Civil aircraft wing root large-size wall plate butt joint structure test device and test method

Abstract

The application discloses a civil aircraft wing root large-size wall plate butt joint structure test device and a test method. The test device comprises a test piece, a support component and two connecting assemblies. The test piece has an outer wing side wall plate and a central wing side wall plate. The two connecting assemblies are clamped on the outer wing side wall plate and the central wing side wall plate of the test piece respectively, and the two connecting assemblies are connected to two chucks of a test machine respectively. The support component supports any one of the connecting assemblies to level the two connecting assemblies. The test device of the application can level the two connecting assemblies by adding the support component, reduces the influence of the gap and assembly error on the test, and guarantees the loading centration of the large-size test piece. The application solves the problems of misalignment and uneven stress distribution in the test process of the large-size wall plate butt joint structure, and can more accurately simulate the stress state of the wing root large-size wall plate butt joint structure.

Description

Technical Field

[0001] This invention relates to the field of testing technology for large-size panel joint structures at the wing root of aircraft, and particularly to a testing device and method for testing large-size panel joint structures at the wing root of civil aircraft. Background Technology

[0002] Currently, advanced civil aircraft wing root connection areas contain numerous complex composite stiffened panel buttress structures, which are the main load-bearing structures of the aircraft, exhibiting complex connection relationships. Under flight loads, the critical connection area at the wing root is subjected to tensile loads. To verify the load-bearing performance of large-size panel buttress structures in the critical connection area of ​​the wing root and the relevant numerical analysis methods, experimental verification research is required.

[0003] During testing, the testing machine is typically connected to the test piece via connecting components. However, for large-sized test pieces, uneven stress distribution is prone to occur due to unreasonable clamping and loading schemes. At the same time, connecting components inevitably have hole position errors and assembly errors, which cannot guarantee that the test piece is under correct tension and cannot guarantee the centering of the loading of large-sized wall panel butt joint structure test pieces at the wing root, thus leading to inaccurate test data. Summary of the Invention

[0004] This invention provides a test device and test method for the large-size panel docking structure of civil aircraft wing root, which solves the problems of misalignment and uneven stress distribution in the test process of large-size panel docking structure, and can more accurately simulate the stress state of the large-size panel docking structure of wing root.

[0005] To achieve the above-mentioned objectives, this application provides the following technical solution:

[0006] The primary objective of this application is to provide a test apparatus for the joint structure of large-size panel at the wing root of a civil aircraft, comprising:

[0007] The test piece has an outer wing sidewall panel and a central wing sidewall panel;

[0008] Two connecting components are respectively clamped to the outer wing sidewall and the central wing sidewall of the test piece, and the two connecting components are respectively connected to the two clamps of the testing machine;

[0009] A support member, which supports either of the connecting components to level the two connecting components.

[0010] Optionally, the connecting assembly includes a clamping assembly and a clamping connector. The clamping assembly clamps the outer wing sidewall or the central wing sidewall of the test piece, and the clamping connector is respectively hinged to the clamping assembly and the chuck of the testing machine.

[0011] The support component is supported on any of the clamping joints.

[0012] Optionally, the clamping joint has a support mating surface perpendicular to the test piece;

[0013] The support component is supported on the support mating surface.

[0014] Optionally, a support mating groove is provided on the support mating surface;

[0015] The end of the support component extends into the support mating groove.

[0016] Optionally, the test device for the large-size panel docking structure of the wing root of a civil aircraft includes two support components, which are respectively connected to the support mating surfaces of two clamping joints;

[0017] The support component has an extended state and a retracted state.

[0018] Optionally, the support component is a single piece, and the support component can be selectively supported on the support mating surface of any clamping joint.

[0019] Optionally, the civil aircraft wing root large-size panel docking structure test device also includes a base frame, the support component is connected to the base frame, and the support component can move and be positioned along the base frame.

[0020] Optionally, the support component has a main body and a telescopic part;

[0021] The telescopic part is movably connected to the main body, and the telescopic part can extend and retract along the main body and be fixed, with the end of the telescopic part abutting against the connecting assembly.

[0022] Optionally, the clamping assembly includes a transition joint and a clamping plate assembly. The clamping plate assembly clamps both sides of the outer wing sidewall or the central wing sidewall in the thickness direction. One end of the transition joint is provided with multiple connecting holes, and the other end is provided with a loading hole. All the connecting holes are located on the same straight line, and the loading hole is located on the perpendicular bisector of the line segment formed by the lines connecting the connecting holes. Each connecting hole is connected to the clamping plate assembly through a connecting pin of the transition joint, and the loading hole is connected to the clamping joint through a loading shaft.

[0023] The second objective of this application is to provide a test method for the above-mentioned test device for the large-size panel docking structure of the wing root of a civil aircraft, including: determining the eccentricity distance D of the test device, supporting the support component on one side of the lower connecting component, and adjusting the height of the support component so that the support component lifts the corresponding connecting component to the height corresponding to the eccentricity distance D.

[0024] Optionally, the eccentricity distance D is estimated using the following formula:

[0025]

[0026] Where E is the elastic modulus, I z Let ε be the moment of inertia, F be the pre-experimental applied force, and ε be the moment of inertia. test1 ε is the pre-test value at the first strain measurement point a. test2 y1 is the pre-test value of the second strain measuring point b, y2 is the distance of the first strain measuring point a from the neutral axis of the side of the test piece, and y3 is the distance of the second strain measuring point b from the neutral axis of the side of the test piece.

[0027] By adopting the above technical solution, this application has the following beneficial effects:

[0028] The test apparatus of this application, by adding supporting components and adjusting the connecting assemblies on both sides, reduces the impact of gaps and assembly errors on the test, ensuring the centering of the large-size test piece under load. This application solves the problems of misalignment and uneven stress distribution in the test of large-size wall panel butt structures, and can more accurately simulate the stress state of large-size wall panel butt structures at the wing root. Attached Figure Description

[0029] The accompanying drawings, which form part of this application, are provided to further illustrate the invention. The illustrative embodiments and descriptions of the invention are used to explain the invention but do not constitute an undue limitation thereof. Clearly, the drawings described below are merely some embodiments, and those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0030] Figure 1 A three-dimensional structural schematic diagram of the test piece of the civil aircraft wing root large-size panel docking structure test device provided in the embodiments of this application;

[0031] Figure 2 Another perspective view of the test specimen of the civil aircraft wing root large-size panel docking structure test device provided in the embodiments of this application;

[0032] Figure 3 A schematic diagram of the civil aircraft wing root large-size panel docking structure test device in the test state provided in the embodiments of this application;

[0033] Figure 4 A front view of the civil aircraft wing root large-size panel docking structure test device provided in the embodiment of this application in the test state;

[0034] Figure 5 A top view of the civil aircraft wing root large-size panel docking structure test device provided in the embodiment of this application, in the test state;

[0035] Figure 6A schematic diagram of the first side clamping plate of the civil aircraft wing root large-size panel docking structure test device provided in the embodiments of this application;

[0036] Figure 7 A schematic diagram of the transition joint of the test device for the large-size panel butt joint structure of the wing root of a civil aircraft provided in this application embodiment;

[0037] Figure 8 A schematic diagram of the clamping joint of the test device for the large-size panel butt joint structure of the wing root of a civil aircraft provided in this application embodiment;

[0038] Figure 9 A schematic diagram of the transition joint connecting pin of the civil aircraft wing root large-size panel butt joint structure test device provided in this application embodiment;

[0039] Figure 10 A schematic diagram of the supporting components of the test device for the large-size panel docking structure of the wing root of a civil aircraft provided in the embodiments of this application;

[0040] Figure 11 A partial exploded view of the test device for the large-size panel docking structure of the wing root of a civil aircraft provided in the embodiments of this application;

[0041] Figure 12 This is a schematic diagram of the test load application method of the test device for the large-size panel butt joint structure of the wing root of a civil aircraft provided in the embodiments of this application;

[0042] Figure 13 A schematic diagram of the off-axis force state of the test piece of the civil aircraft wing root large-size panel docking structure test device provided in the embodiments of this application.

[0043] In the figure: 1. Test piece; 11. Outer wing sidewall panel; 12. Central wing sidewall panel; 13. Inner T-shaped mating strip plate; 14. Outer connecting strip plate; 2. Clamping joint; 21. Support mating surface; 3. Loading shaft; 4. Transition joint; 41. Loading hole; 42. Connecting hole; 5. Transition joint connecting pin; 6. First side clamping plate; 7. Second side clamping plate; 8. Clamping plate connecting pin; 9. Clamping head of the testing machine; 10. Support component; a. First strain measuring point; b. Second strain measuring point. Detailed Implementation

[0044] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments will be clearly and completely described below with reference to the accompanying drawings. The following embodiments are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0045] In the description of this invention, it should be noted that the terms "upper", "lower", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0046] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation" and "connection" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0047] Example 1

[0048] See Figures 1 to 13 As shown, Embodiment 1 of this application provides a test device for the docking structure of a large-size panel at the wing root of a civil aircraft, comprising: a test piece 1, a support component 10, and two connecting assemblies. The test piece 1 has an outer wing side panel 11 and a central wing side panel 12. The two connecting assemblies are respectively clamped to the outer wing side panel 11 and the central wing side panel 12 of the test piece, and the two connecting assemblies are respectively connected to two clamps 9 of the testing machine. The support component 10 supports either of the connecting assemblies to level the two connecting assemblies.

[0049] During the test, two connecting components are used to clamp the test piece 1 at both ends. However, the connecting components inevitably have errors in hole position and assembly, which cannot guarantee that the test piece 1 is in a horizontal tensile state and cannot guarantee the centering of the large-size wall panel butt structure test piece 1 under load. To address this, in this embodiment, a support component 10 is designed to support the lower connecting component, leveling the two connecting components, reducing the impact of gaps and assembly errors, ensuring the centering of the large-size wall panel butt structure test piece 1 under load, and improving the accuracy of the test.

[0050] See Figure 1 and Figure 2As shown in the embodiments of this application, the selected test piece 1 can be a large-size structure. Test piece 1 can be composed of an inner T-shaped docking strip 13, an outer wing sidewall panel 11 (including skin and stringers), a central wing sidewall panel 12 (including skin and stringers), an outer connecting strip 14, and connecting bolts. The configuration of this test piece 1 is a large-size wing panel docking structure, characterized by high ultimate load and large size. Its static test belongs to the large-scale test of composite material details, which can more accurately verify the load-bearing capacity of the large-size panel docking structure in the wing root connection area, and provides important experimental data support for the design and selection of wing root docking structures and finite element analysis methods.

[0051] In one possible implementation, the connecting assembly includes a clamping assembly and a clamping connector 2. The clamping assembly clamps the outer wing sidewall 11 or the central wing sidewall 12 of the test specimen 1. The clamping connector 2 is hinged to the clamping assembly and the chuck 9 of the testing machine, respectively. The supporting member 10 is supported on either of the clamping connectors 2.

[0052] In this embodiment, the clamping connector 2 is directly supported by the chuck 9 of the testing machine, which is the end position of the connecting assembly. The supporting component 10 directly applies a supporting force to the clamping connector 2, which is more conducive to leveling the entire connecting assembly. This ensures that all components of the two connecting assemblies are on the same horizontal line.

[0053] During the experiment, test piece 1 was subjected to a horizontal loading method. Test piece 1 is a long plate. Test piece 1 is fixed laterally, and the plane containing test piece 1 is perpendicular to the horizontal plane. The chuck 9 of the testing machine has an upper support arm and a lower support arm. The clamping joint 2 has a through hole extending longitudinally. The clamping joint 2 partially extends between the upper and lower support arms. A rotating shaft passes through the upper support arm, the lower support arm, and the through hole. The support component 10 is parallel to the rotating shaft and abuts against the clamping joint 2. Adjusting the height of the clamping joint 2, the vertically extending rotating shaft provides a certain guiding effect, which helps the support component 10 to effectively raise the lower-positioned connecting components to the required height.

[0054] In one possible implementation, both clamping joints 2 have a support mating surface 21 perpendicular to the test piece 1, and the support member 10 is supported on the support mating surface 21. In this implementation, the support mating surface 21 is one side of the lower surface of the clamping joint 2 in the test state, which can effectively lift the clamping joint 2 to a certain height.

[0055] In one possible implementation, a support groove is provided on the support mating surface 21, and the end of the support member 10 extends into the support groove. By providing a support groove on the support mating surface 21, the top of the support member 10 is confined within the support groove, preventing the support member 10 from changing position during the experiment. Furthermore, by providing a support groove on the support mating surface 21, the support position of the support member 10 is well defined, improving experimental accuracy and facilitating rapid assembly of the support member 10.

[0056] In one possible implementation, the test device for the large-size panel mating structure of the wing root of a civil aircraft may include two support components 10, which are respectively connected to the support mating surfaces 21 of two clamping joints 2. The support components 10 have an extended state and a retracted state.

[0057] In this implementation scheme, support components 10 are installed on both sides of the connecting assembly. The support components 10 are perpendicular to the supporting mating surface 21 and are telescopic and positionable. The experimenter can adjust the telescopic length of the support components 10 and fix them in place. During actual testing, only one of the two support components 10 is used. The support component 10 on the lower connecting assembly extends to support the corresponding clamping joint 2, while the support component 10 on the higher connecting assembly remains retracted.

[0058] The end of the support component 10 can be fixed to the clamping connector 2. A connecting seat can be provided on the clamping connector 2, and the end of the support component 10 is connected to the connecting seat. The support component 10 is detachable for easy replacement and maintenance.

[0059] In another possible implementation, the support component 10 is a single piece, which can be selectively supported on the support mating surface 21 of any clamping connector 2. In this implementation, the support component 10 is a separate accessory structure, convenient for individual storage. The experimenter can manually place the retracted support component 10 at the target position and then control its extension so that its top end abuts against the support mating surface 21. The clamping connector 2 also applies a downward force to the telescopic component, keeping the support component 10 vertical and preventing it from wobbling or tilting.

[0060] In one possible implementation, the civil aircraft wing root large-size panel docking structure test device further includes a base frame, the support component 10 is connected to the base frame, and the support component 10 can move and be positioned along the base frame.

[0061] In this embodiment, the base frame can be installed on the base platform, with the base frame located directly below the test specimen 1 and extending parallel to the test specimen 1. The position of the support component 10 can be adjusted by sliding the support component 10, such as supporting it on the clamping joint 2 of different connecting components, or supporting it at different positions on the support mating surface 21.

[0062] The base frame may include a slide rail, and the support component 10 can be slidably connected to the slide rail. The support component 10 can be moved along the slide rail to adjust its position. Multiple threaded holes can be provided on the slide rail along its length. After the position of the support component 10 is adjusted, bolts are threadedly connected to the corresponding threaded holes at the position of the support component 10. Tightening the bolts will abut against the support component 10, thus fixing its position. Alternatively, the support component 10 may not require bolt fixation; its position can be maintained solely by the pressure applied by the connecting assembly.

[0063] The base frame may also include a lead screw mechanism, which includes a lead screw and a guide rod. The support component 10 may be threaded to the lead screw, and the support component 10 may be sleeved on the guide rod through a through hole. The position of the support component 10 can be adjusted by driving the lead screw to rotate.

[0064] In one possible implementation, the support member 10 has a main body and a telescopic portion. The telescopic portion is movably connected to the main body, can extend and retract along the main body and is fixed, and its end abuts against the connecting assembly.

[0065] The support component 10 can be a telescopic hydraulic cylinder, a telescopic air cylinder, a linear motor, or other telescopic mechanism. When the support component 10 is a telescopic hydraulic cylinder, the cylinder body of the telescopic hydraulic cylinder is the main body, and the telescopic rod of the telescopic hydraulic cylinder is the telescopic part.

[0066] In one possible implementation, see Figure 11 As shown, the clamping assembly includes a transition joint 4 and clamping plate assemblies 6 and 7. The clamping plate assemblies clamp the outer wing sidewall panel 11 or the central wing sidewall panel 12 on both sides in the thickness direction. Multiple clamping plate connecting pins 8 penetrate and connect the test piece 1 to the clamping plate assemblies. See also... Figure 7 As shown, the transition joint 4 has multiple connecting holes 42 at one end and a loading hole 41 at the other end. The connecting holes 42 are located on the same straight line, and the loading hole 41 is located on the perpendicular bisector of the line segment formed by the connecting holes 42. Each connecting hole 42 is connected to the clamping plate assembly through the transition joint connecting pin 5, and the loading hole 41 is connected to the clamping joint 2 through the loading shaft 3.

[0067] In this embodiment, the extending direction of the loading hole 41 is perpendicular to the extending direction of the through hole. The number of connecting holes 42 can be three or determined according to the actual size of the test piece.

[0068] During the test, due to the large size of the test piece 1, in order to minimize the uneven loading caused by loading, the transition joint 4 structure was designed. The end of the transition joint 4 near the test piece 1 is connected to the clamping plate assembly through multiple transition joint connecting pins 5, while the other end of the transition joint 4 is connected to the clamping joint 2 through only one loading shaft 3. This distributes the force output by the loading shaft 3 evenly to different positions of the test piece 1, reducing the uneven stress and strain distribution inside the test piece caused by the concentration of loading force, and realizing uniform loading of the large-size wall panel butt structure test piece 1.

[0069] Example 2

[0070] This application provides a test method for the test device for the large-size panel docking structure of the wing root of a civil aircraft in the above embodiment one, including: determining the eccentric distance D of the test device, supporting the support component 10 on one side of the lower connecting component, and adjusting the height of the support component 10 so that the support component 10 lifts the corresponding connecting component to the height corresponding to the eccentric distance D.

[0071] Optionally, the eccentricity distance D is estimated using the following formula:

[0072]

[0073] Where E is the elastic modulus, I z Let ε be the moment of inertia, F be the pre-experimental applied force, and ε be the moment of inertia. test1 ε is the pre-test value at the first strain measurement point a. test2 y1 represents the pre-test value of the second strain measuring point b, y2 represents the distance of the first strain measuring point a from the neutral axis of the side of the test piece, and y3 represents the distance of the second strain measuring point b from the neutral axis of the side of the test piece. The first strain measuring point a and the second strain measuring point b are symmetrically distributed on both sides of the test piece 1 along the width direction.

[0074] In the specific structure, the clamping plate assembly has a first side clamping plate 6 and a second side clamping plate 7, which are located on both sides of the outer wing side wall panel 11 or the central wing side wall panel 12. Multiple fixing holes are provided on the first side clamping plate 6 and the second side clamping plate 7 to connect with corresponding parts of the large-size test piece 1 via clamping plate connecting pins 8. The transition joint 4 has a clamping groove, and the end of the clamping plate assembly is inserted into the clamping groove. Each connecting hole 42 passes through the transition joint 4, and multiple transition joint connecting pins 5 pass through the corresponding connecting holes 42 and the clamping plate assembly. The loading shaft 3 of the transition joint 4 is connected to the clamping joint 2. During the test, the position of the movable support component 10 can be adjusted according to the test conditions so that it abuts against the lower side of the clamping joint 2.

[0075] according to Figure 12The loading method shown applies mechanical load to the large-size wall panel butt joint structure test specimen 1. Due to machining and assembly tolerances of the large-size wall panel butt joint structure test specimen 1, transition joint 4, transition joint connecting pin 5, and loading shaft 3, the test specimen 1 subjected to horizontal loading has a situation where the loading shaft 3 on the central wing side and the outer wing side are not on the same horizontal line. During the test, in order to maintain the test specimen 1 in a horizontal loaded state, a support component 10 is used to lift the lower side of the test specimen 1, such as... Figure 12 Meanwhile, to ensure a more uniform stress distribution on test specimen 1, the test load F was... jz Decomposed into F via transition joint 4 x1 F x2 F x3 The calculation formula is as follows:

[0076]

[0077] Meanwhile, since the loading axes 3 on the central wing side and the outer wing side are not on the same horizontal line, the material is subjected to off-axis tension, and its stress state can be simplified as follows: Figure 13 At the symmetrical first strain measuring point a and the second strain measuring point b, the strain ε is caused by the applied force F. F The strain ε caused by the bending moment M = F·D (where D is the eccentricity) due to eccentricity. M It consists of two parts, as follows:

[0078]

[0079]

[0080] Where A is the area of ​​the longitudinal section corresponding to the first strain measurement point a to the second strain measurement point b, E is the elastic modulus, and I... z Let y be the moment of inertia, and y be the distance from the strain measuring point to the neutral axis of the side of the test specimen.

[0081] The strain at the first strain measurement point a is ε1=ε F +ε M The strain at the second strain measuring point b is ε2=ε F -ε M The strain test results ε at the first strain measuring point a and the second strain measuring point b can be obtained through preliminary experiments. test1 and ε test2 Substituting these values ​​into the above equation, the eccentricity distance D can be estimated as follows:

[0082]

[0083] As can be seen from the above analysis, the support component 10 is used to lift the test piece 1 to a height of D. The support component 10 is used to balance the positional errors and assembly errors of the loading shaft 3, the transition joint connecting pin 5, and the connecting holes 42 of the transition joint, so as to ensure that the test piece 1 is in a horizontal tensile state.

[0084] To ensure experimental safety, the testing apparatus was strength-calibrated to withstand 2-3 times the estimated failure load. To guarantee the strength of the transition joint connecting pin and the loading shaft, the loading shaft 3 was made of alloy steel, and the transition joint connecting pin was made of ultra-high-strength steel. Strain gauges were attached to the test area of ​​test piece 1 to record experimental data. To obtain more accurate experimental data, strain gauges were attached to the bypass load locations of the fasteners connecting the large-size wall panel butt joint structure.

[0085] The following provides an exemplary sequence for static testing of a large-size test specimen 1 with a butt joint structure:

[0086] (1) Pre-test: Load the load gradually from 5% to 30% failure load, and unload it gradually from 10% failure load. Examine the stress condition of test piece 1 and the operation of the fixture, loading equipment and measuring instruments.

[0087] (2) Load the load in increments of 5% of the failure load up to 65% of the failure load;

[0088] (3) Load the load to 67% failure load in increments of 2% and maintain the load until data recording is completed;

[0089] (4) Load the load to 70% failure load in increments of 3% failure load, and maintain the load until data recording is completed;

[0090] (5) After loading the load to 100% failure load at 5% failure load increments, hold the load for 3 seconds and hold the load until data recording is complete;

[0091] (6) If there is no failure, continue to increase the failure load by 5% per level and keep the load until the data recording is completed, until failure occurs; if the test specimen 1 is not damaged when the load is increased to 120% failure load, stop loading.

[0092] The experimental setup has been verified in the laboratory and has obtained ideal experimental results, proving the effectiveness of the experimental setup.

[0093] The preferred embodiments disclosed above are merely illustrative of this application. These preferred embodiments do not exhaustively describe all details, nor do they limit the application to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of this application, thereby enabling those skilled in the art to better understand and utilize this application. This application is limited only by the claims and their full scope and equivalents.

Claims

1. A test device for the docking structure of large-size wall panels at the wing root of a civil aircraft, characterized in that, include: The test piece has an outer wing sidewall panel and a central wing sidewall panel; Two connecting components are respectively clamped to the outer wing sidewall and the central wing sidewall of the test piece, and the two connecting components are respectively connected to the two clamps of the testing machine; A support member, which supports either of the connecting components to level the two connecting components; The connecting assembly includes a clamping assembly and a clamping connector. The clamping assembly clamps the outer wing sidewall or the central wing sidewall of the test piece. The clamping connector is respectively hinged to the clamping assembly and the chuck of the testing machine. The supporting component is supported on any of the clamping connectors. The clamping joint has a support mating surface perpendicular to the test piece, and the support component is supported on the support mating surface; A support groove is provided on the support mating surface, and the end of the support component extends into the support groove; The chuck of the testing machine has an upper support arm and a lower support arm. The clamping joint has a through hole extending longitudinally. The clamping joint part extends between the upper support arm and the lower support arm. The rotating shaft passes through the upper support arm, the lower support arm and the through hole. The supporting component is parallel to the rotating shaft and abuts against the clamping joint. The height of the clamping joint can be adjusted. The clamping assembly includes a transition joint and a clamping plate assembly. The clamping plate assembly clamps both sides of the outer wing sidewall or the central wing sidewall in the thickness direction. One end of the transition joint is provided with multiple connecting holes, and the other end is provided with a loading hole. All the connecting holes are located on the same straight line, and the loading hole is located on the perpendicular bisector of the line segment formed by the lines connecting the connecting holes. Each connecting hole is connected to the clamping plate assembly through a connecting pin of the transition joint. The loading hole is connected to the clamping joint through a loading shaft, and the loading shaft is perpendicular to the support component.

2. The test device for the large-size panel butt joint structure of civil aircraft wing root as described in claim 1, characterized in that, It includes two support components, which are respectively connected to the support mating surfaces of two clamping joints; The support component has an extended state and a retracted state.

3. The test device for the large-size panel butt joint structure of civil aircraft wing root as described in claim 1, characterized in that, The support component is a single piece, and it can be selectively supported on the support mating surface of any clamping joint.

4. The test device for the large-size panel butt joint structure of civil aircraft wing root as described in claim 1, characterized in that, It also includes a base frame, to which the support component is connected, and the support component is movable and positioned along the base frame.

5. The test device for the large-size panel butt joint structure of civil aircraft wing root according to claim 1, characterized in that, The supporting component has a main body and a telescopic part; The telescopic part is movably connected to the main body, and the telescopic part can extend and retract along the main body and be fixed, with the end of the telescopic part abutting against the connecting assembly.

6. A test method using the test apparatus for the large-size panel butt joint structure of the wing root of a civil aircraft as described in any one of claims 1-5, characterized in that, include: Determine the eccentricity D of the test device, support the supporting component on the side of the lower connecting component, and adjust the height of the supporting component so that the supporting component lifts the corresponding connecting component to the height corresponding to the eccentricity D.

7. The test method according to claim 6, characterized in that, The eccentricity D is estimated using the following formula: Where E is the elastic modulus, I z Let ε be the moment of inertia, F be the pre-test loading force, and ε be the moment of inertia. test1 ε is the pre-test value at the first strain measurement point a. test2 y1 is the pre-test value of the second strain measuring point b, y2 is the distance of the first strain measuring point a from the neutral axis of the side of the test piece, and y3 is the distance of the second strain measuring point b from the neutral axis of the side of the test piece.

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