Aircraft lap joint flexibility test apparatus and method

Abstract

The present application provides an aviation lap wire flexibility testing device, which comprises a stretching assembly, a moving assembly, a rotating assembly and a rack, the stretching assembly and the rotating assembly are respectively arranged at two ends of the rack, the first end of the lap wire is fixedly connected with a rotating ring of the moving assembly, the second end of the lap wire passes through a fixed ring of the stretching assembly, and is connected with a tension sensor and a weight in sequence through a pulley; the present application realizes the linear motion of the rotating ring through the combination of the transverse guide rail, the vertical guide rail and the sliding blocks, and the rotating ring slides in the ring groove on the rotating connecting rod through the second sliding block and the screw sleeve, the rotating ring is fixed on the rotating connecting rod through the locking piece, the rotating radius of the lap wire can be adjusted according to the requirements, the distance between the movable table and the fixed plate is adjusted to meet the testing requirements of lap wires with various lengths, and the tension sensor can monitor the tension of the lap wire in real time, effectively improving the testing accuracy and efficiency of the lap wire.

Description

Technical Field

[0001] This invention belongs to the field of aviation component testing technology, specifically relating to an aviation connection line flexibility testing device and its testing method. Background Technology

[0002] As a component used in aircraft wiring systems, lap joints are suitable for connecting aircraft structural elements and parts. They are often used for aircraft grounding, have good environmental resistance, and low lap resistance. As flexible connectors, their durability and fatigue resistance are crucial.

[0003] Currently, the flexibility test of lap joints mainly uses the bearing end of a bending fatigue testing machine to connect the lap joint, utilizing the eccentric rotation function of the bending fatigue testing machine to achieve the test requirements. However, there are drawbacks such as the lack of protection during rotation, which can easily lead to safety accidents, the lack of closed-loop feedback, and the inability to obtain the number of times the lap joint breaks after it breaks. Furthermore, it cannot be adapted to lap joints of various lengths and cannot meet the flexibility test requirements of lap joints in actual production processes. Therefore, it is necessary to propose an aviation lap joint flexibility testing device and its testing method. Summary of the Invention

[0004] To address the problems existing in the prior art, this invention provides an aviation lap joint flexibility testing device and method. Through the combination of a horizontal guide rail, a vertical guide rail, and various sliders, a linear motion of a rotating ring is achieved. The rotating ring slides within a groove on a rotating connecting rod via a second slider and a screw sleeve. A locking component fixes the rotating ring to the rotating connecting rod, allowing the rotation radius of the lap joint to be adjusted as needed. By adjusting the distance between the movable platform and the fixed plate, various lap joint lengths can be tested. Furthermore, a tension sensor monitors the tension of the lap joint in real time, effectively improving the testing accuracy and efficiency.

[0005] This invention provides an aviation lap joint flexibility testing device, comprising a tensile component, a moving component, and a rotating component. The tensile component includes a base plate, a movable platform, a mounting base, a fixing ring, a pulley, a tension sensor, and lap joints. The base plate is mounted on a frame. The movable platform is located at a first end of the base plate. The mounting base is located above the movable platform. The fixing ring is connected to the first end of the mounting base. The pulley is located at the second end of the mounting base. The tension sensor and a weight are both located on the side of the movable platform, and the tension sensor is connected to the weight via the lap joint. The moving component includes a fixed plate, a connecting block, a vertical guide rail, a guide rail seat, a first slider, a horizontal guide rail, a second slider, a rotating ring, and an inclined support. The fixed plate is vertically mounted in the middle of the frame via the connecting block and the inclined support. The vertical guide rails are symmetrically arranged on both sides of the fixed plate via the guide rail seats. The horizontal guide rails are perpendicular to the vertical guide rails. The two ends of the horizontal guide rails are slidably connected to the vertical guide rails via the first slider. The second slider is mounted on a... The rotating ring is disposed on the first end face of the second slider and slidably connected to the transverse guide rail. The first end of the overlapping line is fixedly connected to the rotating ring, and the second end of the overlapping line passes through the fixed ring of the tension assembly and is connected to the tension sensor and the weight in sequence via pulleys. The rotating assembly includes a drive motor, a motor frame, a rotating connecting rod, a screw sleeve, a screw, a fixing block, a screw seat, and a locking component. The drive motor is disposed at the second end of the frame via the motor frame. The middle part of the rotating connecting rod is connected to the output shaft of the drive motor via the fixing block. Both ends of the rotating connecting rod are provided with first annular grooves. The screw sleeve is disposed in the first annular groove and the bottom end of the screw sleeve is fixedly connected to the second end face of the second slider. The screw passes through the screw sleeve and the two are threadedly connected. Both ends of the screw are respectively connected to the fixing block and the screw seat. A second annular groove is provided on the side of the rotating connecting rod. The locking component is disposed in the second annular groove, and the screw sleeve is snapped onto the rotating connecting rod by the locking component.

[0006] Preferably, the base plate has multiple mounting holes in the middle, allowing the distance between the movable platform and the fixed plate to be adjusted according to the need for different lengths of overlapping lines.

[0007] Preferably, both ends of the rotating link are arc surfaces, the rotating link is disposed in the through hole opened in the fixed plate, and the rotating link rotates around the output shaft of the drive motor.

[0008] Preferably, the boss on the output shaft of the drive motor is sequentially engaged with the groove in the middle of the connecting block and the rotating connecting rod.

[0009] Preferably, the mounting base has a through hole with a diameter larger than that of the lap joint.

[0010] Preferably, the inclined brackets are symmetrically arranged on both sides of the motor frame.

[0011] A second aspect of the present invention provides a testing method for an aircraft splice line flexibility testing device, comprising the following steps:

[0012] S1. Select N segments of the same length to be tested for the lap joint;

[0013] S2. According to the flexibility test requirements of the lap joint, adjust the distance between the movable platform and the fixed plate, and set the rotation radius of the lap joint by adjusting the position of the rotating ring on the rotating connecting rod through the screw sleeve and screw.

[0014] S3. Fix the first end of the lap joint to the rotating ring of the moving component, so that the second end of the lap joint bears the tension, and set the test weight as needed.

[0015] S4. Start the drive motor in the rotating assembly to drive the rotating connecting rod to rotate in a conical shape at an angle of 22°±2°, and ensure that the connecting line is free from torsional force during rotation and only performs circular motion. Set the speed of the rotating motor as needed.

[0016] S5. Measure the pull-out force of the lap joint during rotation using a tension sensor, and take the average value of the tension values ​​of N sample segments. After the test, check the resistance value and pull-out force of the lap joint. If they meet the requirements, they are qualified; otherwise, they are deemed unqualified.

[0017] Preferably, the test weight is set to 8.9 N ± 0.5 N.

[0018] Preferably, the speed of the drive motor is controlled between 30 r / min and 65 r / min, and the cycle is repeated 300,000 times.

[0019] The features and beneficial effects of this invention are:

[0020] 1. The present invention provides an aviation lap joint flexibility testing device. Through the combination of a horizontal guide rail, a vertical guide rail, and various sliders, the linear motion of a rotating ring is achieved. The rotating ring slides in the ring groove on the rotating connecting rod via a second slider and a screw sleeve. The rotating ring is fixed to the rotating connecting rod by a locking component, so that the rotation radius of the lap joint can be adjusted according to requirements. The device has a simple structure and is easy to operate.

[0021] 2. The aviation lap joint flexibility testing device of the present invention can meet the testing requirements of lap joints of various lengths by adjusting the distance between the movable platform and the fixed plate. Furthermore, a tension sensor is installed on the lap joint to monitor the tension of the lap joint in real time, forming a closed-loop feedback with the drive motor to ensure the overall safe and stable operation, effectively improving the testing accuracy and efficiency of lap joints. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the overall structure of the aviation connection line flexibility testing device of the present invention;

[0023] Figure 2 This is a front view schematic diagram of the overall aviation connection line flexibility testing device of the present invention;

[0024] Figure 3 This is a schematic diagram of the structure of the stretching component in this invention;

[0025] Figure 4 This is a schematic diagram of the structure of the moving component in this invention;

[0026] Figure 5 This is a schematic diagram of the rotating component in this invention;

[0027] Figure 6 This is an isometric schematic diagram of the rotating component in this invention;

[0028] Figure 7 This is a schematic diagram illustrating the testing principle of the aviation connection line flexibility testing device of the present invention.

[0029] Key reference numerals:

[0030] Tension assembly 1, base plate 11, mounting hole 111, movable platform 12, mounting base 13, fixing ring 14, pulley 15, tension sensor 16, weight 17, connecting line 18, moving assembly 2, fixing plate 21, connecting block 22, vertical guide rail 23, guide rail seat 24, first slider 25, horizontal guide rail 26, second slider 27, rotating ring 28, inclined bracket 29, rotating assembly 3, drive motor 31, motor frame 32, rotating connecting rod 33, first ring groove 331, second ring groove 332, screw sleeve 34, screw 35, fixing block 36, screw seat 37, locking part 38, frame 4. Detailed Implementation

[0031] To fully describe the technical content, structural features, objectives, and effects of this invention, a detailed description will be provided below in conjunction with the accompanying drawings.

[0032] This invention provides a device for testing the flexibility of aircraft connection lines, such as... Figure 1 and Figure 2 As shown, it includes a tensioning component 1, a moving component 2, a rotating component 3, and a frame 4. The tensioning component 1 and the rotating component 3 are respectively disposed at both ends of the frame 4. The rotating connecting rod 33 of the rotating component 3 is rotatably connected to the fixed plate 21 of the moving component 2.

[0033] like Figure 3As shown, the tension assembly 1 includes a base plate 11, a movable platform 12, a mounting base 13, a fixing ring 14, a pulley 15, a tension sensor 16, a weight 17, and a connecting line 18. The base plate 11 is mounted on the frame 4. The movable platform 12 is located at the first end of the base plate 11. Multiple mounting holes 111 are opened in the middle of the base plate 11. The distance between the movable platform 112 and the fixing plate 21 is adjusted according to the need for different lengths of connecting lines 18. The mounting base 13 is located above the movable platform 12. The fixing ring 14 is connected to the first end of the mounting base 13. The pulley 15 is located at the second end of the mounting base 13. A through hole is opened on the mounting base 13. The diameter of the through hole is larger than the diameter of the connecting line 18. The tension sensor 16 and the weight 17 are both located on the side of the movable platform 12, and the tension sensor 16 is connected to the weight 17 through the connecting line 18.

[0034] like Figure 4 As shown, the moving component 2 includes a fixed plate 21, a connecting block 22, a vertical guide rail 23, a guide rail seat 24, a first slider 25, a horizontal guide rail 26, a second slider 27, a rotating ring 28, and an inclined bracket 29. The fixed plate 21 is vertically set in the middle of the frame 4 through the connecting block 22 and the inclined bracket 29. The vertical guide rail 23 is symmetrically set on both sides of the fixed plate 21 through the guide rail seat 24. The horizontal guide rail 26 is set perpendicular to the vertical guide rail 23. The two ends of the horizontal guide rail 26 are slidably connected to the vertical guide rail 23 through the first slider 25. The second slider 27 is fitted on the horizontal guide rail 26 and the two are slidably connected. The rotating ring 28 is set on the first end face of the second slider 27. The first end of the lap line 18 is fixedly connected to the rotating ring 28. The second end of the lap line 18 passes through the fixed ring 14 of the tension component 1 and is connected to the tension sensor 16 and the weight 17 in sequence through the pulley 15. The inclined bracket 29 is symmetrically set on both sides of the motor frame 32.

[0035] like Figure 5 and Figure 6As shown, the rotating assembly 3 includes a drive motor 31, a motor frame 32, a rotating connecting rod 33, a screw sleeve 34, a screw 35, a fixing block 36, a screw seat 37, and a locking element 38. The drive motor 31 is mounted at the second end of the frame 4 via the motor frame 32. The middle part of the rotating connecting rod 33 is connected to the output shaft of the drive motor 31 via the fixing block 36. The boss on the output shaft of the drive motor 31 is sequentially engaged with the connecting block 22 and the groove in the middle of the rotating connecting rod 33. Both ends of the rotating connecting rod 33 are provided with first annular grooves 331. The screw sleeve 34 is disposed in the first annular groove and the screw sleeve... The bottom end of 34 is fixedly connected to the second end face of the second slider 37. The screw 35 passes through the screw sleeve 34 and the two are threaded together. The two ends of the screw 35 are respectively connected to the fixed block 36 and the screw seat 37. The side of the rotating connecting rod 33 is provided with a second annular groove 332. The locking member 38 is provided in the second annular groove 332. The screw sleeve 34 is fixedly connected to the rotating connecting rod 33 through the locking member 38. Both ends of the rotating connecting rod 33 are arc surfaces. The rotating connecting rod 33 is provided in the through hole opened in the fixed plate 21, and the rotating connecting rod 33 rotates around the output shaft of the drive motor 31.

[0036] like Figure 7 As shown, the testing method of the aviation splice flexibility testing device provided by the present invention includes the following steps:

[0037] S1. Select N segments of the same length to be tested, 18.

[0038] S2. According to the flexibility test requirements of the lap joint, adjust the distance between the movable platform 12 and the fixed plate 21, and adjust the position of the rotating ring 28 on the rotating connecting rod 33 through the screw sleeve 34 and screw 35 to set the rotation radius of the lap joint 18.

[0039] S3. Fix the first end of the lap joint 18 to the rotating ring 28 of the moving component 2, so that the second end of the lap joint 18 bears the tension, and set the test weight 17 as needed.

[0040] S4. Start the drive motor 31 in the rotating assembly 3 to drive the rotating connecting rod 33 to rotate in a conical shape at an angle of 22°±2°, and ensure that the connecting line 18 is not subjected to torsional force during rotation and is in a free state, only making circular motion. Set the speed of the rotating motor as needed.

[0041] S5. Measure the pull-out force of the lap joint 18 during rotation using the tension sensor 16, and take the average value of the tension values ​​of N sample segments. After the test, check the resistance value and pull-out force of the lap joint 18. If they meet the requirements, they are qualified; otherwise, they are deemed unqualified.

[0042] The test weights were set to 8.9 N ± 0.5 N, and the speed of the drive motor 31 was controlled between 30 r / min and 65 r / min, for a total of 300,000 cycles.

[0043] The following describes in further detail the aviation seam flexibility testing device and method of the present invention with reference to embodiments:

[0044] After undergoing a flexibility test of 300,000 cycles, the connection cable should not break. The resistance value and pull-out force should meet the requirements of the table below; otherwise, it is considered unqualified.

[0045]

[0046] The results of the flexibility-pull-out force test after the connection line has undergone 300,000 cycles.

[0047]

[0048] The present invention relates to an aviation lap joint flexibility testing device and method. Through the combination of a horizontal guide rail 26, a vertical guide rail 23, and various sliders, a linear motion of a rotating ring 28 is achieved. The rotating ring 28 slides within a groove on a rotating connecting rod 33 via a second slider 27 and a screw sleeve 34. A locking member 38 fixes the rotating ring 28 to the rotating connecting rod 33, allowing the rotation radius of the lap joint 18 to be adjusted as needed. By adjusting the distance between the movable platform 12 and the fixed plate 21, testing requirements for lap joints 18 of various lengths can be met. Furthermore, a tension sensor 16 monitors the tension of the lap joint 18 in real time, effectively improving the testing accuracy and efficiency of the lap joint.

[0049] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. An aircraft lap wire flexibility test apparatus, characterized by, It includes a stretching assembly, a moving assembly and a rotating assembly, The stretching assembly includes a base plate, a movable table, a mounting seat, a fixed ring, a pulley, a tension sensor and a lap joint wire, the base plate is installed on a rack, the movable table is arranged at a first end of the base plate, the mounting seat is arranged above the movable table, the fixed ring is connected with a first end of the mounting seat, the pulley is arranged at a second end of the mounting seat, the tension sensor and a weight are both located at a side of the movable table, and the tension sensor is connected with the weight through the lap joint wire; The moving assembly includes a fixed plate, a connecting block, vertical guide rails, guide rail seats, first sliding blocks, horizontal guide rails, second sliding blocks, a rotating ring and inclined supports, the fixed plate is vertically arranged in a middle part of the rack through the connecting block and the inclined supports, the vertical guide rails are symmetrically arranged on both sides of the fixed plate through the guide rail seats, the horizontal guide rails are arranged perpendicularly to the vertical guide rails, the two ends of the horizontal guide rails are respectively connected with the vertical guide rails through the first sliding blocks, the second sliding blocks are sleeved on the horizontal guide rails and are slidably connected with the horizontal guide rails, the rotating ring is arranged on a first end face of the second sliding block, a first end of the lap joint wire is fixedly connected with the rotating ring, a second end of the lap joint wire passes through the fixed ring of the stretching assembly and is sequentially connected with the tension sensor and the weight through the pulley; The rotating assembly includes a driving motor, a motor rack, a rotating connecting rod, a screw sleeve, a screw, a fixed block, a screw seat and a locking piece, the driving motor is arranged at a second end of the rack through the motor rack, the middle part of the rotating connecting rod is connected with an output shaft of the driving motor through the fixed block, the two ends of the rotating connecting rod are both provided with first ring grooves, the screw sleeve is arranged in the first ring groove and the bottom end of the screw sleeve is fixedly connected with a second end face of the second sliding block, the screw is arranged in the screw sleeve and is threadedly connected with the screw sleeve, the two ends of the screw are respectively connected with the fixed block and the screw seat, a second ring groove is arranged on a side face of the rotating connecting rod, and the locking piece is arranged in the second ring groove, and the screw sleeve is clamped on the rotating connecting rod through the locking piece.

2. The aircraft lap wire flexibility test apparatus of claim 1, wherein, A plurality of mounting holes are arranged in a middle part of the base plate, and the distance between the movable table and the fixed plate is adjusted according to the needs of lap joint wires with different lengths.

3. The aircraft lap wire flexibility test apparatus of claim 1, wherein, The two ends of the rotating connecting rod are both arc faces, the rotating connecting rod is arranged in a through hole arranged in the fixed plate, and the rotating connecting rod rotates around the output shaft of the driving motor.

4. The aircraft lap wire flexibility test apparatus of claim 1, wherein, The boss on the output shaft of the driving motor is clamped with the connecting block and the groove in the middle part of the rotating connecting rod in sequence.

5. The aircraft lap wire flexibility test apparatus of claim 1, wherein, A through hole is arranged on the mounting seat, and the diameter of the through hole is greater than the diameter of the lap joint wire.

6. The aircraft lap wire flexibility test apparatus of claim 1, wherein, The inclined supports are symmetrically arranged on both sides of the motor rack.

7. A test method for the aircraft lap joint wire flexibility test apparatus of one of claims 1 to 6, characterized in that, The method includes the following steps: S1, selecting N pieces of lap joint wires with the same length; S2, adjusting the distance between the movable table and the fixed plate according to the needs of the flexibility test of the lap joint wire, adjusting the position of the rotating ring on the rotating connecting rod through the screw sleeve and the screw, and setting the rotating radius of the lap joint wire. S3, the first end of the lap joint line is fixed on the rotating ring of the moving assembly, the second end of the lap joint line is subjected to tension, and a test weight is arranged as required; S4, the driving motor in the rotating assembly is started, the rotating connecting rod is driven to rotate in a conical shape at an angle of 22°±2°, and it is ensured that the lap joint line is in a free state only for circular motion in rotation, and the rotating speed of the rotating motor is arranged as required; S5, the pull-off force of the lap joint line in rotation is measured through the tension sensor, the average value of N sample pull-off force values is taken, the resistance value and the pull-off force of the lap joint line are checked after the test, and if the requirements are met, it is qualified, otherwise it is determined as unqualified.

8. The method of testing an aircraft lap joint wire flexibility test apparatus of claim 7, wherein, The test weight is arranged as 8.9 N±0.5 N.

9. The method of testing an aircraft lap joint wire flexibility test apparatus of claim 7, wherein, The rotating speed of the driving motor is controlled at 30r / min~65r / min, and a total cycle of 300,000 times is realized.

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