CN113899479A - Ultrasonic detection method for stress of T-shaped R region of fuselage structure - Google Patents

Ultrasonic detection method for stress of T-shaped R region of fuselage structure Download PDF

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CN113899479A
CN113899479A CN202111040627.6A CN202111040627A CN113899479A CN 113899479 A CN113899479 A CN 113899479A CN 202111040627 A CN202111040627 A CN 202111040627A CN 113899479 A CN113899479 A CN 113899479A
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CN113899479B (en
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阚艳
范鑫
宣善勇
朱萌
程宗辉
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State Run Wuhu Machinery Factory
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L1/00—Measuring force or stress, in general
    • G01L1/25—Measuring force or stress, in general using wave or particle radiation, e.g. X-rays, microwaves, neutrons
    • G01L1/255—Measuring force or stress, in general using wave or particle radiation, e.g. X-rays, microwaves, neutrons using acoustic waves, or acoustic emission
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
    • G01L5/0047—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes measuring forces due to residual stresses

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Abstract

The invention provides a T-shaped R region stress ultrasonic detection method facing a machine body structure, wherein an array element inclined probe is placed on the back plane of a T-shaped component to be detected, and the internal R region is subjected to stress detection; because the stress of the R region component is mainly concentrated near the surface of the R region, the average stress value detected by the stress is equivalent to the stress value near the surface of the R region, qualitative representation of the plane stress of the R region component is realized, and for one point P on the surface of the R region, two fixed refraction directions theta are selected1、θ2The single-array element oblique probe ultrasonic transducer respectively carries out longitudinal wave stress detection to obtain corresponding propagation time t1、t2The stress values sigma in two directions can be respectively obtained by the longitudinal wave stress detection principle1*、σ2*And combining the Morel circle stress theory to obtain two main stress magnitudes of X, Y directions of the surface measurement point P of the R area of the T-shaped detection piece.

Description

Ultrasonic detection method for stress of T-shaped R region of fuselage structure
Technical Field
The invention belongs to the technical field of ultrasonic detection, and particularly relates to a T-shaped R region stress ultrasonic detection method for a machine body structure.
Background
Compared with the world advanced countries, the current aviation maintenance detection technology in China has certain defects, even though the technology is developed rapidly in recent years, the nondestructive detection technology of airplanes in China is continuously strengthened in the aspects of tip, precision, high grade and the like, and particularly, the related technology in the aspect of self-detection inside airplanes is ensured to be really applied to airplane maintenance.
In various machines and machines, residual stress is generated in the components, and the generated residual stress state is greatly different according to various processing methods or treatment methods. Residual stress and residual stress maldistribution will have a significant impact on fatigue strength, static strength, structural deformation, and service life of the component. For example, the residual stress of the weld seam, which affects the life cycle of the welded structure, causes severe stress concentration at the weld seam, which leads to microcracks in the weld seam, and the cracks may cause cracking of the welded part under certain conditions.
In order to be suitable for different application occasions, most of the members in aerospace have complex shape structure areas, such as L-shaped members, T-shaped members, omega-shaped members and the like which are collectively called as R areas. The transition region of the fuselage structure R is a stress concentration region, and defects such as cracks and gaps are easy to generate during production, manufacturing and use, and phenomena such as fracture occur. In order to guarantee the service life of the airplane and the safety and reliability requirements of users, the residual stress generated in the structural design, manufacturing process and service process must be fully paid attention to, the R region of the airplane body structure is subjected to stress field detection, safety performance evaluation, measures and countermeasures by adopting an accurate and reliable nondestructive detection technology, and the method has very important significance for ensuring the production, stabilizing the quality, prolonging the service life and the like.
Compared with other nondestructive testing methods for residual stress, the ultrasonic nondestructive testing method has the advantages of high testing speed, no radiation damage to human bodies, low cost, better spatial resolution, larger testing depth range, capability of realizing field holding and carrying, capability of completing the testing of the macroscopic participation of surface and subsurface stress in the stress magnitude and the tension and compression state and the like, and has been widely paid attention by domestic and foreign scholars. Great university of the connective industry proposes a surface residual stress ultrasonic detection method of direct coupling wave (a surface residual stress ultrasonic detection method of direct coupling wave. publication No. CN 106679872B). The method adopts a wave-making mode of coupling agent direct coupling, ultrasonic waves directly enter a material to be detected through a single coupling agent medium, and a direct coupling wave-making type ultrasonic probe is in a stress measurement mode of 'one-shot and two-shot'. Firstly, designing and assembling a direct coupling wave type ultrasonic probe, placing the assembled direct coupling wave type ultrasonic probe on the surface of a measured material, and keeping a measurement base surface to be fully contacted with the surface. The couplant is stably injected into the couplant cavity through the valve port to form an ultrasonic direct propagation passage for ultrasonic detection of surface residual stress. The method completes wave generation and coupling simultaneously, has few ultrasonic wave propagation interfaces, ensures the quality of received signals and improves the signal-to-noise ratio. The stress measurement mode is adopted, the calculation accuracy of the acoustic time difference is ensured, and the measurement spatial resolution is improved. The method has problems that: the method has certain requirements on detecting the surface flatness and cannot be suitable for detecting the stress of the T-shaped R region of the airframe structure.
The south-Guangxi aluminum processing Co., Ltd provides a nondestructive testing method and equipment for residual stress of aluminum alloy (a nondestructive testing method and equipment for residual stress of aluminum alloy. publication No. CN 111623913A). Respectively preparing near-zero residual stress samples parallel to and perpendicular to the main deformation direction of the aluminum alloy, carrying out different annealing treatments on the samples, establishing a goods returning state-electric conductivity database of the samples, establishing a first stress-sound time difference database and a second stress-sound time difference database, then, conducting conductivity detection on the aluminum alloy to be subjected to residual stress nondestructive testing actually, obtaining a corresponding annealing state in an annealing state-conductivity database, inputting the annealing state into a first stress-sound time difference database and a second stress-sound time difference database to obtain a corresponding stress-sound time difference curve, collecting sound time difference data of the detected position of the aluminum alloy in a direction parallel to and perpendicular to the main deformation direction of the aluminum alloy, and finally substituting the collected sound time difference data into the stress-sound time difference curve to obtain corresponding residual stress. The invention can realize high-precision repeatable nondestructive detection. The method has problems that: when the method and the equipment are used for detecting the residual stress of the to-be-detected piece, the to-be-detected piece needs to be independently operated, and the method and the equipment cannot be suitable for the in-service detection of the stress of the T-shaped R area of the machine body structure.
Beijing university of science and engineering proposes a non-linear ultrasonic detection method of residual stress (a non-linear ultrasonic detection method of residual stress publication No. CN 108225632A). By utilizing the corresponding relation between the ultrasonic second-order and third-order nonlinear coefficients and the residual stress, the internal residual stress of the component can be detected in a non-contact manner through water coupling or air coupling, and researches and experimental verification prove that the method has correct theoretical basis, feasible technical scheme, effective implementation method and reliable and repeatable detection result, and fundamentally solves the fundamental requirement of rapid nondestructive detection of the internal residual stress of the large component. The method has problems that: when the method is used for detecting the residual stress of the to-be-detected piece, the to-be-detected piece needs to be independently operated, and the method cannot be applied to the in-service detection of the stress of the T-shaped R area of the machine body structure.
At present, ultrasonic stress detection on a to-be-detected piece in the market is usually oriented to common structures such as flat plates, bolts and welding lines, and the to-be-detected piece needs to be independently operated. However, in the actual detection requirement of aerospace, the fuselage component with the R region also needs to be subjected to stress nondestructive detection by a corresponding detection method. In summary, the existing market lacks a T-shaped R-region stress ultrasonic detection method which can be oriented to a fuselage structure and is used for in-service detection and qualitative and quantitative characterization of the stress.
Disclosure of Invention
Aiming at the defects of the prior art of ultrasonic detection of the stress of the T-shaped R region of the fuselage structure, the invention provides an ultrasonic detection method of the stress of the T-shaped R region facing the fuselage structure, wherein an oblique probe of a unit is placed on the back plane of a T-shaped member to be detected, and the stress of the internal R region is detected. Because the stress of the R-area component is mainly concentrated near the surface of the R-area, the average stress value detected by the stress is equivalent to the stress value near the surface of the R-area, and the qualitative representation of the plane stress of the R-area component is realized. Based on the assumption, two fixed refraction directions are selected for one point P on the surface of the R regionθ1、θ2The single-array element oblique probe ultrasonic transducer respectively carries out longitudinal wave stress detection to obtain corresponding propagation time t1、t2. Stress values sigma in two directions can be respectively obtained through the longitudinal wave stress detection principle1*、σ2*And combining the Morel circle stress theory to obtain two main stress magnitudes of X, Y directions of the surface measurement point P of the R area of the T-shaped detection piece.
A T-shaped R-zone stress ultrasonic detection method for a fuselage structure comprises the following steps:
the method specifically comprises the following steps:
the method comprises the following steps: placing the array element inclined probe 1 on the back plane of a T-shaped piece to be detected 2, and carrying out stress detection on an internal R area;
step two: determining the radius of a stress circle and the position of a center point of the stress circle by combining the Morse circle stress theory;
step three: stress ultrasonic detection; and (3) equating the average stress value of the stress detection to the stress value near the surface of the R area to obtain two main stress magnitudes in the X, Y direction of the R area surface measuring point P of the T-shaped detection piece 2.
Further, in the second step, the first step,
selecting two mutually perpendicular planes by means of the stress (σ) on these two planesx,τxy)、(σy,τyx) Determining a connecting line as a diameter of the stress circle; then, one half of the distance between the two stress points is the radius of the stress circle, the central position of the two stress points is the center of the stress circle, and the formula of the stress circle is as follows:
Figure BDA0003249044260000031
in the formula, σα、ταNormal stress and shear stress on any plane; sigmax、σy、τxyNormal stress and shear stress at any angle;
by principal stress (σ)1，0)、(σ20) is used as the starting point, and the inversion is carried out by 2 times of the included angle theta between the wave velocity propagation direction and the maximum main stressRotating in the clockwise direction; the two principal stresses in this direction at the two points of intersection with the moire stress circle are then:
Figure BDA0003249044260000032
further, in the third step,
for one point P on the surface of the R region, two fixed refraction directions theta are selected1、θ2The single-array element oblique probe ultrasonic transducer respectively carries out longitudinal wave stress detection to obtain corresponding propagation time;
according to the corresponding propagation time, respectively obtaining two directional stress values sigma through a longitudinal wave stress detection principle1*And σ2*And two principal stress magnitudes in the X, Y direction of the R region surface measuring point P of the T-shaped detecting element 2 can be obtained by combining the Morel circle stress theory;
the stress values in both directions are related to the two principal stress values as follows,
σ1*＝σ1cos2θ1+σ2sin2θ1
σ2*＝σ1cos2θ2+σ2sin2θ2 (3)
solving the formula (3), obtaining two main stress values in the X, Y direction of the measuring point P point of the T-shaped detecting piece 2:
Figure BDA0003249044260000041
the invention has the beneficial effects
(1) The invention is oriented to the T-shaped R area of the fuselage structure, and stress ultrasonic detection is carried out on the surface measuring points of the R area based on the longitudinal wave stress detection principle and the Morel circle stress theory, and qualitative and quantitative characterization is carried out;
(2) in order to verify the performance of the method proposed by the invention, a hyperspectral video dataset is verified. The data is from the office of the 'Hyperspectral Object Tracking Challenge' competition, and comprises 40 groups of training set videos and 35 groups of test set videos, each group of videos comprises a 16-wave-band (470-620nm) Hyperspectral video and an RGB (red, green and blue) video shot at the same angle, distance and resolution, each video is about 500 frames, the number of the video frames is 25FPS, an Object to be tracked is given in an initial frame in the form of the vertex, the length and the width of the enclosed minimum rectangular frame, and the Object covers various types of vehicles, human bodies, books, coins and the like and is a common near-distance image or a non-remote sensing image. The experimental result shows that the hyperspectral video target tracking method based on the depth tensor can realize real-time and accurate tracking of the target in the hyperspectral video.
Drawings
FIG. 1 is a schematic structural diagram of an ultrasonic testing device of the present invention; wherein 1 is a single-array element inclined probe, and 2 is a T-shaped detection part;
FIG. 2 is a schematic representation of the Morel circle stress theory;
FIG. 3 is a diagram illustrating stress detection in the T-shaped R region.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments; all other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In conjunction with the figures 1 to 3,
a T-shaped R-zone stress ultrasonic detection method for a fuselage structure comprises the following steps:
the method specifically comprises the following steps:
the method comprises the following steps: placing the array element inclined probe 1 on the back plane of a T-shaped piece to be detected 2, and carrying out stress detection on an internal R area; because the stress of the R area component is mainly concentrated near the surface of the R area, the average stress value detected by the stress is equivalent to the stress value near the surface of the R area;
step two: determining the radius of a stress circle and the position of a center point of the stress circle by combining the Morse circle stress theory;
step three: stress ultrasonic detection; and (3) equating the average stress value of the stress detection to the stress value near the surface of the R area to obtain two main stress magnitudes in the X, Y direction of the R area surface measuring point P of the T-shaped detection piece 2.
In step two, two mutually perpendicular planes are selected, the stress (σ) on these two planes being passed throughx,τxy)、(σy,τyx) Determining a connecting line as a diameter of the stress circle; then, one half of the distance between the two stress points is the radius of the stress circle, the central position of the two stress points is the center of the stress circle, and the formula of the stress circle is as follows:
Figure BDA0003249044260000051
in the formula, σα、ταNormal stress and shear stress on any plane; sigmax、σy、τxyNormal stress and shear stress at any angle;
by principal stress (σ)1，0)、(σ20) starting from the starting point, rotating counterclockwise by 2 times of the included angle theta between the wave velocity propagation direction and the maximum main stress; the two principal stresses in this direction at the two points of intersection with the moire stress circle are then:
Figure BDA0003249044260000052
in step three, for a point P on the surface of the R area, two fixed refraction directions theta are selected1、θ2The single-array element oblique probe ultrasonic transducer respectively carries out longitudinal wave stress detection to obtain corresponding propagation time;
according to the corresponding propagation time, respectively obtaining two directional stress values sigma through a longitudinal wave stress detection principle1*And σ2*And two principal stress magnitudes in the X, Y direction of the R region surface measuring point P of the T-shaped detecting element 2 can be obtained by combining the Morel circle stress theory;
the stress values in both directions are related to the two principal stress values as follows,
σ1*＝σ1cos2θ1+σ2sin2θ1
σ2*＝σ1cos2θ2+σ2sin2θ2 (3)
solving the formula (3) to obtain two main stress values in the X, Y direction of the measuring point P of the T-shaped detecting piece (2):
Figure BDA0003249044260000061
the ultrasonic detection method for the stress of the T-shaped R region facing the fuselage structure, which is provided by the invention, is introduced in detail, the principle and the implementation mode of the invention are explained, and the description of the embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.

Claims (3)

1. A T-shaped R region stress ultrasonic detection method for a fuselage structure is characterized by comprising the following steps:
the method specifically comprises the following steps:
the method comprises the following steps: placing the array element inclined probe (1) on the back plane of the T-shaped piece to be detected (2), and carrying out stress detection on an internal R area;
step two: determining the radius of a stress circle and the position of a center point of the stress circle by combining the Morse circle stress theory;
step three: stress ultrasonic detection; and (3) equating the average stress value of the stress detection to the stress value near the surface of the R area to obtain two main stress magnitudes in the X, Y direction of the R area surface measuring point P of the T-shaped detection piece (2).
2. The method of claim 1, further comprising: in the second step, the first step is carried out,
selecting two mutually perpendicular planes by means of the stress (σ) on these two planesx,τxy)、(σy,τyx) Determining a connecting line as a diameter of the stress circle; then, one half of the distance between the two stress points is the radius of the stress circle, the central position of the two stress points is the center of the stress circle, and the formula of the stress circle is as follows:
Figure FDA0003249044250000011
in the formula, σα、ταNormal stress and shear stress on any plane; sigmax、σy、τxyNormal stress and shear stress at any angle;
by principal stress (σ)1，0)、(σ20) starting from the starting point, rotating counterclockwise by 2 times of the included angle theta between the wave velocity propagation direction and the maximum main stress; the two principal stresses in this direction at the two points of intersection with the moire stress circle are then:
Figure FDA0003249044250000012
3. the method of claim 1, further comprising: in the third step, the first step is carried out,
for one point P on the surface of the R region, two fixed refraction directions theta are selected1、θ2The single-array element oblique probe ultrasonic transducer respectively carries out longitudinal wave stress detection to obtain corresponding propagation time;
according to the corresponding propagation time, respectively obtaining two directional stress values sigma through a longitudinal wave stress detection principle1*And σ2*And two main stress magnitudes in the X, Y direction of the R area surface measuring point P of the T-shaped detecting piece (2) can be obtained by combining the Morel circle stress theory;
the stress values in both directions are related to the two principal stress values as follows,
σ1*＝σ1cos2θ1+σ2sin2θ1
σ2*＝σ1cos2θ2+σ2sin2θ2 (3)
solving the formula (3) to obtain two main stress values in the X, Y direction of the measuring point P of the T-shaped detecting piece (2):
Figure FDA0003249044250000021
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