An aircraft panel structure strength inspection device
The aircraft panel structure strength testing device, which uses a hydraulic cylinder and lead screw, solves the problem of sliding and displacement caused by poor fixation, and achieves stable and accurate aircraft panel strength testing.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- CHENGDU HONGXIA TECH CO LTD
- Filing Date
- 2022-07-18
- Publication Date
- 2026-06-02
AI Technical Summary
Existing aircraft panel strength testing devices have poor fixation, causing the aircraft panels to easily slide and shift during testing, affecting the accuracy of the test results and making it difficult to accurately test different locations.
A strength testing device for aircraft panel structures was designed. It uses a hydraulic cylinder to drive a pressure head to apply pressure, combined with pressure sensor monitoring. The device achieves limit clamping through the cooperation of a lead screw and a slider, and the cylinder adjusts the clamping block. The cooperation of the U-shaped frame and the limit rod ensures the stability of movement and adapts to the strength testing of different positions.
It ensures the stability of the aircraft panel, prevents slippage and displacement, improves the accuracy of inspection data, and can adapt to strength inspections in different locations, obtaining multiple sets of accurate data.
Smart Images
Figure CN117451518B_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of aircraft panel processing technology, and in particular relates to an aircraft panel structural strength testing device. Background Technology
[0002] Aircraft panels are generally thin-walled curved components. After the aircraft panels are manufactured, they need to undergo strength testing to ensure safety during later use.
[0003] Currently, existing aircraft panel fixing methods are ineffective during strength testing. When subjected to pressure, the panels are prone to slippage and displacement, affecting test results. Furthermore, most testing devices are not suitable for testing different locations on the aircraft panel, resulting in inaccurate test data and impacting the accuracy of the tests. To address these issues, we have designed an aircraft panel structural strength testing device. Summary of the Invention
[0004] To solve the above-mentioned technical problems, the present invention is achieved through the following technical solution:
[0005] This invention relates to an aircraft panel structural strength testing device, comprising a testing table and conveyor frames. Several conveyor frames are horizontally arranged on the upper surface of the testing table. The upper surface of the testing table has several first sliding grooves, each containing a first lead screw. Two sliders are threaded onto the first lead screw, and a limit frame is fixed to the upper surface of each slider. A cylinder is installed on the upper surface of the limit frame, and a locking block is connected to the telescopic end of the cylinder. Second sliding grooves are formed on both the front and rear sides of the upper surface of the testing table, each containing a second lead screw. A U-shaped frame is positioned between two second lead screws, and a through groove is formed on the upper surface of the U-shaped frame. A third lead screw is threaded onto the through groove, and a movable block is threaded onto the third lead screw. A hydraulic cylinder is installed on the lower surface of the movable block, and a pressure sensor is connected to the output end of the hydraulic cylinder. A pressure head is connected to the lower side of the pressure sensor.
[0006] The hydraulic cylinder drives the pressure head to move up and down, applying pressure to the aircraft panel for strength testing. Combined with a pressure sensor, the pressure application is easily monitored, facilitating observation and recording by staff. The conveyor frame facilitates the loading and unloading of the aircraft panel to be tested. The threaded engagement between the first lead screw and the slider allows for adjustment of the two sliders, moving them closer or further apart, which in turn moves the limiting frames on both sides to clamp the aircraft panel. Simultaneously, the cylinder-adjustable locking block presses against the edge of the aircraft panel, further pressing and fixing it, ensuring the panel's stability and preventing slippage during testing that could affect the results. The third lead screw allows for adjustment of the movable block's forward and backward movement, which in turn moves the pressure head forward and backward. Combined with the second lead screw, it allows for adjustment of the U-shaped frame's left and right movement, which in turn moves the pressure head left and right, adapting to strength testing at different locations on the aircraft panel, facilitating the acquisition of multiple sets of data, and improving the accuracy of the test data.
[0007] Preferably, a movable groove is provided on the rear side of the through groove, and the rear end of the third lead screw extends into the movable groove and is connected to a driven gear. A driving gear meshes with the right side of the driven gear. A limit rod is provided inside the driving gear, and several protrusions are provided on the outer surface of the limit rod, which cooperate with the driving gear. The cooperation between the limit rod and the protrusions facilitates the limiting of the U-shaped frame, ensuring the stability of the U-shaped frame moving left and right in the horizontal direction. At the same time, the limit rod and the protrusions work together to drive the driving gear to rotate. Combined with the meshing of the driving gear and the driven gear, the third lead screw is driven to rotate, thereby achieving the purpose of adjusting the pressure head to move back and forth.
[0008] Preferably, the conveyor frame includes a conveyor roller and a fixing plate. Several fixing plates are arranged opposite each other on the front and rear sides of the upper surface of the inspection table, and the front and rear ends of the conveyor roller are respectively rotatably engaged with the front and rear fixing plates.
[0009] Preferably, the lower part of the limiting frame and the inner side of the locking block are inclined structures, and a limiting baffle is fixed on the right side of the upper surface of the inspection table. The inclined structure of the lower part of the limiting frame and the inner side of the locking block facilitates the fit with the aircraft panel and improves the fixing effect of the aircraft panel. The limiting baffle limits the right end of the aircraft panel, further ensuring the stability of the aircraft panel.
[0010] Preferably, the upper surface of the inspection table is provided with a strip groove, and a plurality of rotating rods are arranged inside the strip groove. The rear end of the rotating rod passes through the inner wall of the strip groove and is connected to the front end of the first lead screw. A first pulley is provided on the rotating rod. A first motor is installed on the lower surface of the inspection table. The output end of the first motor is connected to a rotating shaft. A plurality of second pulleys are arranged on the rotating shaft. The first pulleys and second pulleys correspond one-to-one and cooperate with each other. The plurality of second pulleys are respectively connected to the first pulleys on the left and right sides by a first belt. Through the transmission cooperation of the first belt, the first pulleys and the second pulleys, combined with the first motor, it is easy to drive the rotation of the first lead screw, realize the relative movement of the adjustment limit frame, and facilitate the fixing and removal of the aircraft panel.
[0011] Preferably, a fixing block is fixed to the front side of the lower surface of the inspection table, and the front end of the rotating shaft is connected to the fixing block.
[0012] Preferably, the right ends of both second lead screws pass through the right surface of the inspection table and are connected to third pulleys. A second belt is provided between the front and rear third pulleys for transmission. The right end of the central shaft of the rear third pulley is connected to a second motor. Through the transmission action of the second belt, combined with the second motor, it is easy to drive the rotation of the second lead screws to achieve the purpose of adjusting the left and right movement of the U-shaped frame.
[0013] Preferably, two support plates are arranged opposite each other on the rear side of the upper surface of the inspection table. The left end of the limiting rod is rotatably engaged with the left support plate, and the right end of the limiting rod passes through the right support plate and is connected to a third motor. The third motor facilitates the rotation of the limiting rod, thereby achieving the purpose of adjusting the pressure head to move back and forth.
[0014] Preferably, a support base is provided on the lower surface of the inspection table, and the lower surface of the first motor is in contact with the support base.
[0015] The present invention has the following beneficial effects:
[0016] 1. This invention uses a hydraulic cylinder to move the pressure head up and down to apply pressure to the aircraft panel for strength testing. Combined with a pressure sensor, the pressure application is easily monitored, facilitating observation and recording by personnel. The conveyor frame facilitates the loading and unloading of the aircraft panel to be tested. The threaded engagement between the first lead screw and the slider allows for adjustment of the two sliders, moving them closer or further apart, which in turn moves the limiting frames on both sides to clamp the aircraft panel. Simultaneously, a cylinder-adjustable locking block presses against the edge of the aircraft panel, further pressing and fixing it, ensuring the panel's stability and preventing slippage during testing that could affect the results. The third lead screw allows for adjustment of the movable block's forward and backward movement, which in turn moves the pressure head forward and backward. Combined with the second lead screw, it allows for adjustment of the U-shaped frame's left and right movement, which in turn moves the pressure head left and right, adapting to strength testing at different locations on the aircraft panel, facilitating the acquisition of multiple sets of data, and improving the accuracy of the test data.
[0017] 2. The present invention uses a limiting rod and a protruding strip to cooperate in order to limit the U-shaped frame and ensure the stability of the U-shaped frame moving left and right in the horizontal direction. At the same time, the limiting rod and the protruding strip work together to drive the drive gear to rotate. Combined with the meshing of the drive gear and the driven gear, the third lead screw is driven to rotate, so as to achieve the purpose of adjusting the pressure head to move back and forth.
[0018] 3. The present invention uses the inclined structure of the lower part of the limiting frame and the inner side of the locking block to facilitate fitting with the aircraft panel and improve the fixing effect of the aircraft panel. The limiting baffle limits the right end of the aircraft panel, further ensuring the stability of the aircraft panel.
[0019] Of course, any product implementing this invention does not necessarily need to achieve all of the advantages described above at the same time. Attached Figure Description
[0020] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0021] Figure 1 This is a schematic diagram of the overall structure of the present invention;
[0022] Figure 2 This is the front view of the present invention;
[0023] Figure 3 for Figure 2 Schematic diagram of the structure of section AA;
[0024] Figure 4 for Figure 3Enlarged structural diagram at point B;
[0025] Figure 5 for Figure 2 Schematic diagram of the structure of the mid-section CC;
[0026] Figure 6 This is a top view of the present invention;
[0027] Figure 7 for Figure 6 Schematic diagram of the structure of the mid-section DD;
[0028] Figure 8 This is a schematic diagram of the structure of the present invention;
[0029] Figure 9 for Figure 8 A magnified structural diagram at point E in the middle.
[0030] The attached diagram lists the components represented by each number as follows:
[0031] 1. Inspection table; 2. Conveyor frame; 3. First chute; 4. First lead screw; 5. Slider; 6. Limiting frame; 7. Clamping block; 8. Cylinder; 9. Second chute; 10. Second lead screw; 11. U-shaped frame; 12. Third lead screw; 13. Driven gear; 14. Driving gear; 15. Limiting rod; 16. Protruding strip; 17. Movable block; 18. Hydraulic cylinder; 19. Pressure sensor; 20. Pressure head; 21. Limiting baffle; 22. First pulley; 23. Second pulley; 24. First belt; 25. First motor; 26. Third pulley; 27. Second belt; 28. Second motor; 29. Support plate; 30. Third motor; 31. Support base frame. Detailed Implementation
[0032] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.
[0033] In the description of this invention, it should be understood that the terms "upper," "middle," "outer," "inner," etc., which indicate orientation or positional relationship, are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the components or elements referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting this invention.
[0034] Please see Figures 1-9As shown, the present invention is an aircraft panel structural strength testing device, including a testing table 1 and a conveyor frame 2. Several conveyor frames 2 are arranged horizontally on the upper surface of the testing table 1. Several first sliding grooves 3 are formed on the upper surface of the testing table 1. A first lead screw 4 is set inside the first sliding groove 3. Two sliders 5 are threadedly fitted on the first lead screw 4. A limit frame 6 is fixed on the upper surface of the slider 5. A cylinder 8 is installed on the upper surface inside the limit frame 6. A locking block 7 is connected to the telescopic end of the cylinder 8. Second sliding grooves 9 are formed on both the front and rear sides of the upper surface of the testing table 1. A second lead screw 10 is set inside the second sliding groove 9. A U-shaped frame 11 is set between the two second lead screws 10. A through groove is formed on the upper surface of the U-shaped frame 11. A third lead screw 12 is set inside the through groove. A movable block 17 is threadedly fitted on the third lead screw 12. A hydraulic cylinder 18 is installed on the lower surface of the movable block 17. A pressure sensor 19 is connected to the output end of the hydraulic cylinder 18. A pressure head 20 is connected to the lower side of the pressure sensor 19.
[0035] The hydraulic cylinder 18 drives the pressure head 20 to move up and down, applying pressure to the aircraft panel for strength testing. Combined with the pressure sensor 19, the pressure application is easily monitored, facilitating observation and recording by staff. The conveyor frame 2 facilitates the loading and unloading of the aircraft panel to be tested. The threaded engagement between the first lead screw 4 and the slider 5 allows for adjustment of the two sliders 5, moving them closer or further apart, which in turn moves the limiting frames 6 on both sides, clamping the aircraft panel on both sides. Simultaneously, the cylinder 8 adjusts the locking block 7 to press against the edge of the aircraft panel, further pressing and fixing it, ensuring the stability of the aircraft panel and preventing slippage during the testing process that could affect the test results. The third lead screw 12 allows for adjustment of the movable block 17's forward and backward movement, which in turn moves the pressure head 20 forward and backward. Combined with the second lead screw 10, it allows for adjustment of the U-shaped frame 11's left and right movement, which in turn moves the pressure head 20 left and right, adapting to strength testing at different positions on the aircraft panel, facilitating the acquisition of multiple sets of data, and improving the accuracy of the test data.
[0036] The lower part of the limiting frame 6 and the inner side of the locking block 7 are both inclined structures. The upper right side of the inspection table 1 is fixed with a limiting baffle 21. The inclined structure of the lower part of the limiting frame 6 and the inner side of the locking block 7 facilitates the fit with the aircraft panel and improves the fixing effect of the aircraft panel. The limiting baffle 21 limits the right end of the aircraft panel, further ensuring the stability of the aircraft panel.
[0037] A movable groove is provided on the rear side of the through groove. The rear end of the third lead screw 12 extends into the movable groove and is connected to a driven gear 13. A driving gear 14 meshes with the right side of the driven gear 13. A limit rod 15 is provided inside the driving gear 14, and several protrusions 16 are provided on the outer surface of the limit rod 15, which cooperate with the driving gear 14. Two support plates 29 are arranged opposite each other on the rear side of the upper surface of the inspection table 1. The left end of the limit rod 15 is rotatably engaged with the left support plate 29, and the right end of the limit rod 15 passes through the right support plate 29 and is connected to a third motor 30. The limiting rod 15 and the protruding strip 16 work together to limit the U-shaped frame 11, ensuring the stability of the U-shaped frame 11 moving left and right in the horizontal direction. At the same time, the limiting rod 15 and the protruding strip 16 work together to drive the drive gear 14 to rotate. Combined with the meshing of the drive gear 14 and the driven gear 13, the third lead screw 12 is driven to rotate, so as to achieve the purpose of adjusting the pressure head 20 moving back and forth. The third motor 30 can drive the limiting rod 15 to rotate, so as to achieve the purpose of adjusting the pressure head 20 moving back and forth. The support plate 29 ensures the stability of the limiting rod 15.
[0038] The upper surface of the inspection table 1 has a strip-shaped groove, inside which are arranged several rotating rods. The rear ends of the rotating rods pass through the inner wall of the strip-shaped groove and are connected to the front end of the first lead screw 4. A first pulley 22 is arranged on the rotating rod. A first motor 25 is installed on the lower surface of the inspection table 1. The output end of the first motor 25 is connected to a rotating shaft. Several second pulleys 23 are arranged on the rotating shaft. The first pulleys 22 and the second pulleys 23 correspond one-to-one and cooperate with each other. The several second pulleys 23 are respectively connected to the first pulleys 22 on the left and right sides by first belts 24. A front side of the lower surface of the inspection table 1 is fixed with A fixed block is connected to the front end of the rotating shaft. A support base 31 is provided on the lower surface of the inspection table 1. The lower surface of the first motor 25 contacts the support base 31. Through the transmission cooperation of the first belt 24, the first pulley 22, and the second pulley 23, combined with the first motor 25, the first lead screw 4 is easily driven to rotate, thereby realizing the relative movement of the adjustment limit frame 6. This facilitates the fixing and placement of the aircraft panel. The fixed block ensures the stability of the rotating shaft and the second pulley 23, while the support base 31 ensures the support stability of the bottom of the device and the stability of the first motor 25.
[0039] The conveyor frame 2 includes a conveyor roller and a fixed plate. Several fixed plates are arranged opposite each other on the front and rear sides of the upper surface of the inspection table 1. The front and rear ends of the conveyor roller are respectively rotatably engaged with the front and rear fixed plates. The rotatable engagement between the conveyor roller and the fixed plate facilitates the left and right pushing of the aircraft panel.
[0040] The right ends of the two second lead screws 10 pass through the right surface of the inspection table 1 and are connected to the third pulleys 26. A second belt 27 is installed between the front and rear third pulleys 26 for transmission. The right end of the central shaft of the rear third pulley 26 is connected to the second motor 28. Through the transmission action of the second belt 27, combined with the second motor 28, it is easy to drive the rotation of the second lead screws 10, so as to achieve the purpose of adjusting the left and right movement of the U-shaped frame 11.
[0041] Example 1: When using this invention, firstly, the cylinder 8, hydraulic cylinder 18, pressure sensor 19, first motor 25, second motor 28 and third motor 30 are all connected to the external control mechanism and the display. At the same time, the aircraft panel to be inspected is placed on the conveyor frame 2. Under the action of the conveyor frame 2, the aircraft panel is pushed to the right until the right end of the aircraft panel abuts against the limit baffle 21.
[0042] At this time, the first motor 25 is driven by an external control mechanism. Under the action of the rotating shaft, the second pulley 23 is driven to rotate. Combined with the transmission action of the first belt 24, the first pulley 22 is driven to rotate. Through the rotating rod inside the first pulley 22, the first lead screw 4 is driven to rotate. Combined with the threaded engagement between the first lead screw 4 and the slider 5, the two sliders 5 are adjusted to move closer to each other, thereby driving the limit frames 6 on both sides to move towards the aircraft panel until the inclined surface of the lower part of the limit frame 6 contacts the lower surface of the aircraft panel, thus limiting and clamping the two sides of the aircraft panel. At the same time, the cylinder 8 is activated. Under the action of the cylinder 8, the clamping block 7 is driven to move downward and clamp at the edge of the aircraft panel, pressing and fixing the aircraft panel to ensure the stability of the aircraft panel and effectively preventing the aircraft panel from sliding or shifting during the pressure process, which would affect the accuracy of the inspection data.
[0043] During the strength test, the second motor 28 is started, and under the transmission action of the second belt 27 and the third pulley 26, the two second lead screws 10 at the front and rear are driven to rotate simultaneously, thereby driving the U-shaped frame 11 to move to the left and driving the pressure head 20 to move directly above the aircraft panel.
[0044] The limiting rod 15 effectively limits the movement of the U-shaped frame 11, ensuring the stability of the U-shaped frame 11 during movement. The limiting rod 15, the protrusion 16 and the U-shaped frame 11 are connected by a bearing rotational engagement.
[0045] Simultaneously, the third motor 30 is driven, which, under the action of the bearing, drives the limit rod 15 and the convex strip 16 to rotate relative to the U-shaped frame 11, thereby driving the drive gear 14 to rotate. Combined with the meshing of the drive gear 14 and the driven gear 13, it drives the rotation of the third lead screw 12. The third lead screw 12 drives the movable block 17 to move back and forth to the appropriate position, and starts the hydraulic cylinder 18 to drive the pressure head 20 to move down to contact the aircraft wall panel. The hydraulic cylinder 18 continues to apply pressure, and the pressure sensor 19 monitors the pressure application in real time and transmits the pressure data to an external display for easy viewing and recording by the staff.
[0046] After the inspection is completed, the drive cylinder 8 retracts, causing the locking block 7 to disengage from the edge of the aircraft panel. At the same time, the first motor 25 reverses, causing the limit frame 6 to move away from the aircraft panel. Finally, the aircraft panel is pulled to the left and removed from the inspection table 1.
[0047] The present invention adjusts the left and right movement of the U-shaped frame 11 by means of the second lead screw 10, and at the same time, the limit rod 15 and the protrusion 16 cooperate to drive the rotation of the drive gear 14. Combined with the meshing of the drive gear 14 and the driven gear 13, and the action of the third lead screw 12, the left and right and forward and backward movement of the pressure head 20 is adjusted, which can adapt to the strength inspection of different aircraft panel positions, facilitate the acquisition of multiple sets of inspection data, and improve the accuracy of the inspection data.
[0048] Limiting grooves are provided on both sides of the first sliding groove 3 and the inner walls of the through groove. Limiting blocks are connected to both sides of the slider 5 and the movable block 17, which cooperate with the limiting grooves to ensure the stability of the slider 5 and the movable block 17 during the forward and backward sliding process.
[0049] It should be further explained that in this invention, the cylinder 8, hydraulic cylinder 18, pressure sensor 19, first motor 25, second motor 28 and third motor 30 are all connected to an external control mechanism and a display, which facilitates operation by the staff. The display facilitates the display of the monitoring data of the pressure sensor 19, which is convenient for the staff to view and record. Moreover, all of the above components are purchased on the market, and those skilled in the art can install and use them according to the requirements.
[0050] In the description of this specification, references to terms such as "an embodiment," "example," "specific example," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.
[0051] The preferred embodiments of the present invention disclosed above are merely illustrative of the invention. These preferred embodiments do not exhaustively describe all details, nor do they limit the invention 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 the invention, thereby enabling those skilled in the art to better understand and utilize the invention. The invention is limited only by the claims and their full scope and equivalents.
Claims
1. An aircraft panel structural strength testing device, comprising a testing table (1) and conveyor frames (2), wherein a plurality of the conveyor frames (2) are arranged horizontally on the upper surface of the testing table (1), characterized in that, The inspection table (1) has several first sliding grooves (3) on its upper surface. A first lead screw (4) is installed inside the first sliding groove (3). Two sliders (5) are threaded onto the first lead screw (4). A limit frame (6) is fixed on the upper surface of the slider (5). A cylinder (8) is installed on the upper surface inside the limit frame (6). A locking block (7) is connected to the telescopic end of the cylinder (8). The inspection table (1) has second sliding grooves (9) on both the front and rear sides. A second lead screw (10) is installed inside the second sliding groove (9). A U-shaped frame (11) is installed between the two second lead screws (10). A through groove is opened on the upper surface of the U-shaped frame (11). A third lead screw (12) is installed inside the through groove. A movable block (17) is threaded onto the third lead screw (12). A hydraulic cylinder (18) is installed on the lower surface of the movable block (17). A pressure sensor (19) is connected to the output end of the hydraulic cylinder (18). A pressure head (20) is connected to the lower side of the pressure sensor (19). The back side of the through groove is provided with a movable groove. The rear end of the third lead screw (12) extends into the movable groove and is connected to a driven gear (13). The right side of the driven gear (13) is meshed with a driving gear (14). The driving gear (14) is provided with a limit rod (15) inside, and the outer surface of the limit rod (15) is provided with several protrusions (16) that cooperate with the driving gear (14). The conveying frame (2) includes a conveying roller and a fixed plate. Several fixed plates are arranged opposite to each other on the front and rear sides of the upper surface of the inspection table (1). The front and rear ends of the conveying roller are respectively rotated and cooperated with the front and rear fixed plates. The lower part of the limit frame (6) and the inner side of the clamp (7) are inclined structures. The right side of the upper surface of the inspection table (1) is fixed with a limit baffle (21).
2. The aircraft panel structure strength testing device according to claim 1, characterized in that, The upper surface of the inspection table (1) is provided with a strip groove, and a number of rotating rods are provided inside the strip groove. The rear end of the rotating rod passes through the inner wall of the strip groove and is connected to the front end of the first lead screw (4). A first pulley (22) is provided on the rotating rod. A first motor (25) is installed on the lower surface of the inspection table (1). The output end of the first motor (25) is connected to a rotating shaft. A number of second pulleys (23) are provided on the rotating shaft. The first pulleys (22) and the second pulleys (23) correspond one to one and cooperate with each other. The number of second pulleys (23) are respectively connected to the first pulleys (22) on the left and right sides by a first belt (24).
3. The aircraft panel structure strength testing device according to claim 2, characterized in that, A fixing block is fixed on the front side of the lower surface of the inspection table (1), and the front end of the rotating shaft is connected to the fixing block.
4. The aircraft panel structure strength testing device according to claim 3, characterized in that, The right ends of the two second lead screws (10) pass through the right surface of the inspection table (1) and are connected to the third pulley (26). A second belt (27) is provided between the front and rear third pulleys (26) for transmission. The right end of the central shaft of the rear third pulley (26) is connected to the second motor (28).
5. The aircraft panel structure strength testing device according to claim 4, characterized in that, The inspection table (1) has two support plates (29) arranged opposite each other on the rear side of its upper surface. The left end of the limiting rod (15) is rotatably engaged with the left support plate (29), and the right end of the limiting rod (15) passes through the right support plate (29) and is connected to a third motor (30).
6. The aircraft panel structure strength testing device according to claim 5, characterized in that, The lower surface of the inspection table (1) is provided with a support base (31), and the lower surface of the first motor (25) is in contact with the support base (31).