Airplane support testing tool
By designing an aircraft bearing test tooling including mounting plate, shear plate, limit plate and pull rod, the problems of low testing accuracy and efficiency in the prior art are solved, and the shearing capacity of aircraft bearings is achieved is achieved. Evaluation and reliability test for bonding strength.
Patent Information
- Application Number
- CN202420913715.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-04-29
- Publication Date
- 2025-01-14
- Estimated Expiration
- 2034-04-29
AI Technical Summary
In the prior art, testing of aircraft bearings is limited by the bonding position, resulting in low test accuracy and efficiency, especially in evaluating the shear bonding strength of thread bearings.
An aircraft bearing testing tool is designed, including a mounting plate, a shear plate, a limit plate and a tie rod. One end of the support is bonded to the mounting plate, and the other end is connected to the shear plate through the limit plate, and through the first The tension forces of the tie rod and the second tie rod act on both ends of the support respectively to ensure the accuracy and reliability of the test.
The test tooling can efficiently and accurately evaluate the shear bearing capacity of the aircraft bearing in the laboratory, improves testing efficiency and reduces manufacturing costs, and ensures reliability and repeatability of bonding strength.
Smart Images
Figure CN222353704U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aircraft support testing, in particular to an aircraft support testing tool. Background Art
[0002] Aircraft supports are now widely used in various types of aircraft, such as civil aviation, military aviation, general aviation and other application fields. Conventional mechanical connection brackets need to drill holes at the connection position, which has high process costs, and the use of a large number of fasteners causes the aircraft to increase weight. In addition, the brackets are used in composite materials. After the holes are made, local stress concentration will occur in the surrounding areas of the composite laminate, reducing the connection efficiency. It also requires high hole-making technology for the composite laminate, resulting in high manufacturing costs and poor economic efficiency.
[0003] The use of bonded threaded supports has a series of advantages that riveting does not have, such as high structural fatigue strength, easy disassembly of bonded brackets, and self-sealing properties. It can greatly reduce manufacturing costs, improve production efficiency, and achieve aircraft weight reduction. However, due to the shaking of cables or wire harnesses caused by aircraft takeoff and landing and when the aircraft encounters gusts, the threaded supports need to bear the shear load from the cables. If the bonded threaded supports are not firmly bonded to the aircraft structure, there may be risks such as the cable falling off or even breaking. Therefore, it is necessary to evaluate the shear bonding strength of the bonded threaded supports.
[0004] In the prior art, workers usually test after gluing the threaded support. Due to the limitation of the gluing position, the use of the test instrument is limited, which affects the accuracy and efficiency of the test.
[0005] Therefore, there is an urgent need for an aircraft support test fixture to solve the above technical problems. Utility Model Content
[0006] The utility model aims to provide an aircraft support test tool, which can ensure the test accuracy and improve the test efficiency.
[0007] To achieve this purpose, the utility model adopts the following technical solutions:
[0008] An aircraft support testing tool is used to test the shear capacity of an aircraft support, comprising: a mounting plate, a shear plate, a limit plate, a first pull rod and a second pull rod, one end of the support is connected to the mounting plate, the mounting plate is installed on the limit plate, and the other end of the support passes through the limit plate and is connected to the shear plate, the first pull rod is connected to the shear plate, and the second pull rod is connected to the limit plate, so that the tension of the first pull rod and the second pull rod can act on the two ends of the support respectively.
[0009] As a preferred technical solution of the above-mentioned aircraft support test fixture, the first pull rod is provided with a first installation groove, and the shear plate is arranged in the first installation groove.
[0010] As a preferred technical solution of the above-mentioned aircraft support test fixture, the first pull rod is provided with a first mounting hole, and the aircraft support test fixture also includes a first mounting member, and the first mounting member can pass through the first mounting hole and the shear plate in sequence.
[0011] As a preferred technical solution of the above-mentioned aircraft support test fixture, the second pull rod is provided with a second installation groove, and the limiting plate is arranged in the second installation groove.
[0012] As a preferred technical solution of the above-mentioned aircraft support test tool, the second pull rod is provided with a second mounting hole, and the aircraft support test tool also includes a second mounting member, and the second mounting member can pass through the second mounting hole and the limit plate in sequence.
[0013] As a preferred technical solution of the above-mentioned aircraft support test fixture, the limiting plate is provided with a limiting groove, and the mounting plate is arranged in the limiting groove.
[0014] As a preferred technical solution of the above-mentioned aircraft support test fixture, the limiting groove is provided with a first through hole, the shear plate is provided with a second through hole, and the other end of the support can pass through the first through hole and be inserted into the second through hole.
[0015] As an optimal technical solution for the above-mentioned aircraft support test tooling, the support includes a mounting seat and a bracket, the mounting seat and the bracket are fixedly connected, the mounting seat is bonded to the mounting plate, and the diameter of the mounting seat is smaller than the aperture of the first through hole.
[0016] As a preferred technical solution of the above-mentioned aircraft support test fixture, the aircraft support test fixture also includes a positioning piece, and the positioning piece can be inserted into the second through hole from an end away from the limiting plate and connected to the bracket.
[0017] As a preferred technical solution of the above-mentioned aircraft support test fixture, the bracket is provided with a threaded hole, the positioning member is a screw, and the positioning member is threadedly connected to the bracket through the threaded hole.
[0018] Beneficial effects of the utility model:
[0019] The utility model provides an aircraft support test tool. The aircraft support test tool is used to test the shear bearing capacity of the aircraft support. The aircraft support test tool includes: a mounting plate, a shear plate, a limit plate, a first pull rod and a second pull rod. One end of the support is bonded to the mounting plate, the mounting plate is installed on the limit plate, and the other end of the support passes through the limit plate and is connected to the shear plate. The first pull rod is connected to the shear plate, and the second pull rod is connected to the limit plate, so that the tension of the first pull rod and the second pull rod can act on the two ends of the support respectively. Compared with the prior art, the aircraft support test tool can complete the test of the support in the laboratory, can ensure the accuracy and reliability of the test, and improve the test efficiency. BRIEF DESCRIPTION OF THE DRAWINGS
[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the contents of the embodiments of the present invention and these drawings without paying any creative work.
[0021] Figure 1 A schematic diagram of the structure of an aircraft support test tool provided by an embodiment of the utility model;
[0022] Figure 2 for Figure 1 Sectional view in the AA direction;
[0023] Figure 3 A cross-sectional view of a first pull rod provided in an embodiment of the utility model;
[0024] Figure 4 A cross-sectional view of a support provided in an embodiment of the utility model.
[0025] In the figure:
[0026] 1. Mounting plate; 2. Shear plate; 3. Limiting plate; 31. Limiting groove; 311. First through hole; 4. First pull rod; 41. First mounting groove; 42. First mounting hole; 5. Second pull rod; 51. Second mounting groove; 6. Support; 61. Mounting seat; 62. Bracket; 621. Threaded hole; 7. First mounting member; 8. Second mounting member; 9. Positioning member. DETAILED DESCRIPTION
[0027] The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only the parts related to the present invention, rather than all structures, are shown in the accompanying drawings.
[0028] 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.
[0029] 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.
[0030] In the description of this embodiment, the terms "upper", "lower", "left", "right" and other directions or positional relationships are based on the directions or positional relationships shown in the drawings, and are only for the convenience of description and simplified operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation of the present invention. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.
[0031] like Figure 1 and Figure 2 As shown, the utility model provides an aircraft support test tool. The aircraft support test tool comprises: a mounting plate 1, a shear plate 2, a limit plate 3, a first tie rod 4 and a second tie rod 5.
[0032] Specifically, one end of the support 6 is bonded to the mounting plate 1, the mounting plate 1 is mounted on the limit plate 3, and the other end of the support 6 passes through the limit plate 3 and is connected to the shear plate 2, the first tie rod 4 is connected to the shear plate 2, and the second tie rod 5 is connected to the limit plate 3, so that the tension of the first tie rod 4 and the second tie rod 5 can act on the two ends of the support 6 respectively. Compared with the prior art, the aircraft support test fixture can complete the test of the support 6 in the laboratory, can ensure the accuracy and reliability of the test, and improve the test efficiency.
[0033] Preferably, in order to facilitate the connection between the first pull rod 4 and the shear plate 2, a first mounting groove 41 is provided at one end of the first pull rod 4, the other end of the first pull rod 4 is connected to the testing machine, and one end of the shear plate 2 is installed in the first mounting groove 41, which is convenient for assembly and disassembly of the test tooling.
[0034] Preferably, if Figure 3 As shown, the first tie rod 4 is provided with a first mounting hole 42, and the aircraft support test fixture further includes a first mounting member 7, and the first mounting member 7 can pass through the first mounting hole 42 and the shear plate 2. Specifically, in order to improve the stability of the connection between the shear plate 2 and the first tie rod 4, the two opposite groove walls of the first mounting groove 41 are both provided with first mounting holes 42, and the two first mounting holes 42 are aligned with each other, the shear plate 2 is provided with a third through hole, the shear plate 2 is inserted into the first mounting groove 41, and the first mounting member 7 can pass through the first mounting hole 42, the third through hole and another first mounting hole 42 to firmly connect the shear plate 2 with the first tie rod 4, so as to prevent the shear plate 2 from being separated from the first tie rod 4.
[0035] Optionally, the first mounting member 7 is a pin.
[0036] Preferably, in order to facilitate the connection between the second pull rod 5 and the limit plate 3, a second mounting groove 51 is provided at one end of the second pull rod 5, the other end of the second pull rod 5 is connected to another testing machine, and one end of the limit plate 3 is installed in the second mounting groove 51, which is convenient for assembly and disassembly of the test tooling.
[0037] Preferably, the second tie rod 5 is provided with a second mounting hole, and the aircraft support test fixture further comprises a second mounting member 8, and the second mounting member 8 can pass through the second mounting hole and the limiting plate 3. Specifically, in order to improve the stability of the connection between the limiting plate 3 and the second tie rod 5, the two opposite groove walls of the second mounting groove 51 are provided with second mounting holes, and the two second mounting holes are aligned with each other, the limiting plate 3 is provided with a fourth through hole, the limiting plate 3 is inserted into the second mounting groove 51, and the second mounting member 8 can pass through the second mounting hole, the fourth through hole and another second mounting hole to firmly connect the limiting plate 3 with the second tie rod 5, so as to prevent the limiting plate 3 from being separated from the second tie rod 5.
[0038] Optionally, the second mounting member 8 is a pin.
[0039] Preferably, the limiting plate 3 is provided with a limiting groove 31, and the mounting plate 1 is installed in the limiting groove 31. Specifically, in order to prevent the mounting plate 1 from moving, the limiting plate 3 is provided with a limiting groove 31, and the mounting plate 1 is installed in the limiting groove 31, and the outer side wall of the mounting plate 1 abuts against the groove wall of the limiting groove 31, which can prevent the movement of the mounting plate 1 from affecting the test results.
[0040] Preferably, the limiting groove 31 is provided with a first through hole 311, the shear plate 2 is provided with a second through hole, and the other end of the support 6 can pass through the first through hole 311 and be inserted into the second through hole. Specifically, the bottom of the limiting groove 31 is provided with a first through hole 311, the shear plate 2 has a second through hole, one end of the support 6 is bonded to the mounting plate 1, and when the mounting plate 1 is fixed to the limiting plate 3, the other end of the support 6 passes through the first through hole 311 and is inserted into the second through hole, and the shear plate 2 and the limiting plate 3 are spaced apart, so that the shear plate 2 and the limiting plate 3 apply opposite pulling forces to the two ends of the support 6, completing the shear strength test of the support 6.
[0041] Preferably, if Figure 4 As shown, the support 6 includes a mounting seat 61 and a bracket 62, the mounting seat 61 and the bracket 62 are fixedly connected, the mounting seat 61 is bonded to the mounting plate 1, and the diameter of the mounting seat 61 is smaller than the aperture of the first through hole 311. Specifically, the support 6 includes the mounting seat 61 and the bracket 62, the mounting seat 61 is circular, the mounting seat 61 is used to bond with the aircraft shell, and the bracket 62 is used to support the cable. When testing the support 6, the mounting seat 61 is bonded to the mounting plate 1, and the diameter of the mounting seat 61 is smaller than the aperture of the first through hole 311, so as to prevent the mounting seat 61 from contacting with the hole wall of the first through hole 311, and to avoid the hole wall of the first through hole 311 from supporting the mounting seat 61, thereby preventing the first through hole 311 from affecting the bonding strength test of the support 6.
[0042] Preferably, the aircraft support test fixture further includes a positioning member 9, which can be inserted into the second through hole from the end away from the limiting plate 3 and connected to the bracket 62. Specifically, in order to prevent the bracket 62 from being separated from the shear plate 2, the test fixture is provided with a positioning member 9, which is inserted into the second through hole from the end away from the limiting plate 3 and connected to the bracket 62, and can improve the stability of the connection between the bracket 62 and the shear plate 2.
[0043] Optionally, the bracket 62 is provided with a threaded hole 621, the positioning member 9 is a screw, and the positioning member 9 is threadedly connected to the bracket 62 through the threaded hole 621. Specifically, one end of the bracket 62 is fixedly connected to the mounting seat 61, and the other end of the bracket 62 is provided with a threaded hole 621, and the positioning member 9 is a screw, which is inserted into the second through hole and threadedly connected to the bracket 62, which can facilitate the assembly and disassembly of the test tooling.
[0044] Optionally, the shear plate 2 is a Z-shaped structure, which can avoid affecting the installation of the limiting plate 3.
[0045] The utility model provides an aircraft support test tool, which is convenient for installation and disassembly, realizes the shear strength test of the bonding support 6 on the aircraft, and ensures the reliability and repeatability of the bonding strength test result. The use process of the test tool is as follows:
[0046] First, bond the support 6 to the support 6 fixing plate; then, assemble the first tie rod 4, the first mounting member 7, and the shear plate 2 as a whole, and assemble the second tie rod 5, the second mounting member 8, and the limit plate 3 as a whole; thereafter, install the bonded support 6 and the fixing plate into the limit groove 31, install the positioning member 9 into the second through hole on the shear plate 2 and connect it to the support 6; then clamp the first tie rod 4 and the second tie rod 5 on the two V-shaped chucks of the material testing machine respectively; when implementing the shear strength test, set the tensile program of the testing machine, drive the chuck of the testing machine away, and collect and record the load at the same time until the support 6 is destroyed; read the peak load measured by the testing machine to obtain the shear capacity of the support 6.
[0047] In addition, the above are only preferred embodiments of the present invention and the technical principles used. Those skilled in the art will understand that the present invention is not limited to the specific embodiments described herein, and that various obvious changes, readjustments and substitutions can be made by those skilled in the art without departing from the scope of protection of the present invention. Therefore, although the present invention is described in more detail through the above embodiments, the present invention is not limited to the above embodiments, and may include more other equivalent embodiments without departing from the concept of the present invention, and the scope of the present invention is determined by the scope of the appended claims.
Claims
1. An aircraft support test tool, used for testing the shear capacity of an aircraft support (6), characterized in that: include: A mounting plate (1), a shear plate (2), a limiting plate (3), a first tie rod (4) and a second tie rod (5), one end of the support (6) is connected to the mounting plate (1), the mounting plate (1) is installed on the limiting plate (3), and the other end of the support (6) passes through the limiting plate (3) and is connected to the shear plate (2), the first tie rod (4) is connected to the shear plate (2), and the second tie rod (5) is connected to the limiting plate (3), so that the tension of the first tie rod (4) and the second tie rod (5) can act on the two ends of the support (6) respectively.
2. The aircraft support test fixture according to claim 1, characterized in that: The first pull rod (4) is provided with a first mounting groove (41), and the shear plate (2) is arranged in the first mounting groove (41).
3. The aircraft support test fixture according to claim 2, characterized in that: The first pull rod (4) is provided with a first mounting hole (42), and the aircraft support test fixture further comprises a first mounting member (7), and the first mounting member (7) can pass through the first mounting hole (42) and the shear plate (2) in sequence.
4. The aircraft support test fixture according to claim 1, characterized in that: The second pull rod (5) is provided with a second installation groove (51), and the limiting plate (3) is arranged in the second installation groove (51).
5. The aircraft support test fixture according to claim 3, characterized in that: The second pull rod (5) is provided with a second mounting hole, and the aircraft support test fixture further comprises a second mounting member (8), and the second mounting member (8) can pass through the second mounting hole and the limiting plate (3) in sequence.
6. The aircraft support test fixture according to claim 1, characterized in that: The limiting plate (3) is provided with a limiting groove (31), and the mounting plate (1) is arranged in the limiting groove (31).
7. The aircraft support test fixture according to claim 6, characterized in that: The limiting groove (31) is provided with a first through hole (311), the shear plate (2) is provided with a second through hole, and the other end of the support (6) can pass through the first through hole (311) and be inserted into the second through hole.
8. The aircraft support test fixture according to claim 7, characterized in that: The support (6) comprises a mounting seat (61) and a bracket (62); the mounting seat (61) and the bracket (62) are fixedly connected; the mounting seat (61) is bonded to the mounting plate (1); and the diameter of the mounting seat (61) is smaller than the aperture of the first through hole (311).
9. The aircraft support test fixture according to claim 8, characterized in that: The aircraft support test fixture further comprises a positioning member (9), wherein the positioning member (9) can be inserted into the second through hole from an end away from the limiting plate (3) and connected to the bracket (62).
10. The aircraft support test fixture according to claim 9, characterized in that: The bracket (62) is provided with a threaded hole (621), the positioning member (9) is a screw, and the positioning member (9) is threadedly connected to the bracket (62) through the threaded hole (621).