Anchoring body nondestructive testing system under action of combined stress

Abstract

The utility model discloses an anchoring body nondestructive testing system under combined stress action, which comprises a machine body frame and a test piece, an axial loading module is arranged on one side in the machine body frame, a clamping device is arranged on the other side in the machine body frame, and a shearing module is arranged above the clamping device; one end of the test piece penetrates through the axial loading module, the other end of the test piece is fixed through the clamping device, and the shearing module is located above the test piece and makes contact with the test piece. The axial loading module is arranged in the machine body frame, the test piece is arranged in the axial loading module, the shearing module is further arranged in the axial loading module, the shearing module is additionally arranged on the basis of axial loading, shearing stress can be applied to the test piece while the shearing module can be matched with axial loading, the stress condition of an anchor rod / an anchor body in a field supporting state is better simulated, and the testing accuracy of the anchor rod / anchor body is improved. And the accuracy and the reliability of the nondestructive testing research result of the anchor rod are improved.

Description

Technical Field

[0001] The utility model relates to the technical field of coal mine shaft and tunnel engineering, in particular to a nondestructive testing system for anchoring bodies under the action of composite stress. Background Art

[0002] Stability control of tunnel surrounding rock is an important prerequisite for safe and efficient production in coal mines. At present, bolt support is the most widely used tunnel support method. The stress and deformation state of the bolt under support is the key factor affecting the stability of the surrounding rock and the quality of tunnel support. The working principle of the bolt determines that it will undergo structural changes with the deformation of the surrounding rock. When the deformation of the bolt or the damage of the anchor body reaches the limit, it may cause anchor failure and large-scale instability of the surrounding rock. Therefore, the detection of the bolt support state is of great significance for tunnel maintenance and coal mine safety. Since underground tunnel bolt support is a concealed project, the bolt length, anchor quality and bolt axial force detection mostly use bolt non-destructive testing technology, but at this stage, there is little research on non-destructive testing of bolt deformation / anchor body damage under composite stress, and there is a lack of corresponding basic research test systems and methods.

[0003] The shortcomings of existing technologies:

[0004] 1. Existing research on non-destructive testing technology for anchor rods mainly focuses on the detection of anchor rod length, anchoring quality and anchor rod axial force. Anchor rod length and anchoring quality are mainly for the detection of anchor rod support construction quality, which is a problem of anchor rod support quality caused by human factors. They can be used to evaluate the quality of anchor rod construction, but cannot judge the quality of anchor rod support in the support state; anchor rod axial force detection is to judge whether the anchor rod support state is good or not based on the axial stress condition in the anchor rod support state. The stress environment in which the anchor rod is supported is complex. Although the anchor rod is mainly subjected to tensile stress, it is subjected to shear stress when the rock formation moves. The anchoring force of the anchor rod under the action of composite stress is different from the anchoring force of the anchor rod under the action of axial load. Therefore, there are great limitations in judging the quality of anchor rod support by anchor rod axial force.

[0005] 2. Existing research on non-destructive testing of anchor rods lacks non-destructive testing systems and methods for the deformation / damage of anchor rods under combined stress. Utility Model Content

[0006] The technical problem to be solved by the utility model is: how to provide a non-destructive testing system for anchor rods / anchor bodies under the action of composite stress.

[0007] In order to solve the above technical problems, the utility model provides the following technical solutions:

[0008] A nondestructive testing system for anchoring bodies under composite stress, comprising a fuselage frame and a test piece, wherein an axial loading module is installed on one side of the fuselage frame, a clamping device is provided on the other side of the fuselage frame, and a shearing module is installed above the clamping device;

[0009] One end of the specimen passes through the axial loading module, the other end of the specimen is fixed by a clamping device, and the shearing module is located above the specimen and in contact with the specimen.

[0010] The present application sets up an axial loading module inside the fuselage frame, and the specimen is placed inside the axial loading module, which also includes a shear module. The present application adds a shear module on the basis of axial loading, which can apply shear stress to the specimen simultaneously with the axial loading, so as to better simulate the stress condition of the anchor rod / anchor body under the on-site support state, and improve the accuracy and reliability of the research results of the anchor rod non-destructive testing.

[0011] As a further solution of the utility model: a column sensor is provided on the outer side wall of the fuselage frame, wherein the column sensor is connected to the axial loading module and receives the axial load signal of the test piece.

[0012] As a further solution of the utility model: one side of the test piece is connected to a displacement observation rod, and the other side of the displacement observation rod is connected to a displacement sensor arranged on the fuselage frame.

[0013] As a further solution of the utility model: an acceleration sensor is provided on the outside of the fuselage frame and on one side of the column sensor, and a roller exciter is also provided on one side of the acceleration sensor. The roller exciter is placed on the outside of the specimen and emits excitation at the end of the specimen; the acceleration sensor is adsorbed on the end of the specimen and receives the vibration signal of the specimen.

[0014] As a further solution of the utility model: a bracket is provided on one side of the fuselage frame, wherein the top of the bracket is connected to a high-speed camera, and the high-speed camera is located above the fuselage frame, with its angle direction facing the test piece of the fuselage frame.

[0015] As a further solution of the utility model: the shearing module includes a support frame installed at the rear end of the fuselage frame, wherein a shearing cylinder is installed on the support frame, and the output end of the shearing cylinder is in contact with the test piece.

[0016] As a further solution of the utility model: a second displacement sensor is provided on the inner wall of the fuselage frame, the second displacement sensor is connected to the shear cylinder, and the second displacement sensor receives the shear displacement signal of the test piece.

[0017] As a further solution of the utility model: the clamping device includes a clamping member and a cylinder, wherein the clamping member is provided with two groups, which are respectively located on both sides of the test piece, and the other sides of the two groups of clamping members are connected to the inner wall of the fuselage frame through the cylinder.

[0018] As a further solution of the utility model: the surface of the clamping member in contact with the test piece is configured to be in a rectangular tooth shape.

[0019] As a further solution of the utility model: it also includes a control end and a microcomputer controller, the control end is connected to the microcomputer controller, and the microcomputer controller is connected to the axial loading module and the shearing module.

[0020] Compared with the prior art, the beneficial effects of the utility model are:

[0021] Firstly, compared with the commonly existing nondestructive testing instruments for anchor rod length and anchoring quality, the present application can realize the nondestructive testing experiment for anchor rod length and anchoring quality without loading, and can completely simulate the nondestructive testing of anchor rod construction quality for different anchor rod lengths and anchoring qualities;

[0022] Secondly, compared with the anchor rod nondestructive testing experimental system composed of the axial loading device of the general universal tensile machine structure, the present application transforms the axial loading module into a hydraulic device structure, which improves the stability of the axial loading and the safety of the test; adds a shear module, which can cooperate with the axial loading module to apply shear stress to the specimen at the same time, better simulates the stress condition of the anchor rod / anchor body under the on-site support state, and improves the accuracy and reliability of the anchor rod nondestructive testing research results;

[0023] Finally, this application is different from the general non-destructive testing methods and test systems for anchor length, anchoring quality and axial force. It is a non-destructive testing test system and method for anchor deformation / anchor body damage under single / compound stress, which supplements the development of existing anchor non-destructive testing technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a schematic structural diagram of a nondestructive testing system for anchoring bodies under composite stress according to an embodiment of the utility model;

[0025] Figure 2 This is a schematic diagram of the structure of the shearing module of an embodiment of the utility model;

[0026] Figure 3 It is a partial structural schematic diagram of the fuselage frame of an embodiment of the utility model;

[0027] Explanation of the reference numerals: 1. Control terminal; 2. Microcomputer controller; 3. Acceleration sensor; 4. Roller vibrator; 5. Displacement sensor 1; 6. Column sensor; 7. Axial loading module; 8. High-speed camera; 9. Shearing module; 91. Support frame; 92. Shearing cylinder; 93. Bobbin; 10. Displacement sensor 2; 11. Clamp; 12. Fuselage frame; 13. Test piece; 14. Cylinder; 15. Bracket. DETAILED DESCRIPTION

[0028] In order to make the purpose, technical solution and advantages of the embodiments of the utility model clearer, the technical solution in the embodiments of the utility model will be clearly and completely described below in combination with the embodiments of the utility model. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0029] Reference Figure 1 A nondestructive testing system for anchoring bodies under composite stress comprises a control terminal 1, a microcomputer controller 2, an acceleration sensor 3, a roller vibrator 4, a displacement sensor 5, a column sensor 6, an axial loading module 7, a high-speed camera 8, a shear module 9, a displacement sensor 10, a clamp 11, a fuselage frame 12, a test piece 13, a cylinder 14 and a bracket 15, wherein the control terminal 1 and the microcomputer controller 2 are located on one side of the fuselage frame 12, a bracket 15 is arranged on the other side of the fuselage frame 12, a rotatable high-speed camera 8 is installed above the bracket 15, and the high-speed camera 8 can be used to take pictures or videos at any time to record image data.

[0030] Reference Figure 1 The control terminal 1 is connected to the microcomputer controller as the upper computer. The experimental plan is written in the computer using special software, and the instructions are output to the microcomputer controller 2 according to the experimental plan, such as loading instructions, stress wave excitation instructions, etc.

[0031] Reference Figure 1 , one end of the microcomputer controller 2 is connected to the control end 1, and the other end is connected to the acceleration sensor 3, the roller vibrator 4, the displacement sensor 1 5, the column sensor 6, the axial loading module 7, the shear module 9, the displacement sensor 2 10 and the cylinder 14. Receiving the instructions from the computer, it can control the roller vibrator 4 to emit excitation, control the axial loading module 7 to apply axial load or displacement to the specimen, control the shear module 9 to move and apply shear force or displacement to the specimen, and control the clamping member 11 to move and clamp the bottom end of the specimen 13; receive the stress wave data input by the acceleration sensor 3, the displacement data input by the displacement sensor 1 5, and the load data input by the column sensor 6, and output them to the computer.

[0032] Reference Figure 1 and Figure 3 The acceleration sensor 3 is arranged on the outside of the fuselage frame 12 and on one side of the column sensor 6. A roller vibrator 4 is also arranged on one side of the acceleration sensor 3. The roller vibrator 4 is placed on the outside of the specimen 13 and emits excitation at the end of the specimen. The acceleration sensor 3 is adsorbed on the end of the specimen 13, connected to the microcomputer controller 2, receives the vibration signal of the specimen 13, and converts the stress wave data into an electrical signal and transmits it to the microcomputer controller 2.

[0033] The roller vibrator 4 is connected to the microcomputer controller 2, and is placed 5-10 cm away from the exposed end of the test piece 13. It is controlled by the microcomputer controller 2 and uses magnetic excitation technology to generate excitation at the end of the test piece.

[0034] Reference Figure 1 and Figure 3 The displacement sensor 5 is arranged on a side wall of the fuselage frame 12 and connected to the microcomputer controller 2. It receives the axial displacement signal of the test piece 13 and converts the displacement data into an electrical signal and transmits it to the microcomputer controller 2.

[0035] Reference Figure 1 and Figure 3 The column sensor 6 is connected to the axial loading module 7, receives the axial load signal of the test piece 13, converts the load data into an electrical signal and transmits it to the microcomputer controller 2. One end of the test piece 13 is connected to the displacement observation rod, and the other side of the displacement observation rod is connected to the displacement sensor 5 arranged on the fuselage frame 12. The displacement sensor 5 detects the displacement of the displacement observation rod, that is, the axial displacement of the test piece 13.

[0036] Reference Figure 3 The axial loading module 7 is actually a mining anchor puller, which is a commonly used device in the field. This application is only for use, so its principle is not introduced in detail; the axial loading module 7 is connected to the fuselage frame 12, wherein one end of the specimen 13 passes through the axial loading module 7, and the other end of the specimen 13 is fixed by the clamping member 11, which is controlled by a microcomputer controller to apply an axial load or displacement to the specimen 13.

[0037] Reference Figure 1 and Figure 3 The high-speed camera 8 is independent and unconnected. The high-speed camera 8 is located above the fuselage frame 12 and can be rotated. Its angle direction is toward the test piece 13 of the fuselage frame 12. It can shoot or take pictures at any time to record image data.

[0038] Reference Figure 2The shearing module 9 is connected to the fuselage and is controlled by the microcomputer controller 2. It can move along the axial direction of the specimen 13 and can apply shear force or displacement to the specimen 13. The shearing module 9 includes a support frame 91 installed at the rear end of the fuselage frame 12, wherein a shearing cylinder 92 is installed on the support frame 91, and the output end of the shearing cylinder 92 is in contact with the specimen 13. A displacement sensor 10 is provided on the inner wall of the fuselage frame 12. The displacement sensor 10 is connected to the shearing cylinder 92, and the displacement sensor 10 is connected to the microcomputer controller 2 to receive the shear displacement signal of the specimen 13 and convert the displacement data into an electrical signal and transmit it to the microcomputer controller 2.

[0039] Reference Figure 3 There are two groups of clamping members 11, which are respectively located on both sides of the test piece 13. The other sides of the two groups of clamping members 11 are connected to the inner wall of the fuselage frame 12 through the cylinder 14. The side of the clamping member 11 in contact with the test piece 13 is set in a rectangular tooth shape. The clamping member 11 is connected to the microcomputer controller 2 and the fuselage frame 12, and is controlled by the microcomputer controller 2 to control the two cylinders 14 to drive the clamping member 11 to clamp the bottom end of the test piece 13.

[0040] The specific operating principles of this application are as follows:

[0041] 1. Preparation before the test.

[0042] Connect the control end 1 to the microcomputer controller 2, connect the displacement sensor 1 5, displacement sensor 2 10, column sensor 6, roller vibrator 4, axial loading module 7, and shear module 9 to the microcomputer controller 2, turn on and debug the high-speed camera 8; use the dedicated software of the control end 1 (i.e., computer) to write the experimental plan, including axial and radial loading instructions, maintenance control instructions, and controlling the roller vibrator 4 to issue excitation instructions, etc.

[0043] 2. Install the test piece and preload it.

[0044] The specimen 13 (i.e., anchor rod / anchor body) is passed through the axial loading module 7, and the clamping device 11 is controlled to clamp the bottom end of the specimen 13. The exposed end of the specimen 13 is fixed with a tray and a nut, and the tray is in contact with the column sensor 6. The roller vibrator 4 is placed 10 cm away from the end of the anchor rod, and the acceleration sensor 3 is adsorbed on the exposed end of the anchor rod. The shear module 9 is controlled to move to the specified position, the shear cylinder 92 is in contact with the specimen 13, and the tray is in contact with the axial loading module 7.

[0045] 3. Start the experiment.

[0046] According to the experimental plan, the axial loading module 7 and the shearing module 9 are controlled to program the specimen 13. All load and displacement data in the anchor loading process are output to the microcomputer controller 2 through the column sensor 6, the displacement sensor 1 5, and the displacement sensor 2 10, and finally output to the computer and saved. The experimental plan sets a maintenance control process (the control variables remain unchanged during the loading process). During the maintenance control process, the roller vibrator 4 is controlled to emit excitation, and the acceleration sensor 3 collects the vibration signal of the specimen 13 under different stress states, which is finally output to the control terminal 1 through the microcomputer controller 2 for storage. While performing stress wave detection, a high-speed camera 8 is used to take pictures to keep the data time point consistent, and record and save the image data of the deformation and destruction process under the combined stress of the anchor / anchor body.

[0047] 4. Non-destructive testing method for anchor deformation / anchor body damage under combined stress.

[0048] The axial, radial and total stress-strain curves of specimen 13 under the composite stress are obtained based on the load-displacement data analysis. The deformation and damage conditions of specimen 13 at each moment are obtained based on the image data analysis. The characteristic value change trend of the specimen at different stretching moments is obtained based on the stress wave data analysis. The different change stages of the specimen under the composite stress are summarized and classified through the stress-strain curve. Standards are formulated for the actual deformation and damage conditions of the specimen corresponding to the different change stages based on the image data. Signal analysis and processing are performed on the stress wave data to summarize the characteristic value change trend of the stress wave data at different change stages of the specimen under the composite stress. Finally, the deformation and damage conditions of the specimen under the composite stress are corresponding to the characteristic values ​​of the anchor stress wave data, thereby achieving the purpose of non-destructive testing of evaluating the deformation of the anchor / anchor body using stress wave signals.

[0049] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A nondestructive testing system for anchoring bodies under combined stress, comprising a fuselage frame (12) and a test piece (13), characterized in that: An axial loading module (7) is installed on one side of the interior of the fuselage frame (12), a clamping device is provided on the other side of the interior of the fuselage frame (12), and a shearing module (9) is installed above the clamping device; One end of the test piece (13) passes through the axial loading module (7), the other end of the test piece (13) is fixed by a clamping device, and the shearing module (9) is located above the test piece (13) and in contact with it.

2. The nondestructive testing system for anchoring bodies under composite stress according to claim 1 is characterized in that: A column sensor (6) is provided on the outer side wall of the fuselage frame (12), wherein the column sensor (6) is connected to the axial loading module (7) and receives the axial load signal of the test piece (13).

3. The nondestructive testing system for anchoring bodies under composite stress according to claim 1 is characterized in that: One side of the test piece (13) is connected to a displacement observation rod, and the other side of the displacement observation rod is connected to a displacement sensor (5) arranged on the fuselage frame (12).

4. The nondestructive testing system for anchoring bodies under composite stress according to claim 1 is characterized by: An acceleration sensor (3) is provided on the outside of the fuselage frame (12) and on one side of the column sensor (6), and a roller exciter (4) is also provided on one side of the acceleration sensor (3). The roller exciter (4) is placed outside the test piece (13) and emits excitation at the end of the test piece; The acceleration sensor (3) is adsorbed on the end of the test piece (13) and receives a vibration signal of the test piece.

5. The nondestructive testing system for anchoring bodies under composite stress according to claim 1 is characterized by: A bracket (15) is provided on one side of the fuselage frame (12), wherein the top of the bracket (15) is connected to a high-speed camera (8), and the high-speed camera (8) is located above the fuselage frame (12), with its angular direction facing the test piece (13) of the fuselage frame (12).

6. The nondestructive testing system for anchoring bodies under composite stress according to claim 1 is characterized by: The shearing module (9) comprises a support frame (91) mounted at the rear end of a fuselage frame (12), wherein a shearing cylinder (92) is mounted on the support frame (91), and an output end of the shearing cylinder (92) is in contact with a test piece (13).

7. The nondestructive testing system for anchoring bodies under combined stress according to claim 6, characterized in that: A second displacement sensor (10) is provided on the inner side wall of the fuselage frame (12); the second displacement sensor (10) is connected to the shearing cylinder (92), and the second displacement sensor (10) receives the shear displacement signal of the test piece (13).

8. The nondestructive testing system for anchoring bodies under composite stress according to claim 1 is characterized by: The clamping device comprises a clamping member (11) and a cylinder (14), wherein the clamping member (11) is provided with two groups, which are respectively located on both sides of the test piece (13), and the other sides of the two groups of clamping members (11) are connected to the inner wall of the fuselage frame (12) through the cylinder (14).

9. The anchor body nondestructive testing system under composite stress according to claim 8, characterized in that: The surface of the clamping piece (11) in contact with the test piece (13) is configured in a rectangular tooth shape.

10. The nondestructive testing system for anchoring bodies under composite stress according to claim 1, characterized in that: It also includes a control end (1) and a microcomputer controller (2), wherein the control end (1) is connected to the microcomputer controller (2), and the microcomputer controller (2) is connected to the axial loading module (7) and the shearing module (9).

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