A test restraint device

Abstract

The utility model belongs to the technical field of airplane strength test, disclose a kind of test restraint device. The device includes support frame and the restraint mechanism being arranged on support frame, first restraint mechanism can also be directly abutted to carry out restraint to the edge of the skin structure of airplane fuselage structure test piece, that is, the free edge of skin, can prevent skin free edge to the out-of-plane direction displacement. Second restraint mechanism is fixed to the end of ordinary frame in airplane fuselage test piece structure, prevents test piece to the out-of-plane direction displacement of skin or rotates around the extension direction of longeron. Third restraint mechanism carries out the support constraint of lamination to butt joint frame, further prevent butt joint frame to the out-of-plane direction displacement of skin or rotates around the extension direction of longeron. The test restraint device provides multiple forms of constraint, effectively solve the influence caused by boundary constraint to test, simulate real constraint condition for this kind of composite material structure compression test, reduce test error, improve the accuracy and effectiveness of test data.

Description

Technical Field

[0001] This utility model relates to the field of aircraft strength testing technology, and in particular to a test constraint device. Background Technology

[0002] Composite materials are widely used due to their excellent properties and lightweight characteristics, especially in aerospace, automotive, and construction. However, testing the bonding performance of aircraft structural components made of composite materials, particularly their compressive performance under complex environments, remains an important research topic.

[0003] Especially at the connection between the mid- and aft fuselage sections of an aircraft, in addition to the need for out-of-plane constraints on the free edges of the skin and the ends of ordinary frames, the spherical frames also provide additional, different constraint support to the mating frames. This makes the connection form of the aircraft structural components at this location more complex, posing a greater challenge to performance simulation. The constraints for this type of structure during compression testing differ significantly from those for general panel compression testing. Research results on the stress and failure modes of the mid- and aft fuselage connection structure under compressive loads indicate that the test results are inextricably linked to the constraints of the test specimen. Currently, there is a lack of a test constraint device specifically designed for this type of composite material structure that can accurately apply constraint conditions to simulate the actual connection constraint conditions of the test specimen within the aircraft fuselage structure. Utility Model Content

[0004] The purpose of this utility model is to provide a test constraint device, mainly used in compression tests of aircraft fuselage structural components. In addition to considering the out-of-plane constraints of the skin free surface and the constraints of the free edges at both ends of the test component, the connection constraints of the ordinary frame and docking frame of the test component with other fuselage structures also need to be considered. In particular, it aims to solve the constraint problem of the test component when the ordinary frame and docking frame on the fuselage structure of the test component are connected with other fuselage structures during compression tests.

[0005] To achieve this objective, the present invention adopts the following technical solution:

[0006] A test constraint device includes a support frame and a constraint mechanism disposed on the support frame. The constraint mechanism includes at least a first constraint mechanism, a second constraint mechanism, and a third constraint mechanism. The first constraint mechanism, the second constraint mechanism, and the third constraint mechanism are respectively connected to different positions of the test piece, and the test piece can be displaced along a preset direction under the constraint of the constraint mechanism.

[0007] The first constraint mechanism is used to directly abut against the structure of the test piece, the second constraint mechanism is used to fix the end of the test piece structure, and the third constraint mechanism is used to fit and fix the structure of the test piece.

[0008] Preferably, the first constraint mechanism includes a support assembly and at least two abutment members, the at least two abutment members being used to directly abut against two opposite sides of the test specimen in the thickness direction, and the support assembly being used to support the abutment members.

[0009] Preferably, the abutting member includes an abutting surface and a limiting surface. The abutting surface matches the shape of the abutting portion of the test piece, and the limiting surface cooperates with the support assembly to allow the abutting member to slide relative to the support assembly in the preset direction.

[0010] Preferably, the second constraint mechanism includes a first constraint connector and a first clamping assembly. The first constraint connector is used to connect to the end of the structure of the test piece. The first constraint connector is clamped by the first clamping assembly, and the first constraint connector can be displaced along the preset direction while being clamped by the first clamping assembly.

[0011] Preferably, the first constraint connector includes a T-shaped connector, one end of which is fixedly connected to the test specimen, and the other two opposite ends are clamped by the first clamping assembly.

[0012] Preferably, the third constraint mechanism includes a second constraint connector and a second clamping assembly. The second constraint connector is used to fit and connect with the structure of the test specimen. The second constraint connector is clamped by the second clamping assembly, and the second constraint connector can be displaced along the preset direction while being clamped by the second clamping assembly.

[0013] Preferably, the second constraint connector includes a first connecting portion and a second connecting portion, the first connecting portion is located at both ends of the second connecting portion, the second connecting portion is used to fit and fix with the test piece, and the second clamping assembly clamps the first connecting portion.

[0014] Preferably, there are two support frames, which are spaced apart. The test piece is placed between the two support frames, and the constraint mechanisms on the two support frames are symmetrically arranged to constrain the test piece.

[0015] Preferably, the test constraint device further includes an end constraint mechanism, which is disposed at one end of the two support frames along the preset direction.

[0016] Preferably, the end constraint mechanism includes a base and a third clamping assembly disposed on the base, the third clamping assembly being located between the two support frames and used to clamp one end of the test piece along the preset direction.

[0017] The beneficial effects of this utility model are:

[0018] The test constraint device provided by this utility model includes a support frame and constraint mechanisms mounted on the support frame. The constraint mechanisms include at least a first constraint mechanism, a second constraint mechanism, and a third constraint mechanism. These three mechanisms are respectively connected to different positions on the test piece, and the test piece can be displaced along a preset direction under the constraint of the constraint mechanisms. Specifically, the first constraint mechanism directly abuts against the structure of the test piece, the second constraint mechanism fixes the ends of the test piece structure, and the third constraint mechanism fits and fixes the test piece structure. The first constraint mechanism of this utility model can directly abut against the edge of the skin structure of the aircraft fuselage test piece, i.e., the free edge of the skin, to constrain it, preventing the free edge of the skin from displacing outwards. The second constraint mechanism fixes the ends of the ordinary frame in the aircraft fuselage test piece structure, preventing the test piece from displacing outwards from the skin surface or rotating around the extension direction of the stringer. Considering the connection between the docking frame and the spherical skin of the aircraft spherical frame in the test specimen structure, the web of the docking frame is supported out-of-plane by the spherical skin. Therefore, this invention also provides a third constraint mechanism to provide a close-fitting support constraint for the docking frame, while further preventing the docking frame from displacing outward in the skin direction or rotating around the extension direction of the stringer. Through the constraints of the first, second, and third constraint mechanisms on the test specimen, the out-of-plane displacement of the free edge of the skin, both ends of the ordinary frame, and the docking frame under compressive load can be accurately constrained simultaneously. This effectively solves the influence of boundary constraints on the test, provides multiple constraint forms to simulate real constraint conditions, reduces the sources of test error in the compression test of this type of composite material structure, and improves the accuracy and effectiveness of the test data. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the test constraint device and pressure block described in an embodiment of the present invention;

[0020] Figure 2 This is a schematic diagram of the structure of the test piece described in an embodiment of this utility model;

[0021] Figure 3 This is a schematic diagram of the assembly of the test constraint device and test piece according to an embodiment of the present invention;

[0022] Figure 4 This is a schematic diagram of the structure of the first constraint mechanism described in an embodiment of the present invention;

[0023] Figure 5 This is a schematic diagram of the structure of the second constraint mechanism described in an embodiment of the present invention;

[0024] Figure 6 This is a schematic diagram of the structure of the third constraint mechanism described in an embodiment of the present invention;

[0025] Figure 7 This is a schematic diagram of the end constraint mechanism described in an embodiment of the present invention.

[0026] In the picture:

[0027] 1. Support frame; 21. First constraint mechanism; 211. Support assembly; 2111. Support cutter head; 2112. Support base; 212. Abutment part; 2121. Abutment surface; 2122. Limiting surface; 22. Second constraint mechanism; 221. First constraint connector; 222. First clamping assembly; 23. Third constraint mechanism; 231. Second constraint connector; 2311. First connecting part; 2312. Second connecting part; 232. Second clamping assembly; 3. End constraint mechanism; 31. Base; 32. Third clamping assembly; 100. Test piece; 101. Skin; 102. Ordinary frame; 103. Butt frame; 200. Pressure block. Detailed Implementation

[0028] The embodiments of this utility model are described in detail below. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar parts or parts having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this utility model, and should not be construed as limiting this utility model.

[0029] In the description of this utility model, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection or a detachable connection; a mechanical connection or an electrical connection; a direct connection or an indirect connection through an intermediate medium; or the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0030] In the description of this utility model, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0031] The technical solution of this utility model will be further described below with reference to the accompanying drawings and specific embodiments.

[0032] like Figures 1 to 7 As shown, this utility model provides a test constraint device for performing compressive load tests on the structure at the connection between the mid- and rear fuselage of an aircraft.

[0033] For details, please refer to Figure 1 and Figure 2 The test constraint device provided by this utility model includes a support frame 1 and a constraint mechanism disposed on the support frame 1. The constraint mechanism includes at least a first constraint mechanism 21, a second constraint mechanism 22, and a third constraint mechanism 23. The first constraint mechanism 21, the second constraint mechanism 22, and the third constraint mechanism 23 are respectively connected to different positions of the test specimen 100, and the test specimen 100 can be displaced along a preset direction under the constraint of the constraint mechanism. It can be understood that the preset direction is the direction in which the test specimen 100 is compressed during the compressive load test. In this embodiment, the preset direction is the Z-axis direction.

[0034] Among them, reference Figure 1 , Figure 2 and Figure 3The first constraint mechanism 21 is used to directly abut against the edge of the structure of the test piece 100, the second constraint mechanism 22 is used to fix the end structure of the test piece 100, and the third constraint mechanism 23 is used to fit and fix the structure of the test piece 100. The first constraint mechanism 21 of this invention can directly abut against the opposite sides of the edge of the skin 101 structure of the aircraft fuselage structure test piece 100, that is, the free edge of the skin 101, to constrain it, preventing the free edge of the skin 101 from displacing in the outward direction (Y-axis direction). The second constraint mechanism 22 fixes the end of the ordinary frame 102 in the structure of the aircraft fuselage test piece 100, preventing the test piece 100 from displacing in the outward direction of the skin 101 or rotating around the extension direction (Z-axis direction) of the stringer (not shown in the figure). Considering the connection form between the docking frame 103 of the test piece 100 structure and the spherical skin of the aircraft spherical frame (not shown in the figure), the web of the docking frame 103 is supported out-of-plane by the spherical skin. Therefore, this utility model also provides a third constraint mechanism 23 to provide close support constraint for the docking frame 103, while further preventing the docking frame 103 from displacing out-of-plane in the skin 101 or rotating around the extension direction of the stringer. Through the constraint of the test piece 100 by the first constraint mechanism 21, the second constraint mechanism 22 and the third constraint mechanism 23, the out-of-plane displacement of the free edge of the skin 101, the two ends of the ordinary frame 102 and the docking frame 103 under compressive load can be accurately constrained simultaneously, effectively solving the influence of boundary constraints on the test, reducing the sources of test error for the compression test of this type of composite material structure, and improving the accuracy and effectiveness of test data. It is understood that accurately simulating the multiple out-of-plane support constraint states of the test piece 100 provides support for in-depth research on the connection performance between aircraft sections, and is of great significance for studying the connection performance of this type of composite material structure and ensuring the safety and reliability of the structure.

[0035] In some embodiments, such as Figure 4As shown, the first constraint mechanism 21 includes a support component 211 and at least two abutment members 212. The at least two abutment members 212 are used to directly abut against two opposite surfaces in the thickness direction of the test piece 100. The support component 211 supports the abutment members 212. In some specific embodiments, the abutment member 212 includes an abutment surface 2121 and a limiting surface 2122. The abutment surface 2121 matches the shape of the abutment portion of the test piece 100, and the limiting surface 2122 cooperates with the support component 211 to allow the abutment member 212 to slide relative to the support component 211 in a predetermined direction. It is understood that the abutment surface 2121 and the limiting surface 2122 of the abutment member 212 are opposite to each other, that is, the abutment surface 2121 and the limiting surface 2122 are two opposite surfaces of the abutment member 212. The contact surface 2121 directly contacts the skin 101 structure of the test piece 100. The limiting surface 2122 is set to match the shape of the support component 211, so that the contact part 212 and the test piece 100 are fully fitted together, and the relatively set contact part 212 maintains a stable contact and clamping of the test piece 100. Moreover, the cooperation between the limiting surface 2122 and the support component 211 also allows the contact part 212 to move along a preset direction under the constraint of the support component 211 while it is contacting the test piece 100.

[0036] In some optional embodiments, the limiting surface 2122 of the abutment 212 is V-shaped, forming a guide groove-like effect. The support assembly 211 includes a support blade 2111, which functions similarly to a guide rail. After installation, the support blade 2111 can cooperate with the V-shaped limiting surface 2122 to achieve the cooperation of a guide rail and a guide groove, so that the abutment 212 can only move in a preset direction under the restriction of the support blade 2111. The support assembly 211 may also include a support base 2112, on which the support blade 2111 is disposed. The support blade 2111 can be integrally formed with the support base 2112. The support base 2112 is detachably connected to the support frame 1, that is, the position of the support base 2112 on the support frame 1 is adjustable to be adaptively adjusted according to different parameters such as the thickness of the test piece 100, and the length of the support base 2112 or the support blade 2111 meets the travel distance of the test piece 100 during the compressive load test.

[0037] It is understood that multiple support components 211 of the first constraint mechanism 21 can be provided on the support frame 1. Multiple support components 211 are spaced apart on the support frame 1 along a preset direction and support the abutment 212. This can shorten the length of a single abutment 212. By using multiple spaced abutments 212, the surface curvature that may exist on the test piece 100 can be adapted to, so as to fully support the abutment 212 and the test piece 100, and ensure the constraint stability of the free edge of the skin 101 of the test piece 100.

[0038] In some embodiments, such as Figure 5 As shown, the second constraint mechanism 22 includes a first constraint connector 221 and a first clamping assembly 222. The first constraint connector 221 is used to connect to the end of the structure of the test specimen 100. The first constraint connector 221 is clamped by the first clamping assembly 222, and the first constraint connector 221 can be displaced in a preset direction while being clamped by the first clamping assembly 222. It can be understood that, in this embodiment, the first constraint connector 221 is specifically connected to both ends of the structure of the ordinary frame 102 on the test specimen 100. Through the clamping action of the first clamping assembly 222 on the first constraint connector 221, the first constraint connector 221 can be displaced in a preset direction, thus constraining the test specimen 100 without affecting the normal compressive load test.

[0039] In some specific embodiments, the first constraint connector 221 includes a T-shaped connector, one end of which is fixedly connected to the test specimen 100, while the other two opposite ends are clamped by the first clamping assembly 222. It is understood that by connecting the T-shaped connector to the end of the ordinary frame 102 of the test specimen 100, the ordinary frame 102 can be constrained, interference with other structures can be avoided, and the actual constraint conditions can be better simulated.

[0040] In some embodiments, such as Figure 6 As shown, the third constraint mechanism 23 includes a second constraint connector 231 and a second clamping assembly 232. The second constraint connector 231 is used to fit and connect with the structure of the test piece 100. The second constraint connector 231 is clamped by the second clamping assembly 232, and the second constraint connector 231 can be displaced in a preset direction while being clamped by the second clamping assembly 232. In this embodiment, the docking frame 103 of the test piece 100 structure is connected to the spherical skin of the aircraft spherical frame under actual connection conditions. The web of the docking frame 103 is supported by the out-of-plane support of the spherical skin. By setting a third constraint mechanism 23, the second constraint connector 231 is attached and fixed to the docking frame 103 of the test piece 100 along the length direction of the docking frame 103, and the attachment is along the full length, so as to provide out-of-plane support for the docking frame 103 and simulate the actual connection constraint conditions. Then, the second clamping component 232 is used to clamp the second constraint connector 231, so that the second constraint connector 231 can be displaced in a preset direction. While constraining the test piece 100, it will not affect the normal compression load test.

[0041] In some specific embodiments, reference continues to be made to Figure 6The second constraint connector 231 includes a first connecting portion 2311 and a second connecting portion 2312. The first connecting portion 2311 is located at both ends of the second connecting portion 2312. The second connecting portion 2312 is used to fit and fix the test piece 100 along its entire length. The second clamping assembly 232 clamps the first connecting portion 2311 located at both ends of the second connecting portion 2312. It can be understood that the first connecting portion 2311 is a polygonal block structure, such as a cube, cuboid, or other square piece, which is convenient for clamping. The second connecting portion 2312 is a long strip connector so as to fit and fix the docking frame 103 along its entire length.

[0042] Since the first constraint mechanism 21, the second constraint mechanism 22 and the third constraint mechanism 23 are connected to the test piece 100 at different positions, the first constraint mechanism 21 and the second constraint mechanism 22 and the third constraint mechanism 23 can be spaced apart in the thickness direction of the test piece 100 to better adapt to the installation position and connection position.

[0043] In some embodiments, such as Figure 1 and Figure 3 As shown, there are two support frames 1, spaced apart. The test piece 100 is positioned between the two support frames 1, and the constraint mechanisms on the two support frames 1 are symmetrically arranged to constrain the test piece 100. It can be understood that since the second constraint connector 231 is fully fitted with the mating frame 103 of the test piece 100, the second constraint mechanisms 22 on the two support frames 1 share a single second constraint connector 231.

[0044] In some embodiments, such as Figure 1 , Figure 3 and Figure 7 As shown, the test constraint device also includes an end constraint mechanism 3, which is disposed at one end of the two support frames 1 along a preset direction to constrain one end of the test piece 100 along the preset direction and prevent out-of-plane displacement of the filling end skin 101 of the test piece 100. The end constraint mechanism 3 includes a base 31 and a third clamping assembly 32 disposed on the base 31. The third clamping assembly 32 is located between the two support frames 1 and is used to clamp one end of the test piece 100 along the preset direction. It can be understood that by setting the end constraint mechanism 3, the pressure block 200 and the end constraint mechanism 3 work together to apply pressure to the test piece 100 between them.

[0045] In some specific embodiments, the first clamping assembly 222, the second clamping assembly 232, and the third clamping assembly 32 are all clamping bars spaced apart. The clamping of the constraint connector or test piece 100 is achieved by adjusting the spacing between the clamping bars. The support frame 1 is provided with multiple mounting holes, and each constraint mechanism is also provided with mounting holes. Connection, fixation, and position adjustment are achieved by bolts passing through the mounting holes of both. Alternatively, the support frame 1 can be directly and spaced apart on the base 31 to improve structural stability. In some optional embodiments, the support frame 1 is also provided with connecting flanges (not shown in the figure) for connection to an external test platform.

[0046] Reference Figures 1 to 7 When using the test constraint device of this utility model, first connect the free edges and lower sealing ends of the left and right sides of the skin 101 to the test constraint device, then connect the left and right ends of the ordinary frame 102 to the test constraint device, and finally connect the docking frame 103 to the test constraint device.

[0047] For details, please refer to Figures 1 to 3 When connecting the free edges on both sides (X-axis direction) of the skin 101 and the lower potting end (the potting end in the downward direction of the Z-axis) to the test constraint device, first align the lower potting end of the test piece 100 and place it into the groove of the lower end constraint mechanism 3 to constrain the out-of-plane displacement of the potting end skin 101. Then, align the skin 101 of the test piece 100 and place it into the groove formed by the support component 211 of the first constraint mechanism 21 on the support frame 1. The abutment member 212 directly contacts the skin 101 to prevent the skin 101 from displacing out-of-plane and to prevent the skin 101 from rotating around the extension direction of the stringer (not shown in the figure). Figure 1 As shown, the stringer extends in the Z direction.

[0048] When connecting the left and right ends of the ordinary frame 102 to the test constraint device, the T-shaped connector is connected to the web of the ordinary frame 102 by bolts. The T-shaped connector is clamped by clamping strips to constrain it, thereby constraining the two ends of the ordinary frame 102. This restricts the out-of-plane (Y-axis) displacement of the skin 101 of the T-shaped connector and restricts its rotation around the extension direction of the stringer (rotation around the Z-axis), while releasing the movement in the loading direction (Z-axis).

[0049] When connecting the docking frame 103 to the test constraint device, the docking frame 103 is connected to the elongated second connecting constraint member along its full length by bolts. That is, the second connecting part 2312 of the second connecting constraint member is provided with multiple mounting holes, and the second connecting part 2312 is fixed to the docking frame 103 by bolts. The first connecting parts 2311 at both ends of the second constraint connecting member 231 are clamped by the second clamping assembly 232 for constraint, so as to not only restrict the out-of-plane displacement (Y-axis direction) and rotation around the stringer direction (rotation around the Z-axis direction) of the connecting block, but also simulate the supporting effect of the docking frame 103 when the entire web is connected to other structures in a real installation environment.

[0050] After installation, the pressure block 200, located above the test constraint device, applies pressure to the test piece 100 to conduct a compressive load test.

[0051] Understandably, when this test constraint device is used for compressive load tests on the structure connecting the middle and rear fuselage of an aircraft, it can simultaneously and accurately constrain the out-of-plane displacement of the free edge of the skin 101, both ends of the ordinary frame 102, and the docking frame 103 under compressive load. This effectively solves the influence of boundary constraints on the test, reduces the sources of test error for the compression test of this type of composite material structure, and improves the accuracy and effectiveness of the test data.

[0052] Obviously, the above embodiments of this utility model are merely examples for clearly illustrating the present utility model, and are not intended to limit the implementation of the present utility model. Those skilled in the art can make other variations or modifications based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this utility model should be included within the protection scope of the claims of this utility model.

Claims

1. A test constraint device, characterized in that, The device includes a support frame (1) and a constraint mechanism disposed on the support frame (1). The constraint mechanism includes at least a first constraint mechanism (21), a second constraint mechanism (22), and a third constraint mechanism (23). The first constraint mechanism (21), the second constraint mechanism (22), and the third constraint mechanism (23) are used to connect to different positions of the test piece (100) respectively, and the test piece (100) can be displaced along a preset direction under the constraint of the constraint mechanism. The first constraint mechanism (21) is used to directly abut against the structure of the test piece (100), the second constraint mechanism (22) is used to fix the end of the structure of the test piece (100), and the third constraint mechanism (23) is used to fit and fix the structure of the test piece (100).

2. The test constraint device according to claim 1, characterized in that, The first constraint mechanism (21) includes a support assembly (211) and at least two abutments (212), the at least two abutments (212) being used to directly abut against two opposite sides of the test piece (100) in the thickness direction, and the support assembly (211) being used to support the abutments (212).

3. The test constraint device according to claim 2, characterized in that, The abutment (212) includes an abutment surface (2121) and a limiting surface (2122). The abutment surface (2121) matches the shape of the abutment portion of the test piece (100). The limiting surface (2122) cooperates with the support component (211) so that the abutment (212) can slide relative to the support component (211) in the preset direction.

4. The test constraint device according to claim 1, characterized in that, The second constraint mechanism (22) includes a first constraint connector (221) and a first clamping assembly (222). The first constraint connector (221) is used to connect to the end of the structure of the test piece (100). The first constraint connector (221) is clamped by the first clamping assembly (222), and the first constraint connector (221) can be displaced along the preset direction while being clamped by the first clamping assembly (222).

5. The test constraint device according to claim 4, characterized in that, The first constraint mechanism (21) includes a T-shaped connector, one end of which is fixedly connected to the test piece (100), and the other two opposite ends are clamped by the first clamping assembly (222).

6. The test constraint device according to claim 1, characterized in that, The third constraint mechanism (23) includes a second constraint connector (231) and a second clamping assembly (232). The second constraint connector (231) is used to fit and connect with the structure of the test piece (100). The second constraint connector (231) is clamped by the second clamping assembly (232), and the second constraint connector (231) can be displaced along the preset direction while being clamped by the second clamping assembly (232).

7. The test constraint device according to claim 6, characterized in that, The second constraint connector (231) includes a first connecting part (2311) and a second connecting part (2312). The first connecting part (2311) is located at both ends of the second connecting part (2312). The second connecting part (2312) is used to fit and fix with the test piece (100). The second clamping assembly (232) clamps the first connecting part (2311).

8. The test constraint device according to any one of claims 1-7, characterized in that, There are two support frames (1), which are spaced apart. The test piece (100) is placed between the two support frames (1). The constraint mechanisms on the two support frames (1) are symmetrically arranged to constrain the test piece (100).

9. The test constraint device according to claim 8, characterized in that, The test constraint device further includes an end constraint mechanism (3), which is disposed at one end of the two support frames (1) along the preset direction.

10. The test constraint device according to claim 9, characterized in that, The end constraint mechanism (3) includes a base (31) and a third clamping assembly (32) disposed on the base (31). The third clamping assembly (32) is located between the two support frames (1) and is used to clamp one end of the test piece (100) along the preset direction.

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