Test fixture and test device for aircraft bonding support

Abstract

The utility model discloses a test fixture and a test device for an aircraft bonding support, and belongs to the technical field of aerospace equipment, and the test fixture comprises a supporting assembly, a connecting assembly and a stretching assembly. The supporting assembly comprises a containing space and a placing opening, and the bonding support can be placed in the containing space through the placing opening; a first connecting rod is arranged on the supporting assembly, extends in the first linear direction and can be connected with a testing machine. A connecting opening is formed in the supporting assembly, and one end of the connecting assembly can penetrate through the connecting opening and is detachably connected with the bonding support; the stretching assembly comprises a stretching connector and a second connecting rod, the stretching connector can be connected with the end, away from the bonding support, of the connecting assembly, the second connecting rod is arranged on the stretching connector, and the second connecting rod can be connected with a testing machine. The testing device comprises a testing machine and the testing clamp, and can effectively simulate and measure the bonding strength of the bonding support of the airplane in a dynamic load environment.

Description

Technical Field

[0001] The utility model relates to the technical field of aerospace equipment, in particular to a test fixture and a test device for an aircraft bonding support. Background Art

[0002] In modern aircraft design, the safety and reliability of the electrical wiring system (EWIS) is critical to the overall flight safety. The EWIS system usually consists of multiple cables, which need to be fixed to the aircraft structure through adhesive supports. During takeoff and landing, and when encountering severe weather conditions such as gusts, the aircraft structure will vibrate and shake violently, causing corresponding dynamic stress in the cables and harnesses. This stress is mainly manifested as an out-of-plane tensile load on the adhesive support, that is, a tensile force perpendicular to the bonding surface.

[0003] Traditionally, bonded mounts are designed to withstand and distribute the dynamic and static loads from cables to prevent them from shifting or being damaged during flight. However, if the bond between the bonded mount and the aircraft structure is not strong enough, the cable may fall out of the mount or even break under the out-of-plane tensile load, which poses a serious threat to the safe operation of the aircraft.

[0004] Although the importance of this issue has been widely recognized, the existing technology still lacks a method to evaluate the bond strength of bonded bearings under out-of-plane tensile loads. Most of the existing evaluation technologies focus on the bonding performance under standard static loads, while the technology for evaluating the bond strength under complex dynamic load environments is still immature. Utility Model Content

[0005] The utility model aims to provide a test fixture and a test device for an aircraft bonding support, so as to solve the technical problem in the prior art that the bonding strength of the bonding support under a dynamic load environment cannot be measured.

[0006] As conceived above, the technical solution adopted by the utility model is:

[0007] On the one hand, an embodiment of the utility model provides a test fixture for an aircraft bonding support, comprising:

[0008] A support assembly, the support assembly comprising a receiving space and a placement opening, the placement opening being connected to the receiving space, and the adhesive support can be placed in the receiving space through the placement opening; a first connecting rod is provided on the support assembly, the first connecting rod extends along a first straight line direction, and the first connecting rod can be connected to the testing machine;

[0009] A connecting component, wherein a connecting port is provided on the supporting component, the connecting port is connected to the accommodating space, and one end of the connecting component can pass through the connecting port and be detachably connected to the adhesive support;

[0010] A stretching assembly, the stretching assembly comprising a stretching joint and a second connecting rod, the stretching joint being capable of connecting an end of the connecting assembly away from the bonding support, the second connecting rod being arranged on the stretching joint, the second connecting rod extending along the first straight line and in a direction opposite to the first connecting rod, and the second connecting rod being capable of being connected to the testing machine.

[0011] Preferably, the connecting assembly includes a bearing column and a connecting piece, one end of the bearing column is fixedly connected to the supporting assembly, the other end of the bearing column is connected to the tensile joint, and the connecting piece can be connected to the bearing column and detachably connected to the adhesive support.

[0012] Preferably, the connecting member comprises a connecting plate and an adhesive plate, the connecting plate and the adhesive plate are integrally formed, the connecting plate can be passed through the connecting port and detachably connected to the bearing column, and the adhesive plate can be bonded to the adhesive support.

[0013] Preferably, the cross-sectional area of ​​the adhesive plate is larger than the area of ​​the connecting port.

[0014] Preferably, the connecting assembly includes a locking bolt, a connecting hole is formed on the connecting plate, a threaded hole is formed at a corresponding position of the supporting column, and the locking bolt can pass through the connecting hole and be threadedly connected with the threaded hole.

[0015] Preferably, the bearing column includes a first vertical plate, a second vertical plate and a horizontal plate, which are integrally formed, the first vertical plate and the second vertical plate are arranged in parallel and connected by the horizontal plate, the first vertical plate is fixedly connected to the supporting assembly, and the extension direction of the second vertical plate coincides with the first straight line and can be connected to the tensile joint.

[0016] Preferably, a positioning groove is provided on the stretch joint, and the bearing column can be inserted into the positioning groove and hinged to the stretch joint.

[0017] Preferably, the first connecting rod and / or the second connecting rod can be telescopic along its own axial direction.

[0018] Preferably, a transparent blocking door is provided on the support assembly, and the transparent blocking door is movably connected to the support assembly, and the transparent blocking door can open or close the placement opening.

[0019] On the other hand, an embodiment of the utility model also provides a testing device, including a testing machine and the above-mentioned testing fixture for aircraft adhesive supports, the testing machine including a driving unit and two clamping heads, the two clamping heads can respectively clamp the first connecting rod and the second connecting rod, and the driving unit can respectively drive the two clamping heads to move in opposite directions.

[0020] Beneficial effects of the utility model:

[0021] The test fixture for aircraft adhesive support proposed by the utility model, when in use, first connects the adhesive support with the connection assembly, and clamps the first connecting rod of the support assembly through a clamping head of the testing machine; then, installs the adhesive support together with the connection assembly in the accommodating space, and makes one end of the connecting assembly pass through the connection port and connect with the tensile joint; finally, adjusts the relative position between the two clamps of the testing machine so that the second connecting rod on the tensile joint is clamped by the other clamping head of the testing machine. After the connection is completed, the tensile strength test is implemented, firstly, the tensile program of the testing machine is set, the clamping head of the testing machine is driven to move so as to apply a tensile load to the adhesive support, and at the same time, the load is collected and recorded until the adhesive support is destroyed. After the test is completed, the peak load measured by the testing machine is read to obtain the out-of-plane tensile strength of the adhesive support. By setting the accommodating space on the support assembly, the test fixture can be conveniently placed and fixed on the adhesive support, ensuring the stability and repeatability during the test process. The size and shape of the accommodating space can be accurately manufactured according to the actual size of the adhesive support to ensure the correct position and direction of the adhesive support during the test, thereby improving the accuracy of the test results. By applying forces in different directions through the first connecting rod and the second connecting rod, the out-of-plane tensile load on the bonded bearing when the aircraft encounters gusts or other dynamic stresses is simulated, thereby more accurately simulating and evaluating the performance of the bonded bearing in actual use. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic structural diagram of the cooperation between the test fixture and the test device for the aircraft bonding support provided in the first embodiment of the utility model;

[0023] Figure 2 This is a schematic structural diagram of a test fixture for aircraft bonding supports provided in the first embodiment of the utility model;

[0024] Figure 3 It is a structural schematic diagram of the support assembly provided in the first embodiment of the utility model;

[0025] Figure 4 It is a structural schematic diagram of a connecting piece provided in Embodiment 1 of the present utility model;

[0026] Figure 5 It is a structural schematic diagram of a bearing column provided in Embodiment 1 of the present utility model;

[0027] Figure 6 It is a structural schematic diagram of the stretching assembly provided in Example 1 of the utility model.

[0028] In the figure:

[0029] 100. Testing machine; 101. Clamping head;

[0030] 10. Support assembly; 11. Placement port; 12. Connection port; 13. First connection rod;

[0031] 20. Connecting assembly; 21. Load-bearing column; 211. First vertical plate; 212. Second vertical plate; 213. Horizontal plate; 22. Connecting member; 221. Connecting plate; 222. Adhesive plate;

[0032] 30. stretching assembly; 31. stretching joint; 311. positioning groove; 32. second connecting rod. DETAILED DESCRIPTION

[0033] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0034] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral 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, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0035] In the present utility model, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0036] The technical solution of the utility model is further explained below with reference to the accompanying drawings and through specific implementation methods.

[0037] See also Figures 1 to 3 The test fixture for aircraft adhesive supports provided by the embodiment of the utility model includes a support assembly 10, a connection assembly 20 and a stretching assembly 30. The support assembly 10 includes a receiving space and a placement opening 11, the placement opening 11 is connected to the receiving space, and the adhesive support can be placed in the receiving space through the placement opening 11; a first connecting rod 13 is provided on the support assembly 10, the first connecting rod 13 extends along the first straight line direction, and the first connecting rod 13 can be connected to the test machine 100; a connection opening 12 is provided on the support assembly 10, the connection opening 12 is connected to the receiving space, and one end of the connection assembly 20 can pass through the connection opening 12 and be detachably connected to the adhesive support; the stretching assembly 30 includes a stretching joint 31 and a second connecting rod 32, the stretching joint 31 can connect one end of the connection assembly 20 away from the adhesive support, and a second connecting rod 32 is provided on the stretching joint 31, the second connecting rod 32 extends along the first straight line and in the opposite direction to the first connecting rod 13, and the second connecting rod 32 can be connected to the test machine 100.

[0038] Adhesive supports can be used at the corners of aircraft structures to achieve connection. They not only have the advantages of simple process, convenient installation, and low structural weight gain, but also have strong adaptability to the bonding position and are suitable for the EWIS system of composite aircraft. Adhesive supports are common basic equipment in this field, and their specific structure and working principle will not be described in detail here.

[0039] In this embodiment, the support assembly 10 is horizontally arranged, and the first straight line direction is defined as the vertical direction. For the convenience of description in conjunction with the drawings, the directions below are described in accordance with the directions shown in the drawings, but are not limited thereto.

[0040] When in use, first connect the bonding support to the connection assembly 20, and clamp the first connecting rod 13 of the support assembly 10 through a clamping head 101 of the testing machine 100; then, install the bonding support together with the connection assembly 20 in the accommodation space, and make one end of the connection assembly 20 pass through the connection port 12 and connect with the tensile joint 31; finally, adjust the relative position between the two clamping heads 101 of the testing machine 100 so that the second connecting rod 32 on the tensile joint 31 is clamped by the other clamping head 101 of the testing machine 100. After the connection is completed, the tensile strength test is carried out. First, the tensile program of the testing machine 100 is set, and the clamping head 101 of the testing machine 100 is driven to move so as to apply a tensile load to the bonding support, and the load is collected and recorded at the same time until the bonding support is destroyed. After the test is completed, the peak load measured by the testing machine 100 is read to obtain the out-of-plane tensile strength of the bonding support. By setting an accommodation space on the support assembly 10, the test fixture can be conveniently placed and fixed on the bonding support to ensure stability and repeatability during the test. The size and shape of the accommodating space can be precisely manufactured according to the actual size of the bonding support to ensure the correct position and direction of the bonding support during the test, thereby improving the accuracy of the test results. By applying forces in different directions through the first connecting rod 13 and the second connecting rod 32, the out-of-plane tensile load on the bonding support when the aircraft encounters gusts or other dynamic stresses is simulated, thereby more accurately simulating and evaluating the performance of the bonding support in actual use.

[0041] Regarding the connection assembly 20, the connection assembly 20 includes a bearing column 21 and a connector 22. One end of the bearing column 21 is fixedly connected to the support assembly 10, and the other end of the bearing column 21 is connected to the tensile joint 31. The connector 22 can be connected to the bearing column 21 and detachably connected to the adhesive support. The bearing column 21 makes the structure of the entire test fixture more stable, ensuring that when performing a tensile test, the entire test fixture can stably withstand a large tensile force and reduce test errors caused by structural instability. The connector 22 can be detachably connected to the bearing column 21, thereby improving flexibility. The operator can select or adjust different connectors 22 according to different types and sizes of adhesive supports to meet various testing requirements.

[0042] See also Figure 4Specifically, the connecting member 22 includes a connecting plate 221 and an adhesive plate 222, and the connecting plate 221 and the adhesive plate 222 are integrally formed. The connecting plate 221 can be inserted into the connecting port 12 and detachably connected to the bearing column 21, and the adhesive plate 222 can be bonded to the adhesive support. The integrally formed design of the connecting plate 221 and the adhesive plate 222 improves the strength and durability of the overall structure. The bonding of the adhesive plate 222 to the adhesive support thereby improves the applicability, so that the connecting member 22 can be connected to a variety of adhesive supports. In other embodiments, it can also be set to be magnetically connected to the adhesive support, bolted, etc., which is not limited here.

[0043] In order to prevent the connecting plate 221 from driving the adhesive plate 222 during the test so that the adhesive support falls out of the connecting port 12, affecting the test process and posing a safety hazard, in this embodiment, the cross-sectional area of ​​the adhesive plate 222 is larger than the area of ​​the connecting port 12, so that the adhesive plate 222 can also play a limiting role, preventing the adhesive support from falling out of the connecting port 12.

[0044] More specifically, the connection assembly 20 includes a locking bolt, a connection hole is provided on the connection plate 221, and a threaded hole is provided at a corresponding position of the bearing column 21, and the locking bolt can pass through the connection hole and be threadedly connected with the threaded hole. The use of the locking bolt through the threaded connection of the connection hole and the threaded hole improves the stability and vibration resistance of the connection assembly 20, and can prevent the connection plate 221 from falling off from the bearing seat due to vibration or tensile force during the test, thereby ensuring the accuracy and reliability of the test. In other embodiments, the connection plate 221 can also be connected to the bearing column 21 by a pin, a snap-on connection, etc., which is not limited here.

[0045] See also Figure 5 Regarding the specific structure of the bearing column 21, in this embodiment, the bearing column 21 includes a first vertical plate 211, a second vertical plate 212 and a horizontal plate 213, which are integrally formed. The first vertical plate 211 and the second vertical plate 212 are arranged in parallel and connected by the horizontal plate 213. The first vertical plate 211 is fixedly connected to the support assembly 10, and the extension direction of the second vertical plate 212 coincides with the first straight line and can be connected to the tension joint 31. The first vertical plate 211 and the second vertical plate 212 are integrally formed and connected by the horizontal plate 213, which enhances the structural stability and rigidity of the entire bearing column 21, so that the bearing column 21 can withstand higher loads and has better stability. The extension direction of the second vertical plate 212 coincides with the first straight line, thereby ensuring that the tension joint 31 and the second connecting rod 32 also coincide with the first straight line, so that the second connecting rod 32 is coaxially arranged with the first connecting rod 13, ensuring that a uniform and symmetrical tension can be applied to the bonding support during the stretching process, thereby more accurately simulating and evaluating the performance of the bonding support in actual use.

[0046] In actual situations, sometimes the directions of the forces on both sides of the bonding support are not in the same straight line. Therefore, in order to improve the realistic effect of the test fixture simulation, a positioning groove 311 is provided on the tensile joint 31, and the bearing column 21 can be inserted into the positioning groove 311 and hinged to the tensile joint 31. The positioning groove 311 and the hinge design allow the tensile joint 31 to be rotated as needed during use, thereby changing the direction of the first connecting rod 13, so that the test fixture can simulate forces in different directions and more realistically simulate the dynamic loads on the bonding support in actual flight.

[0047] See also Figure 2 and Figure 6 Specifically, through holes are symmetrically arranged on both sides of the positioning groove 311, and a through hole is arranged at one end of the second vertical plate 212. The pin can be inserted into the through hole and the through hole to connect the bearing column 21 and the stretching joint 31. When in use, the stretching joint 31 can be pushed according to demand, so that the stretching joint 31 rotates around the pin, so that the direction of the first connecting rod 13 can be adjusted to change the load direction of the bonding support. In other embodiments, the second vertical plate 212 can also be bolted to the positioning groove 311, which is not limited here.

[0048] In order to improve the adaptability of the test fixture so as to be suitable for different types of test machines 100, the first connecting rod 13 and / or the second connecting rod 32 can be extended and retracted along their own axis. Thus, the lengths of the first connecting rod 13 and the second connecting rod 32 can be adjusted as required to facilitate connection with the test machine 100, which has high flexibility.

[0049] In addition, in order to prevent debris from splashing into the equipment gap after the adhesive support is destroyed, causing damage to the equipment. In this embodiment, a transparent blocking door is provided on the support assembly 10, and the transparent blocking door is movably connected to the support assembly 10, and the transparent blocking door can open or close the placement port 11. The transparent blocking door is provided on the side wall of the placement port 11 and is hinged to the side of the placement port 11, so as to facilitate opening and closing of the transparent blocking door. When the adhesive support needs to be installed, the transparent blocking door is opened to place the adhesive support into the accommodating space from the placement port 11; when the test starts, the transparent blocking door is closed to prevent debris from splashing. In addition, the transparent blocking door makes it convenient for the operator to observe the test status of the adhesive support in the accommodating space from the outside.

[0050] Embodiment 2

[0051] The embodiment of the utility model also provides a testing device, including a testing machine 100 and the above-mentioned test fixture for aircraft adhesive supports, the testing machine 100 includes a driving unit and two clamping heads 101, the two clamping heads 101 can clamp the first connecting rod 13 and the second connecting rod 32 respectively, and the driving unit can drive the two clamping heads 101 to move in opposite directions respectively. By independently driving the two clamping heads 101, the actual force exerted on the adhesive support in situations such as aircraft takeoff, landing and encountering gusts during flight can be accurately simulated, thereby providing more accurate test results. The two clamping heads 101 can clamp the first connecting rod 13 and the second connecting rod 32 of the test fixture respectively, which not only makes the testing device applicable to adhesive supports of various sizes and designs, but also can cope with a variety of test situations, such as tensile tests at different angles and directions. It can be understood that the testing machine 100 uses existing mechanical equipment, and its specific structure and working principle will not be repeated here.

[0052] The above embodiments are only to illustrate the basic principles and characteristics of the present invention. The present invention is not limited by the above embodiments. Without departing from the spirit and scope of the present invention, the present invention may be subject to various changes and modifications, which are within the scope of the present invention. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A test fixture for aircraft bonded supports, characterized in that: include: A support assembly (10), the support assembly (10) comprising a containing space and a placement opening (11), the placement opening (11) being connected to the containing space, and the adhesive support can be placed in the containing space through the placement opening (11); a first connecting rod (13) is provided on the support assembly (10), the first connecting rod (13) extends along a first straight line direction, and the first connecting rod (13) can be connected to the testing machine (100); A connecting component (20), wherein the supporting component (10) is provided with a connecting port (12), the connecting port (12) being connected to the accommodating space, and one end of the connecting component (20) being able to pass through the connecting port (12) and be detachably connected to the adhesive support; A stretching assembly (30), the stretching assembly (30) comprising a stretching joint (31) and a second connecting rod (32), the stretching joint (31) being capable of connecting an end of the connecting assembly (20) away from the bonding support, the second connecting rod (32) being arranged on the stretching joint (31), the second connecting rod (32) extending along the first straight line and in a direction opposite to the first connecting rod (13), the second connecting rod (32) being capable of connecting to the testing machine (100).

2. The test fixture for aircraft bonded supports according to claim 1, characterized in that: The connection assembly (20) comprises a bearing column (21) and a connection piece (22), one end of the bearing column (21) is fixedly connected to the support assembly (10), the other end of the bearing column (21) is connected to the tensile joint (31), and the connection piece (22) can be connected to the bearing column (21) and can be detachably connected to the adhesive support.

3. The test fixture for aircraft bonded supports according to claim 2, characterized in that: The connecting member (22) comprises a connecting plate (221) and an adhesive plate (222); the connecting plate (221) and the adhesive plate (222) are integrally formed; the connecting plate (221) can be inserted into the connecting port (12) and detachably connected to the bearing column (21); and the adhesive plate (222) can be bonded to the adhesive support.

4. The test fixture for aircraft bonded supports according to claim 3, characterized in that: The cross-sectional area of ​​the adhesive plate (222) is larger than the area of ​​the connecting port (12).

5. The test fixture for aircraft bonded supports according to claim 3, characterized in that: The connection assembly (20) comprises a locking bolt, a connection hole is provided on the connection plate (221), a threaded hole is provided at a corresponding position of the bearing column (21), and the locking bolt can pass through the connection hole and be threadedly connected to the threaded hole.

6. The test fixture for aircraft bonded supports according to claim 2, characterized in that: The bearing column (21) comprises a first vertical plate (211), a second vertical plate (212) and a horizontal plate (213), which are integrally formed; the first vertical plate (211) and the second vertical plate (212) are arranged in parallel and connected via the horizontal plate (213); the first vertical plate (211) is fixedly connected to the supporting assembly (10); the extension direction of the second vertical plate (212) coincides with the first straight line and can be connected to the tension joint (31).

7. The test fixture for aircraft bonded mounts according to claim 2, characterized in that: The stretch joint (31) is provided with a positioning groove (311), and the bearing column (21) can be inserted into the positioning groove (311) and hinged to the stretch joint (31).

8. The test fixture for aircraft bonded supports according to any one of claims 1 to 7, characterized in that: The first connecting rod (13) and / or the second connecting rod (32) are capable of extending and retracting along their own axial direction.

9. The test fixture for aircraft bonded supports according to any one of claims 1 to 7, characterized in that: The support assembly (10) is provided with a transparent blocking door, the transparent blocking door is movably connected to the support assembly (10), and the transparent blocking door can open or close the placement opening (11).

10. A testing device, characterized in that: The invention comprises a testing machine (100) and a test fixture for an aircraft adhesive support according to any one of claims 1 to 9, wherein the testing machine (100) comprises a driving unit and two clamping heads (101), wherein the two clamping heads (101) can respectively clamp the first connecting rod (13) and the second connecting rod (32), and the driving unit can respectively drive the two clamping heads (101) to move in opposite directions.

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