain analysis to obtain a time domain signal on each sampling position, solving ultrasonic sampling time of each sampling position according to the time domain signal on each sampling position, and further constructing a surface function of the structure to be detected. According to the method, the shape reconstruction of the T-shaped R region in the wing can be completed on the premise of not damaging a piece to be detected, and the ultrasonic echo data is processed, so that the structural information such as the position, the radius and the like of the T-shaped R region in the wing can be effectively obtained, and a series of high-precision detection tasks such as detection of internal defects of the R region and a stress field are facilitated.

Description

Ultrasonic shape reconstruction method for T-shaped R region of wing

Technical Field

The invention relates to the technical field of ultrasonic detection, in particular to a method for reconstructing ultrasonic shape of T-shaped R region of wing.

Background

After the airplane trains and performs tasks, the airplane is inevitably damaged due to factors such as severe weather influence and high-intensity use. The wing is used as the most main stressed structure, damage such as fracture, deformation and the like can occur after long-time use, and the internal defects of the wing can be found in time and maintained, so that the wing has important significance for prolonging the service life of the airplane and protecting the flight safety of a driver.

The bearing structure in the wing comprises an L-shaped component, a T-shaped component and the like, the ribbed wall plates are all provided with R-area structures, and the R-areas in the wing structural components are easy to generate fatigue due to long-time action of force in the flying process of an airplane, so that internal defects such as cracks, gaps and the like exist. Effective detection of defects such as fine cracks, pores and the like requires that an ultrasonic detection instrument has high detection precision, and can find fine internal defects in time.

The general information of the internal structure of the wing needs to be known in the ultrasonic nondestructive detection of the R region, so that detection personnel can conveniently and reasonably install the high-precision ultrasonic probe, determine the incident angle, the ultrasonic type, the frequency and the like, further improve the detection efficiency and timely find and position defects.

Specifically, a three-dimensional reconstruction method for inclusions in a metal material based on an ultrasonic detection technology is provided in a related technology, and the method includes the steps of firstly, carrying out two-step detection of rough scanning and fine scanning on the material by using an ultrasonic microscope to obtain ultrasonic echo signals of the inclusions; secondly, preprocessing the ultrasonic echo signal, and setting a judgment threshold value of the inclusion echo signal; then extracting the space coordinates of the positions of the inclusions; then fitting discrete sampling points of the positions of the inclusions into a curved surface by using a curved surface interpolation fitting method; and finally obtaining the three-dimensional shape of the inclusion. The method can detect impurities of other materials in the metal material so as to reconstruct the appearance of the impurities, but the method has the defect that the internal appearance of a single material cannot be reconstructed.

The ultrasonic phased array detection device for the R area of the composite material, which is provided by the third related technology, comprises a water bag coupling module and a supporting module; the water bag coupling module comprises a water bag and a probe, liquid is filled in a water bag cavity of the water bag, and one side of the probe, facing the workpiece, is wrapped by a water bag sleeve of the water bag; the water bag coupling module can realize good coupling of the probe and R regions of workpieces with different curvatures through the water bag; the supporting module is used for realizing stable support of the probe. The detection device does not need water immersion type coupling, is not limited by the external field test condition, can be suitable for ultrasonic detection of R areas with different curvatures, and avoids the condition that the structural part cannot be subjected to ultrasonic detection due to deviation in manufacturing and processing. The device needs the water pocket coupling module to solve the problem that detection device needs water coupling, detects to the R district of different curvatures and has better precision, but the device's water pocket coupling module need laminate R district, R district under the inconvenient detection wing.

In summary, most of the R-region detection at present is performed with higher accuracy on the premise that the shape of the R-region is known, but the actual R-region detection, such as T-shaped R-region detection in the airfoil, is performed on the premise that the shape and position of the R-region are unknown, so a detection method capable of reconstructing the shape of the R-region in the airfoil is urgently needed.

Disclosure of Invention

The present invention is directed to solving, at least to some extent, one of the technical problems in the related art.

Therefore, the invention aims to provide an ultrasonic shape reconstruction method facing a T-shaped R region of a wing, which can complete shape reconstruction of the T-shaped R region in the wing on the premise of not damaging a piece to be detected.

In order to achieve the purpose, the embodiment of the invention provides an ultrasonic shape reconstruction method facing a T-shaped R region of an airfoil, which comprises the following steps: step S1, placing a linear array ultrasonic phased array probe on a structural part to be tested, and taking one side of the linear array ultrasonic phased array probe as a zero sampling position; step S2, selecting five sampling positions on the structural part to be tested to mark by taking the zero sampling position as a start; step S3, sequentially placing the linear array ultrasonic phased array probe at six sampling positions, respectively exciting a transducer of the linear array ultrasonic phased array probe to emit ultrasonic waves, and receiving ultrasonic echo data at each sampling position; step S4, performing time domain analysis on the ultrasonic echo data at each sampling position to obtain a time domain signal at each sampling position, and solving the ultrasonic sampling time of each sampling position according to the time domain signal at each sampling position; and step S5, constructing a surface function of the structure to be measured according to the ultrasonic sampling time and the six sampling positions of each sampling position.

According to the ultrasonic shape reconstruction method for the T-shaped R region of the wing, disclosed by the embodiment of the invention, the transducer is excited to emit ultrasonic waves in a specific mode through positioning and sampling to obtain echo data, then time domain analysis is carried out on the ultrasonic echo data, and an echo time domain signal of a specific array element is obtained and processed, so that structural information such as the position, the radius and the like of the T-shaped R region in the wing is effectively obtained, a high-precision ultrasonic probe can be conveniently and reasonably installed by a detector, the ultrasonic nondestructive detection of the R region is completed, and a series of high-precision detection tasks such as detection of internal defects of the R region, stress field and the like are facilitated.

In addition, the ultrasonic shape reconstruction method facing the T-shaped R region of the wing according to the above embodiment of the present invention may further have the following additional technical features:

further, in an embodiment of the present invention, the step S2 specifically includes: marking the zero sampling position as a No. 1 sampling position, taking the No. 1 sampling position as a starting point, selecting five sampling positions of the structural part to be detected, and respectively marking the sampling positions as a No. 2 sampling position, a No. 3 sampling position, a No. 4 sampling position, a No. 5 sampling position and a No. 6 sampling position, wherein the intervals of the six sampling positions are equal.

Further, in an embodiment of the present invention, the step S4 specifically includes: step S401, performing inverse transformation on the ultrasonic echo data at each sampling position in step S3 to obtain a time domain signal at each sampling position; in the step 402, 64 time domain signals at each sampling position are analyzed, and the ultrasonic sampling time at each sampling position is obtained.

Further, in an embodiment of the present invention, the ultrasound echo data at each sampling position is:

H_jl(ω)＝S(ω)D(ω,θ_j)D(ω,θ_l)R(ω,θ_l,θ_j)G(r_s,r_j)G(r_l,r_s)

wherein H_jl(omega) is ultrasonic echo data at each sampling position, and S (omega) is a transmitting array element r of the linear array ultrasonic phased array probe_jFrequency spectrum, D (omega, theta) of ultrasonic longitudinal wave signal s (t)_j) And D (ω, θ)_l) For transmitting array element r_jAnd a receiving array element r_lFar field directivity function in solid media, R (omega, theta)_l,θ_j) As scattering coefficient, G (r)_s,r_j) And G (r)_l,r_s) Is the green function of the medium.

Further, in an embodiment of the present invention, the surface function of the structure to be measured is:

g(x,y,z)＝f(x,y,z)+c_Lt_i

wherein g (x, y, z) is of the structure to be measuredSurface function, f (x, y, z) is the surface function of the structure, c_LAt longitudinal wave velocity, t_iThe ultrasound sampling time for each sampling position.

Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.

Drawings

The foregoing and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:

FIG. 1 is a flowchart of an ultrasonic topography reconstruction method for a T-shaped R region of an airfoil according to an embodiment of the invention;

FIG. 2 is a schematic diagram illustrating the detection of the R region of the structure under test according to one embodiment of the present invention;

FIG. 3 is a schematic diagram of ultrasonic wave transmission and reception of a linear array ultrasonic phased array probe according to an embodiment of the present invention;

FIG. 4 is a graph of ultrasonic propagation distance versus sampling position for one embodiment of the present invention.

Description of reference numerals:

1-linear array ultrasonic phased array probe, 2-structural component to be tested and 3-R area of structural component to be tested.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.

The ultrasonic shape reconstruction method facing the T-shaped R region of the wing provided by the embodiment of the invention is described below with reference to the attached drawings.

FIG. 1 is a flowchart of an ultrasonic topography reconstruction method for a T-shaped R region of an airfoil according to an embodiment of the invention.

As shown in fig. 1, the ultrasonic topography reconstruction method facing the T-shaped R region of the wing includes the following steps:

in step S1, the linear array ultrasonic phased array probe is placed on the structural member to be measured, and one side of the linear array ultrasonic phased array probe is used as a zero sampling position.

In step S2, five sampling positions are selected from the zero sampling position as the start of marking on the structural member to be tested.

Further, in an embodiment of the present invention, the step S2 specifically includes:

marking the zero sampling position as a No. 1 sampling position, taking the No. 1 sampling position as a starting point, selecting five sampling positions of the structural part to be detected, and respectively marking the sampling positions as a No. 2 sampling position, a No. 3 sampling position, a No. 4 sampling position, a No. 5 sampling position and a No. 6 sampling position, wherein the intervals of the six sampling positions are equal.

Specifically, as shown in fig. 2, in the embodiment of the present invention, a 64-array linear array ultrasonic phased array probe is adopted, thearray elements 1 are numbered sequentially from left to right, the probe is placed on the structural member to be measured 2, the reference number is No. 1 with one side of the probe as a zero start point, and sampling positions with appropriate interval lengths are taken on the structural member to be measured and are numbered as No. 2, No. 3, and the like.

In step S3, the linear array ultrasonic phased array probe is sequentially placed at six sampling positions, the transducers of the linear array ultrasonic phased array probe are respectively excited to emit ultrasonic waves, and ultrasonic echo data at each sampling position is received.

That is to say, control the excitation time and the delay time of every array element after numbering in proper order to the array element of linear array ultrasonic phased array probe from left to right, at first arouse and receive No. 1 array element, arouse and receive No. 2 array elements again after gathering and storing echo data to accomplish the ultrasonic echo data acquisition of whole 64 array elements.

Wherein, step S3 may specifically include:

step S301, placing the linear array ultrasonic phased array probe on the No. 1 sampling position of the structure to be tested, exciting a transducer of the linear array ultrasonic phased array probe to transmit ultrasonic waves, and receiving ultrasonic echo data on the No. 1 sampling position;

step S302, placing the linear array ultrasonic phased array probe at the No. 2 sampling position of the structure to be tested, exciting a transducer of the linear array ultrasonic phased array probe to emit ultrasonic waves, and receiving ultrasonic echo data at the No. 2 sampling position;

step S303, placing the linear array ultrasonic phased array probe at the No. 3 sampling position of the structure to be tested, exciting a transducer of the linear array ultrasonic phased array probe to transmit ultrasonic waves, and receiving ultrasonic echo data at the No. 3 sampling position;

step S304, placing the linear array ultrasonic phased array probe at the No. 4 sampling position of the structure to be tested, exciting a transducer of the linear array ultrasonic phased array probe to transmit ultrasonic waves, and receiving ultrasonic echo data at the No. 4 sampling position;

step S305, placing the linear array ultrasonic phased array probe at the No. 5 sampling position of the structure to be tested, exciting a transducer of the linear array ultrasonic phased array probe to emit ultrasonic waves, and receiving ultrasonic echo data at the No. 5 sampling position;

and S306, placing the linear array ultrasonic phased array probe at the No. 6 sampling position of the structure to be detected, exciting a transducer of the linear array ultrasonic phased array probe to emit ultrasonic waves, and receiving ultrasonic echo data at the No. 6 sampling position.

In step S4, performing time domain analysis on the ultrasound echo data at each sampling position to obtain a time domain signal at each sampling position, and solving the ultrasound sampling time at each sampling position according to the time domain signal at each sampling position.

Namely, after the region to be measured is marked, the ultrasonic probe transducer is excited to emit ultrasonic waves to collect internal information of the structural member, the structural member is scanned integrally, and propagation time of the ultrasonic waves is obtained according to the obtained time domain signals of ultrasonic echo waves. In fig. 2, the propagation time of the ultrasonic wave is clearly different between the non-R region part and theR region part 2a of the T-shaped structural member, and the approximate position of the R region to be detected is determined by scanning the whole.

Further, the step S4 may specifically include:

step S401, performing inverse transformation on the ultrasonic echo data at each sampling position in step S3 to obtain a time domain signal at each sampling position;

in the step 402, 64 time domain signals at each sampling position are analyzed, and the ultrasonic sampling time at each sampling position is obtained.

As shown in fig. 3, by a transmitting array element r_jThe sent ultrasonic longitudinal wave signal is received by array element r₁The frequency spectrum of the received signal can be expressed as follows, namely the ultrasonic echo data at each sampling position is:

H_jl(ω)＝S(ω)D(ω,θ_j)D(ω,θ_l)R(ω,θ_l,θ_j)G(r_s,r_j)G(r_l,r_s)

in the formula, H_jl(omega) is ultrasonic echo data at each sampling position, and S (omega) is a transmitting array element r of the linear array ultrasonic phased array probe_jFrequency spectrum, D (omega, theta) of ultrasonic longitudinal wave signal s (t)_j) And D (ω, θ)_l) For transmitting array element r_jAnd a receiving array element r_lFar field directivity function in solid media, R (omega, theta)_l,θ_j) As scattering coefficient, G (r)_s,r_j) And G (r)_l,r_s) Is the green function of the medium.

Wherein, when the ultrasonic longitudinal wave propagates in the isotropic solid medium, the far field directional function is as follows:

D(ω,θ)＝D_f(ω,θ)D_L(θ)

wherein D is_L(θ) can be expressed as:

green function G (r)₁,r₂) Describes the sound wave at any two points r in the medium₁And r₂The propagation characteristics between can be approximately expressed as:

to H_jl(omega) inverse transformation can obtain a time domain signal h received by a receiving array element in the array_jl(t) a scattering coefficient R (ω, θ) for a structure with known physical properties according to the array element excitation and reception method of step S3, i.e., j (l) 1,2, … …_l,θ_j) Longitudinal and transverse acoustic velocity c_L,c_SAs known, for the selected ultrasonic probe, the distance between the adjacent array elements is known, and the propagation time t of the ultrasonic echo can be obtained by analyzing 64 time domain signals respectively_i。

In step S5, a surface function of the structure to be measured is constructed from the ultrasonic sampling time and the six sampling positions for each sampling position.

g(x,y,z)＝f(x,y,z)+c_Lt_i

wherein g (x, y, z) is the surface function of the structure to be measured, f (x, y, z) is the surface function of the structural member, c_LAt longitudinal wave velocity, t_iThe ultrasound sampling time for each sampling position.

For example, as shown in fig. 4, the two-dimensional shape of the R region can be obtained by drawing a relation curve of the sampling position and the distance according to the surface function of the structure to be measured. If the

sampling positions

1 and 2 show that the R area is not detected by the probe, the sampling positions 3 and 5 can obtain the position depth of the R area.

According to the ultrasonic shape reconstruction method facing the T-shaped R region of the wing, provided by the embodiment of the invention, the position of the probe is marked, some proper sampling positions of the part to be detected are selected, ultrasonic detection is carried out, for the structural member made of a known material, the physical properties of the material, such as attenuation coefficient, longitudinal wave and transverse wave speed, are known, the proper ultrasonic probe is selected, each array element in the probe is excited to fit in a one-transmitting-one-receiving mode to obtain a time domain signal, the time domain signal of ultrasonic waves is analyzed to obtain the information of the position, the structural shape and the like in the R region, the shape information of the R region and other positions of the structural member can be obtained, and the method is simple to operate and suitable for in-service detection.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.

Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.

Claims

1. An ultrasonic shape reconstruction method facing a T-shaped R region of an airfoil is characterized by comprising the following steps:

step S1, placing a linear array ultrasonic phased array probe on a structural part to be tested, and taking one side of the linear array ultrasonic phased array probe as a zero sampling position;

step S2, selecting five sampling positions on the structural part to be tested to mark by taking the zero sampling position as a start;

step S3, sequentially placing the linear array ultrasonic phased array probe at six sampling positions, respectively exciting a transducer of the linear array ultrasonic phased array probe to emit ultrasonic waves, and receiving ultrasonic echo data at each sampling position;

step S4, performing time domain analysis on the ultrasonic echo data at each sampling position to obtain a time domain signal at each sampling position, and solving the ultrasonic sampling time of each sampling position according to the time domain signal at each sampling position;

and step S5, constructing a surface function of the structure to be measured according to the ultrasonic sampling time and the six sampling positions of each sampling position.

2. The ultrasonic topography reconstruction method facing the T-shaped R region of the wing as claimed in claim 1, wherein the step S2 is specifically as follows:

3. The ultrasonic topography reconstruction method facing an airfoil T-shaped R region as claimed in claim 1, wherein said step S3 specifically comprises:

4. The ultrasonic topography reconstruction method facing an airfoil T-shaped R region as claimed in claim 1, wherein said step S4 specifically comprises:

5. The ultrasonic topography reconstruction method facing the T-shaped R region of the wing according to claim 4, wherein the ultrasonic echo data at each sampling position are:

H_jl(ω)＝S(ω)D(ω,θ_j)D(ω,θ_l)R(ω,θ_l,θ_j)G(r_s,r_j)G(r_l,r_s)

6. The ultrasonic topography reconstruction method for the wing T-shaped R region according to claim 1, wherein the surface function of the structure to be measured is:

g(x,y,z)＝f(x,y,z)+c_Lt_i