Acoustic emission sensor mounting device on aircraft structure

Abstract

The utility model belongs to the technical field of installation and design of acoustic emission sensors on airplane structures, and particularly relates to an installation device of an acoustic emission sensor on an airplane structure, which comprises a shell, a connecting edge, a vertical positioning screw and a lateral positioning screw, the shell is of a columnar structure, the top is blocked, the bottom is opened, and the acoustic emission sensor is covered; a vertical positioning screw hole is formed in the top of the shell, a plurality of lateral positioning screw holes are formed in the side wall of the shell, the two connecting edges are of a sheet structure, are connected to the outer side of the bottom of the shell and are symmetrically distributed on the outer side of the shell, the bottom of the shell is provided with an adhesive layer, and the adhesive layer is adhered to an aircraft structure; a vertical positioning screw is mounted in the vertical positioning screw hole and is propped against the top of the sensor, so that the acoustic sensor is kept in contact with the aircraft structure; the lateral positioning screws abut against the lateral direction of the acoustic sensor and fix the acoustic sensor in the lateral direction.

Description

Technical Field

[0001] The present application belongs to the technical field of acoustic emission sensor installation design on aircraft structures, and specifically relates to an acoustic emission sensor installation device on an aircraft structure. Background Art

[0002] Acoustic sensors are important components for aircraft structural health monitoring. To avoid damage to the aircraft structure, it is strictly forbidden to install acoustic sensors using fastening mounting devices.

[0003] Currently, acoustic sensors are often mounted on aircraft structures using magnetic mounting devices. However, some aircraft structures where acoustic sensors are required are constructed of non-ferromagnetic materials such as aluminum alloy, titanium alloy, and composite materials, making them impractical for magnetic mounting. Currently, the common practice is to affix the acoustic sensor to the aircraft structure using adhesive tape. This technical solution is inconvenient to install the acoustic sensor on the aircraft structure, lacks reliability in positioning the acoustic sensor on the aircraft structure, and makes it difficult to effectively monitor the health of the aircraft structure. Furthermore, the acoustic sensor is prone to detachment and lacks the necessary protection, making it susceptible to external damage.

[0004] This application is proposed in view of the above-mentioned technical defects. Summary of the Invention

[0005] The purpose of the present application is to provide an acoustic emission sensor mounting device on an aircraft structure to overcome or alleviate at least one of the existing technical deficiencies.

[0006] The technical solution of this application is:

[0007] An acoustic emission sensor mounting device on an aircraft structure comprises a housing, a connecting edge, vertical positioning screws, and lateral positioning screws;

[0008] The shell is a columnar structure with a sealed top and an open bottom, covering the acoustic emission sensor; the top of the shell has a vertical positioning screw hole, and the side wall has multiple lateral positioning screw holes;

[0009] The connecting edges are in the form of a sheet, there are two of them, connected to the outside of the bottom of the shell, symmetrically distributed on the outside of the shell, and have an adhesive layer at the bottom, which is attached to the aircraft structure;

[0010] The vertical positioning screw is installed in the vertical positioning screw hole and pressed against the top of the sensor to keep the acoustic sensor in contact with the aircraft structure;

[0011] Each lateral positioning screw is pressed against the side of the acoustic sensor to fix the acoustic sensor in the lateral direction.

[0012] According to at least one embodiment of the present application, in the above-mentioned device for mounting an acoustic emission sensor on an aircraft structure, the shell has a thickness of 3 mm to 5 mm, and the interior is flat and burr-free;

[0013] The vertical positioning screw holes and lateral positioning screw holes are reamed.

[0014] According to at least one embodiment of the present application, in the above-mentioned device for mounting an acoustic emission sensor on an aircraft structure, the thickness of the connecting edge is 2 mm to 3 mm;

[0015] The connecting edge is integrally formed with the shell.

[0016] According to at least one embodiment of the present application, in the above-mentioned device for mounting an acoustic emission sensor on an aircraft structure, the vertical positioning screw is a knurled head non-stripping screw;

[0017] The lateral positioning screw adopts a knurled head that will not fall out.

[0018] According to at least one embodiment of the present application, in the above-mentioned device for mounting an acoustic emission sensor on an aircraft structure, there may be four lateral positioning screws and their corresponding lateral positioning screw holes, which are distributed on the shell at 90° intervals along the circumferential direction.

[0019] This application has at least the following beneficial technical effects:

[0020] Provided is a device for mounting an acoustic emission sensor on an aircraft structure, which can achieve reliable positioning of the acoustic sensor on the aircraft structure and realize effective health detection of the aircraft structure. The device is easy to install and operate, is unlikely to cause the acoustic sensor to fall off, and can protect the acoustic sensor from external damage. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the use of the device for installing an acoustic emission sensor on an aircraft structure provided by an embodiment of the present application;

[0022] Figure 2 is a schematic diagram of a partial structure of an acoustic emission sensor installation device on an aircraft structure provided by an embodiment of the present application;

[0023] in:

[0024] 1-shell; 2-connecting edge; 3-vertical positioning screw; 4-lateral positioning screw; 5-aircraft structure; 6-acoustic sensor.

[0025] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limiting this application. DETAILED DESCRIPTION

[0026] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant parts can refer to the general design.

[0027] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the usual meanings understood by those skilled in the art in the field to which this application belongs. The words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application means that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0028] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0029] An acoustic emission sensor mounting device on an aircraft structure, such as Figure 1 As shown, it includes a shell 1, a connecting edge 2, a vertical positioning screw 3, and a lateral positioning screw 4.

[0030] The housing 1 is a columnar structure with a sealed top and an open bottom. The top has a vertical positioning screw hole and the side wall has multiple lateral positioning screw holes, such as Figure 2 The shell 1 has a thickness of 3 mm to 5 mm and is smooth and burr-free. The vertical and lateral positioning screw holes are reamed.

[0031] The connecting edge 2 is a sheet-like structure with a thickness of 2mm to 3mm. There are two of them, which are connected to the outside of the bottom of the shell 1 and can be integrally formed with the shell 1. They are symmetrically distributed at 180 degrees on the outside of the shell 1. Figure 2 As shown, the bottom has an adhesive layer. The adhesive layer can be made by applying adhesive.

[0032] The vertical positioning screw 3 is installed in the vertical positioning screw hole and adopts a knurled head non-slip screw GB / T839-1988.

[0033] There are multiple lateral positioning screws 4, which are installed in each lateral positioning screw hole and adopt knurled head non-slip screws GB / T839-1988. There can be four lateral positioning screws 4 and their corresponding lateral positioning screw holes, which are distributed on the housing 1 at 90° intervals along the circumference.

[0034] The aircraft structure acoustic emission sensor mounting device disclosed in the above embodiment can be adhered to the aircraft structure 5 through the adhesive layer during use, and the shell 1 can cover the acoustic sensor 6. The vertical positioning screw 3 can then be tightened so that the vertical positioning screw 3 presses against the top of the sensor 6, thereby maintaining reliable contact between the acoustic sensor and the aircraft structure 5. The lateral positioning screws 4 can also be tightened so that the lateral positioning screws 4 press against the sides of the acoustic sensor 6, thereby fixing the acoustic sensor 6 laterally. This allows for reliable positioning of the acoustic sensor 6 on the aircraft structure 5, enabling effective health detection of the aircraft structure 6. The installation operation is convenient, and the acoustic sensor 6 is unlikely to fall off. The acoustic sensor 6 can also be protected from external damage.

[0035] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. An acoustic emission sensor mounting device on an aircraft structure, characterized in that: It comprises a housing (1), a connecting edge (2), a vertical positioning screw (3), and a lateral positioning screw (4); The housing (1) is a columnar structure with a sealed top and an open bottom, covering the acoustic emission sensor (6); the top of the housing (1) has a vertical positioning screw hole, and the side wall has a plurality of lateral positioning screw holes; The connecting edges (2) are in a sheet-like structure, and are two in number, connected to the outer side of the bottom of the shell (1), symmetrically distributed on the outer side of the shell (1), and have an adhesive layer at the bottom, which is adhered to the aircraft structure (5); The vertical positioning screw (3) is installed in the vertical positioning screw hole and is pressed against the top of the sensor (6) so that the acoustic sensor maintains contact with the aircraft structure (5); Each lateral positioning screw (4) is pressed against the side of the acoustic sensor (6) to fix the acoustic sensor (6) in the lateral direction.

2. The device for mounting an acoustic emission sensor on an aircraft structure according to claim 1, wherein: The shell (1) has a thickness of 3 mm to 5 mm, and the interior is smooth and burr-free; The vertical positioning screw holes and lateral positioning screw holes are reamed.

3. The device for mounting an acoustic emission sensor on an aircraft structure according to claim 1, wherein: The thickness of the connecting edge (2) is 2 mm to 3 mm; The connecting edge (2) and the shell (1) are integrally formed.

4. The device for mounting an acoustic emission sensor on an aircraft structure according to claim 1, wherein: The vertical positioning screw (3) adopts a knurled head that does not fall out; The lateral positioning screw (4) adopts a knurled head that does not fall out.

5. The device for mounting an acoustic emission sensor on an aircraft structure according to claim 1, wherein: Specifically, there may be four lateral positioning screws (4) and corresponding lateral positioning screw holes, which are distributed on the housing (1) at intervals of 90° along the circumferential direction.

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