Aircraft main landing gear fatigue detection device

Abstract

The utility model discloses an aircraft main landing gear fatigue detection device, which comprises a bearing platform, a supporting assembly is arranged above the bearing platform, a detection platform and a lifting assembly are arranged at the top of the supporting assembly, and a detection assembly is arranged on one side, above the detection platform, of the lifting assembly. According to the utility model, the design structure is reasonable, a plurality of first supporting columns and second supporting columns are respectively arranged on the bearing platform, and a plurality of mounting holes are formed in the first supporting columns and the second supporting columns; then the space between the first supporting columns and the second supporting columns is adjusted to adjust the unfolding area of the first supporting columns and the second supporting columns, and then detection tables of different sizes are installed, so that loads are conveniently applied to undercarriages of different sizes for carrying out sexual simulation detection, and the problems that the size of an existing platform for placing the undercarriages is inconvenient to adjust, and the working efficiency is high are solved. And the application range of the detection device is influenced.

Description

Technical Field

[0001] This utility model relates to the field of aircraft landing gear fatigue detection technology, specifically an aircraft main landing gear fatigue detection device. Background Technology

[0002] Fatigue cracks in aircraft main landing gear are usually repaired using cold spray technology. However, in order to test the effectiveness of cold spray repair, it is usually necessary to conduct simulated tests on the repaired landing gear to evaluate the improvement of cold spray technology and the fatigue performance after repair.

[0003] Chinese invention patent CN112461648B discloses a test device for fatigue performance testing of aircraft landing gear samples. This device applies loads in both horizontal and vertical directions and precisely controls the tensile or propulsive amounts for simulated testing. In the vertical direction, a lifting mechanism drives a lifting plate to press the sample vertically, applying a load to the sample. Metallographic testing is then used to assess fatigue strength. However, while different counterweights can be used to test samples of different sizes, the platform size below the counterweights is fixed, making it difficult to adjust according to the landing gear size. When the test sample is small and the platform is large, operation is inconvenient; conversely, a small platform makes it difficult to test larger landing gears, thus limiting the device's applicability. Utility Model Content

[0004] The purpose of this invention is to overcome the shortcomings of the existing technology and provide a fatigue detection device for aircraft main landing gear.

[0005] To achieve the above objectives, this utility model provides the following technical solution:

[0006] A fatigue testing device for aircraft main landing gear includes a platform, on which a support assembly, a testing platform, a lifting assembly, and a testing component are respectively arranged. The lifting assembly is installed on top of the support assembly, which includes several horizontally arranged first and second support columns, both of which are slidably connected to the top of the platform. The first and second support columns are of the same length and are staggered to form a square platform. The surface of the square platform has several mounting holes, and the testing platform is detachably mounted on the square platform through the mounting holes. An adjustment mechanism is provided at the bottom of the platform, which is connected to the first and second support columns. The distance between the first and second support columns is adjusted by the adjustment mechanism to control the length and width of the square platform and to replace testing platforms of different sizes.

[0007] Furthermore, the adjustment mechanism includes two sets of first drive components, which are symmetrically distributed on the side of the support platform away from the support components. One end of each first drive component is connected to a push plate, and the sides of the two push plates away from the first drive components are respectively connected to several first support columns and second support columns, so that the first drive components drive the first support columns and second support columns to adjust the length of the square platform.

[0008] Two push plates are respectively provided with folding and telescopic structures between them and a number of first support columns and a number of second support columns. One side of the folding and telescopic structure is connected to the push plate, and a number of connecting frames are provided in the middle of the folding and telescopic structure. The ends of the connecting frames away from the folding and telescopic structure are respectively connected to the corresponding first support columns and second support columns, so that the folding and telescopic structure can adjust the width of the square platform.

[0009] Furthermore, the lifting assembly includes a first telescopic assembly, a second telescopic assembly, and a third telescopic assembly with their bottoms set on the first support column, and the line connecting the first telescopic assembly and the second telescopic assembly is perpendicular to the line connecting the second telescopic assembly and the third telescopic assembly, so that the first telescopic assembly, the second telescopic assembly, and the third telescopic assembly form a right-angled triangle.

[0010] An adjustable connecting structure is provided between the first telescopic component and the third telescopic component, and the middle part of the connecting structure is connected to the detection component.

[0011] Furthermore, the first support column has two sets of sliding grooves, and the second support column has one set of sliding grooves.

[0012] Each slide is equipped with a movable component, the top of which is connected to the bottom of the corresponding first telescopic component, second telescopic component and third telescopic component respectively;

[0013] The movable component includes a movable frame with an open top. The movable frame is slidably connected to the slide grooves corresponding to the first support column and the second support column, respectively. A self-locking component is provided between the movable frame and the corresponding slide groove to lock the slide groove and the movable frame.

[0014] The movable frame is internally connected to a threaded rod, and the end of the threaded rod is provided with a driving structure to drive the threaded rod to rotate. The part of the threaded rod located inside the movable frame is threadedly connected to a threaded sleeve. The outer side of the threaded sleeve is slidably connected to the inner wall of the movable frame. The side of the threaded sleeve away from the movable frame is connected to the bottom of the corresponding first telescopic component, second telescopic component and third telescopic component.

[0015] Furthermore, the self-locking component includes a rectangular groove formed on the first support column / second support column, a magnetic rod slidably connected to the rectangular groove, one end of the magnetic rod passing through the rectangular groove, and the other end of the magnetic rod away from the rectangular groove being inserted into the side of the movable frame;

[0016] An electromagnet is installed on the other side of the magnetic rod, which drives the magnetic rod to move away from / near the moving frame.

[0017] Furthermore, the connecting structure includes a third connecting block that is slidably sleeved on the outside of the first telescopic component, a second connecting block that is slidably sleeved on the outside of the second telescopic component, and a fourth connecting block that is slidably sleeved on the outside of the third telescopic component.

[0018] The third connecting block has a connecting structure hinged on one side, the other end of the connecting structure is hinged to the fourth connecting block, and the middle part of the connecting structure is connected to the detection component.

[0019] The fourth connecting block and the second connecting block are connected by a control structure, which adjusts the height of the detection component.

[0020] Furthermore, the control structure includes two first connecting blocks, which are respectively fixed to the top of the second telescopic component and the third telescopic component, and are connected to each other through a telescopic first connecting component. A second driving component is also provided on the first connecting component, and a collar is provided at the bottom of the second driving component. The collar is sleeved on the outside of the third connecting component, and one end of each of the two third connecting components is connected to the fourth connecting block and the second connecting block, respectively.

[0021] Compared with existing technologies, this aircraft main landing gear fatigue detection device has the following advantages:

[0022] I. This utility model provides a plurality of first support columns and second support columns respectively set on a support platform, and a plurality of mounting holes are provided on the first support columns and second support columns. By adjusting the distance between the first support columns and second support columns, the unfolded area of ​​the plurality of first support columns and second support columns can be adjusted, thereby installing test platforms of different sizes, so as to apply loads to landing gear of different sizes for simulated testing, thus solving the problem that the existing landing gear placement platform is not easy to adjust in size, which affects the adaptability of the testing device.

[0023] II. This utility model installs the detection component on top through the first telescopic component, the second telescopic component, and the third telescopic component, and adjusts the height through the fifth drive component. Then, the hydraulic lifting in the detection component is used to apply a downward load to facilitate the detection of landing gear at different heights. Attached Figure Description

[0024] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0025] Figure 2 This is a schematic diagram of the three-dimensional structure of the movable frame in this utility model;

[0026] Figure 3 This is a three-dimensional structural diagram of the push plate in this utility model;

[0027] Figure 4 This is a three-dimensional structural diagram of the first support column in this utility model;

[0028] Figure 5 This is a three-dimensional structural diagram of the first telescopic component in this utility model;

[0029] Figure 6 This is a three-dimensional structural diagram of the first connecting cylinder in this utility model.

[0030] In the diagram: 1. Support platform; 2. Support assembly; 201. First support column; 202. Second support column; 3. Detection platform; 4. First drive assembly; 5. Push plate; 6. Folding telescopic structure; 7. Connecting frame; 8. Moving frame; 9. Magnetic rod; 10. Electromagnet; 11. Threaded rod; 12. Threaded sleeve; 13. First telescopic assembly; 14. Second telescopic assembly; 15. Third telescopic assembly; 16. First connecting block; 17. First connecting assembly; 18. Second drive assembly; 19. Third connecting assembly; 20. Second connecting block; 21. Second connecting assembly; 22. Third connecting block; 23. Fourth connecting block; 24. Fourth telescopic assembly; 25. Third drive assembly; 26. Detection assembly; 27. Calibration block. Detailed Implementation

[0031] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0032] like Figure 1-6As shown, this utility model provides a technical solution: an aircraft main landing gear fatigue testing device, including a support platform 1, a support assembly 2 above the support platform 1, a testing platform 3 and a lifting assembly at the top of the support assembly 2, and a testing assembly 26 on one side of the lifting assembly above the testing platform 3, through which the testing assembly 26 applies a vertical load to the landing gear on the testing platform 3; the support assembly 2 includes several horizontally arranged first support columns 201 and second support columns 202, both of which are slidably connected to the top of the support platform 1, and the bottom of the lifting assembly is disposed on the several first support columns 201 and second support columns 202. On the support column 202; the first support column 201 and the second support column 202 are of the same length, and the first support column 201 and the second support column 202 are staggered in sequence, forming a square platform through several first support columns 201 and second support columns 202. The surface of the square platform is provided with several mounting holes, and the detection platform 3 is detachably mounted on the square platform through the mounting holes; the bottom of the support platform 1 is provided with an adjustment mechanism, which is connected to the first support column 201 and the second support column 202 respectively. The distance between the first support column 201 and the second support column 202 is adjusted by the adjustment mechanism to control the length and width of the square platform and replace the detection platform 3 of different sizes.

[0033] In use, each of the first support columns 201 and the second support columns 202 has several mounting holes at equal intervals, allowing the testing platform 3 to be detachably mounted on the top of the first support column 201 / second support column 202 through these holes. The bottom of the testing platform 3 is in contact with the top of the first support column 201 and the second support column 202. The first support columns 201 and the second support columns 202 are arranged sequentially from front to back, that is, along the width of the square platform. Both the first support columns 201 and the second support columns 202 are elongated and distributed left and right. In the initial state when the square platform is at its smallest, the sequence from front to back is: first first support column 201, first second support column 202, second first support column 201, second second support column 202. 2. Similarly, the gap between the first support column 201 and the second support column 202 is zero. When it is necessary to increase the width of the square platform, the width of the square platform is adjusted by driving the first support column 201 and the second support column 202 to move away from each other in the front-back direction. When it is necessary to increase the length of the square platform, the length is the same as the length of the lower support platform 1 in the initial state. The length of the square platform is adjusted by driving the first support column 201 and the second support column 202 to move away from each other in the left-right direction. When adjusting the width / length, the mounting hole is moved at the same time, thereby replacing the detection platform 3 of different sizes. The bottom of the detection platform 3 contacts the top of the first support column 201 and the second support column 202 to support the detection platform 3.

[0034] The adjustment mechanism includes two sets of first drive components 4, which are symmetrically distributed on the side of the support platform 1 away from the support component 2. One end of each first drive component 4 is connected to a push plate 5. The sides of the two push plates 5 away from the first drive components 4 are respectively connected to several first support columns 201 and second support columns 202, so that the first drive components 4 drive the first support columns 201 and second support columns 202 to adjust the length of the square platform. A folding telescopic structure 6 is provided between the two push plates 5 and the corresponding several first support columns 201 and several second support columns 202. One side of the folding telescopic structure 6 is connected to the push plate 5. Several connecting frames 7 are provided in the middle of the folding telescopic structure 6. The ends of the several connecting frames 7 away from the folding telescopic structure 6 are respectively connected to the corresponding first support columns 201 and second support columns 202, so that the folding telescopic structure 6 can adjust the width of the square platform.

[0035] In use, the first drive assembly 4 can be an electric push rod, fixed to the support leg of the support platform 1. The folding telescopic structure 6 can be a scissor-folding parallel four-bar telescopic structure. Its principle can be referred to as a scissor lift. The drive end is located on one side of the push plate 5 and fixed to the push plate 5 by a rectangular column. Then, two scissor lift structures are symmetrically installed. The two ends of the scissor X-shaped structure are pushed closer to each other by a screw or telescopic rod, and then extended to both sides. The connecting frames 7 are evenly distributed at the intersection of the X-shaped structure's connecting rods on the folding telescopic structure 6, so that when the folding telescopic structure 6 moves, it can drive several connecting frames 7 to move away from each other, and thus drive the adjacent first support column 201 and the two adjacent second support columns 202 to move away from each other. Then, the first drive assembly 4 drives the first support column 201 and the second support column 202 to move in the left and right directions, and the folding telescopic structure 6 drives the first support column 201 and the second support column 202 to move back and forth, so as to adjust the width and length.

[0036] The lifting assembly includes a first telescopic component 13, a second telescopic component 14, and a third telescopic component 15, the latter of which are mounted on a first support column 201 and on a second support column 202. The line connecting the first telescopic component 13 and the second telescopic component 14 is perpendicular to the line connecting the second telescopic component 14 and the third telescopic component 15, forming a right-angled triangle. An adjustable connecting structure is provided between the first telescopic component 13 and the third telescopic component 15, with the middle of the connecting structure connected to the detection component 26. During use, the two sides of the support platform 1... A horizontal tensioning platform is provided on the side, which is fixedly connected to the first support column 201 and the second support column 202 in the middle. When the width of the square platform is expanded, it expands to both sides from the first support column 201 and the second support column 202 in the middle, while the middle part remains stationary. Then, the first telescopic component 13 and the second telescopic component 14 above move synchronously a suitable distance. Then, a wider area is formed in front of the third telescopic component 15 through the right triangle and the quadrilateral, which facilitates the replacement of the landing gear and improves the efficiency of the landing gear replacement. Then, relevant data are recorded in the load simulation to analyze and judge the fatigue.

[0037] Two sets of sliding grooves are provided on the first support column 201, and one set of sliding grooves is provided on the second support column 202. Each sliding groove is equipped with a moving component, the top of which is connected to the bottom of the corresponding first telescopic component 13, second telescopic component 14, and third telescopic component 15. The moving component includes a moving frame 8 with an open top. The moving frame 8 is slidably connected to the corresponding sliding groove of the first support column 201 and the second support column 202. A self-locking component is provided between the moving frame 8 and the corresponding sliding groove to lock the sliding groove and the moving frame 8. A threaded rod 11 is rotatably connected inside the moving frame 8. A driving structure is provided at the end of the threaded rod 11 to drive the threaded rod 11 to rotate. The part of the threaded rod 11 inside the moving frame 8 is threadedly connected to a threaded sleeve 12. The outer side of the threaded sleeve 12 is slidably connected to the inner wall of the moving frame 8. The side of the threaded sleeve 12 away from the moving frame 8 is connected to the bottom of the corresponding first telescopic component 13, second telescopic component 14, and third telescopic component 15.

[0038] In use, the drive structure adopts a forward and reverse rotating motor. The motor drives the threaded rod 11 to rotate, causing the threaded rod 11 to drive the threaded sleeve 12 to slide inside the moving frame 8. The axis of the threaded rod 11 is perpendicular to the left and right directions of the first support column 201 and the second support column 202. The rotation of the threaded rod 11 drives the threaded sleeve 12 to move, which in turn drives the first telescopic component 13, the second telescopic component 14 and the third telescopic component 15 to move. This is used to adjust the width between the second telescopic component 14 and the first telescopic component 13. At the same time, the third telescopic component 15 and the second telescopic component 14 move synchronously to ensure that the three form a right-angled triangle.

[0039] The self-locking assembly includes a rectangular slot formed on the first support column 201 / second support column 202, with a magnetic rod 9 slidably connected to the rectangular slot. One end of the magnetic rod 9 passes through the rectangular slot, and the end of the magnetic rod 9 away from the rectangular slot is inserted into the side of the movable frame 8. An electromagnet 10 is provided on the other side of the magnetic rod 9 to drive the magnetic rod 9 away from / close to the movable frame 8. In use, each of the first support column 201 and second support column 202 has a sliding groove, and the movable frame 8 spans multiple sliding grooves simultaneously. Each sliding groove corresponds to one self-locking assembly. The self-locking mechanism is based on the first telescopic assembly 13 and the second telescopic assembly 14. To adjust the width between the telescopic components 14, select appropriate self-locking components on the first support column 201 and the second support column 202, so that the magnetic rod 9 is inserted into the moving frame 8 under the thrust of the electromagnet 10, and move away from the moving frame 8 along with the magnetic rod 9, so that the moving frame 8 moves with the corresponding first support column 201 and the second support column 202. First, adjust the second telescopic component 14 and the first telescopic component 13 to the appropriate position, and then further adjust them precisely through the threaded rod 11 so that the width between the first telescopic component 13 and the second telescopic component 14 is adapted to the width between the detection platform 3 below.

[0040] The connecting structure includes a third connecting block 22 slidably sleeved on the outside of the first telescopic component 13, a second connecting block 20 slidably sleeved on the outside of the second telescopic component 14, and a fourth connecting block 23 slidably sleeved on the outside of the third telescopic component 15. A connecting structure is hinged to one side of the third connecting block 22, and the other end of the connecting structure is hinged to the fourth connecting block 23. The middle part of the connecting structure is connected to the detection component 26. The fourth connecting block 23 and the second connecting block 20 are connected by a control structure, which adjusts the height of the detection component 26. In use, the connecting structure includes two fourth telescopic components 24. The ends of the two fourth telescopic components 24 are fixedly connected by a horizontal plate. The horizontal plate is hinged to the corresponding fourth connecting block 23 and third connecting block 22 so that when adjusting the width and length, the hinge and the extension and retraction of the fourth telescopic components 24 can adapt to the changes in width and length, avoiding jamming.

[0041] The third connecting block 22 and the second connecting block 20 are connected by a retractable second connecting component 21 to increase the stability above. The control structure includes two first connecting blocks 16, which are respectively fixed to the top of the second telescopic component 14 and the third telescopic component 15, and are connected by a retractable first connecting component 17. The first connecting component 17 is also provided with a second driving component 18, and the bottom end of the second driving component 18 is provided with a collar, which is sleeved on the outside of the third connecting component 19. One end of the two third connecting components 19 is respectively connected to the fourth connecting block 23 and the second connecting block 20. In use, the second driving component 18 adopts an electric push rod, which drives the third connecting component 19 to move up and down. The third connecting component 19 drives the second connecting block 20 and the fourth connecting block 23 to move up and down, which in turn drives the fourth telescopic component 24 to move up and down, thereby adjusting the height of the detection component 26.

[0042] A calibration block 27 is connected between the two third connecting components 19; a third drive component 25 is provided at one end of the fourth telescopic component 24, and one end of the third drive component 25 is connected to the detection component 26; in use, the detection component 26 includes a hydraulic rod, a connecting plate, and a mounting plate. The connecting plate is sleeved on the outside of the fourth telescopic component 24 and connected to one end of the third drive component 25. The third drive component 25 uses an electric push rod, which pushes the connecting plate to slide on the fourth telescopic component 24 to adjust the overall position of the detection component 26 and improve the accuracy of the detection component 26; the connecting plate and the mounting plate are connected by a hydraulic rod, and the mounting plate is detachably connected to the counterweight. The hydraulic rod drives the counterweight to rise and fall, applying vertical loads to the landing gear for detection; at the same time, an adjustable infrared laser rangefinder is provided on the connecting plate so that the ray is perpendicular to the side of the first connecting component 17. By observing the point where the ray falls on the calibration block 27, the relative position of the detection component 26 and the center of the square platform is determined, thereby improving the measurement accuracy.

[0043] The first connecting assembly 17, the second connecting assembly 21, the third connecting assembly 19, the first telescopic assembly 13, the second telescopic assembly 14, the third telescopic assembly 15, and the fourth telescopic assembly 24 all include a first connecting cylinder and a second connecting cylinder, which are slidably connected and have the same diameter. The bottom of the first connecting cylinder of the first telescopic assembly 13, the second telescopic assembly 14, and the third telescopic assembly 15 is connected to the corresponding threaded sleeve 12, and a fourth driving assembly is provided between the first and second connecting cylinders of the three components. The top of the second connecting cylinder of the second telescopic assembly 14 and the third telescopic assembly 15 is connected to the first connecting block 16. The fourth driving assembly uses an electric push rod to adjust the height of the second connecting cylinder. The ends of the first and second connecting cylinders of the fourth telescopic assembly 24 that are far apart from each other are hinged to the third connecting block 22 and the fourth connecting block 23, respectively. The middle parts of the first and second connecting cylinders are slidably connected to the connecting plate of the detection assembly 26. The ends of the first and second connecting cylinders of the connecting assembly 17 that are far apart from each other are respectively connected to the corresponding first connecting block 16, and the outer sides of the first and second connecting cylinders are respectively connected to the corresponding second driving assembly 18; the first connecting cylinder and the second driving assembly 18 are fixedly connected, and the corresponding second driving assembly 18 is slidably connected to the second connecting cylinder, while the other is fixedly connected to the second connecting cylinder and slidably connected to the first connecting cylinder; the ends of the first and second connecting cylinders of the second connecting assembly 21 that are far apart from each other are respectively connected to the second connecting block 20 and the third connecting block 22; the first connecting cylinders of the two third connecting assemblies 19 are respectively connected to the second connecting block 20 and the fourth connecting block 23, and the ends of the two second connecting cylinders that are far apart from the first connecting cylinder are symmetrically connected to both sides of the calibration block 27; the first and second connecting cylinders are both slidably connected to the collar; in use, the diameter of the outer layer remains unchanged during expansion and contraction through the mutual crossing of the first and second connecting cylinders, so as to facilitate the sliding of the outer layer and provide support.

Claims

1. A fatigue testing device for aircraft main landing gear, comprising a support platform (1), wherein a support assembly (2), a testing platform (3), a lifting assembly, and a testing assembly (26) are respectively arranged above the support platform (1), characterized in that: The lifting assembly is installed on the top of the support assembly (2). The support assembly (2) includes several horizontally arranged first support columns (201) and second support columns (202). The first support columns (201) and the second support columns (202) are slidably connected to the top of the support platform (1). The first support column (201) and the second support column (202) have the same length, and the first support column (201) and the second support column (202) are staggered in sequence, forming a square platform through a number of first support columns (201) and second support columns (202). The surface of the square platform is provided with a number of mounting holes, and the detection table (3) is detachably mounted on the square platform through the mounting holes. The bottom of the support platform (1) is provided with an adjustment mechanism, which is connected to the first support column (201) and the second support column (202) respectively. The distance between the first support column (201) and the second support column (202) is adjusted by the adjustment mechanism to control the length and width of the square platform and replace the detection platform (3) of different sizes.

2. The aircraft main landing gear fatigue detection device according to claim 1, characterized in that: The adjustment mechanism includes two sets of first drive components (4). The two sets of first drive components (4) are symmetrically distributed on the side of the support platform (1) away from the support component (2). One end of the first drive component (4) is connected to a push plate (5). The sides of the two push plates (5) away from the first drive component (4) are respectively connected to a plurality of first support columns (201) and second support columns (202) so that the first drive component (4) drives the first support columns (201) and the second support columns (202) to adjust the length of the square platform. The two push plates (5) are respectively provided with a folding telescopic structure (6) between them and a number of first support columns (201) and a number of second support columns (202). One side of the folding telescopic structure (6) is connected to the push plate (5). A number of connecting frames (7) are provided in the middle of the folding telescopic structure (6). The ends of the connecting frames (7) away from the folding telescopic structure (6) are respectively connected to the corresponding first support columns (201) and second support columns (202) so that the folding telescopic structure (6) can adjust the width of the square platform.

3. The aircraft main landing gear fatigue detection device according to claim 1, characterized in that: The lifting assembly includes a first telescopic assembly (13) and a second telescopic assembly (14) with their bottoms set on a first support column (201) and a third telescopic assembly (15) with their bottoms set on a second support column (202). The line connecting the first telescopic assembly (13) and the second telescopic assembly (14) is perpendicular to the line connecting the second telescopic assembly (14) and the third telescopic assembly (15), so that a right triangle is formed between the first telescopic assembly (13), the second telescopic assembly (14) and the third telescopic assembly (15). A retractable connection structure is provided between the first telescopic component (13) and the third telescopic component (15), and the middle part of the connection structure is connected to the detection component (26).

4. The aircraft main landing gear fatigue detection device according to claim 1, characterized in that: The first support column (201) has two sets of sliding grooves, and the second support column (202) has one set of sliding grooves; Each of the slides is provided with a movable component, the top of which is connected to the bottom of the corresponding first telescopic component (13), second telescopic component (14) and third telescopic component (15); The moving component includes a moving frame (8) with an open top. The moving frame (8) is slidably connected to the corresponding slides of the first support column (201) and the second support column (202). A self-locking component is provided between the moving frame (8) and the corresponding slide to lock the slide and the moving frame (8). The movable frame (8) is rotatably connected to a threaded rod (11). The end of the threaded rod (11) is provided with a driving structure, which drives the threaded rod (11) to rotate. The part of the threaded rod (11) located inside the movable frame (8) is threadedly connected to a threaded sleeve (12). The outer side of the threaded sleeve (12) is slidably connected to the inner wall of the movable frame (8). The side of the threaded sleeve (12) away from the movable frame (8) is connected to the bottom of the corresponding first telescopic component (13), second telescopic component (14) and third telescopic component (15).

5. The aircraft main landing gear fatigue detection device according to claim 4, characterized in that: The self-locking assembly includes a rectangular groove formed on the first support column (201) / second support column (202), and a magnetic rod (9) is slidably connected to the rectangular groove. One end of the magnetic rod (9) passes through the rectangular groove, and the end of the magnetic rod (9) away from the rectangular groove is inserted into the side of the movable frame (8). An electromagnet (10) is provided on the other side of the magnetic rod (9), which serves to drive the magnetic rod (9) away from / near the moving frame (8).

6. The aircraft main landing gear fatigue detection device according to claim 3, characterized in that: The connection structure includes a third connecting block (22) that is slidably sleeved on the outside of the first telescopic component (13), a second connecting block (20) that is slidably sleeved on the outside of the second telescopic component (14), and a fourth connecting block (23) that is slidably sleeved on the outside of the third telescopic component (15). The third connecting block (22) has a connecting structure hinged on one side, the other end of the connecting structure is hinged to the fourth connecting block (23), and the middle part of the connecting structure is connected to the detection component (26). The fourth connecting block (23) and the second connecting block (20) are connected by a control structure, and the height of the detection component (26) is adjusted by the control structure.

7. The aircraft main landing gear fatigue detection device according to claim 6, characterized in that: The control structure includes two first connecting blocks (16), which are fixed on the top of the second telescopic component (14) and the third telescopic component (15) respectively. The two first connecting blocks (16) are connected by a telescopic first connecting component (17). A second driving component (18) is also provided on the first connecting component (17). A collar is provided at the bottom of the second driving component (18). The collar is sleeved on the outside of the third connecting component (19). One end of the two third connecting components (19) is connected to the fourth connecting block (23) and the second connecting block (20) respectively.

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